Explain the myth of the Golden Carp and explore its significance in Essay

Explain the myth of the Golden Carp and explore its significance in Antonio' spiritual coming of age in Anaya's Bless Me, Ultima - Essay Example Antonio feels difficulty to lead a life in between the conflicts of his father’s and mother families, namely, the Marez and the Juans. These conflicts, along with his mother persuasion to make him a Catholic priest and his father’s wish to join him with the Marez, wild and untamed vaqueros, also poses several questions in Antonio’s mind and seeks answers to all these questions with the help of Ultima, the Curandera—the traditional folk healer. An overview of the novel clearly brings out the role of myth which predominates from the beginning to the end. The purpose of the study is to unveil the significance of the myth of golden carp on Antonio and explore its significance in Antonios spiritual coming of age. Among the different myths used in the novel, one can see that the myth of the golden carp plays a decisive role in determining or guiding the story. â€Å"The myth of the golden carp is certainly the most significant myth used in the novel, particularly because it helps to elucidate Antonio’s increasing anxiety and eventual acceptance of the differing religious beliefs that he encounters† (Bless Me, Ultima Study Guide). The role of the minor myths on the novel also is not negligible as they help the readers to have glimpse of Mexican –American culture. When tracing the origin of the myths, it leads us to Aztec Mythology of Mexican-American culture which supported polytheism. Antonio had to meet many different kinds of myth all through the novel and each had a dominant influence in his character formation. The myth of the golden carp brings new perspectives to Antonio when he identifies it as different from Catholicism. The myth of golden carp was takes substance from the Aztec legend according to which, â€Å"there were four ages of the world or â€Å"suns† before the present world, each of which was destroyed by an individual

Gross Domestic Product, its importance, calculation and other basics Essay Example for Free

Gross Domestic Product, its importance, calculation and other basics Essay Gross domestic product is a term used in macroeconomics to measure the total of finished goods and services produced in a country during a period usually a year. Those things which are produced in the country are counted in GDP. Things like remittance and other things which are earned from other countries are not taken into consideration while calculating GDP. It is the most important indicator which tells about the economy of a country. It incorporates several other indicators as well like retail sales, personal consumptions, etc. II. Body A. Four parts that make up Gross Domestic Product The main components of GDP are consumption, investment accounts, spending and net exports. GDP can be calculated in three different approaches, product approach, expenditure approach and income approach. Product approach is considered to be the most direct approach in which all outputs are summed up. While the expenditure approach follows this equation: GDP = C+I+S+NE. The assumption made in this equation is that all organizations produce things or services which can be consumed by the users and is a source of investment for the organization. This equation also implies that the organization follow the supply and demand trends in the market. The income approach implies the principle that the income of the producers must be equal to that of their products. †¢ Consumption Consumption is the purchase of goods or services by the consumers. Consumption can be of three types, durable goods, non durable goods and services. Durable goods are those good which last for a long time. They are also considered as consumer investments even. Those goods which come under the head of durable goods are automobiles, refrigerator, etc. These types of goods are bought with the intention of retaining them for a long time thus are known as durable goods. Non durable goods are those goods which have a comparatively short life time than that of durable goods. They could be newspapers, grocery, etc. Services are intangible things. Things which can be classified as a service are medical treatment, teaching, etc. †¢ Investment accounts Investment is the purchase of purchase of things which are used in the production. They can also be classified into three group, business investment, residential construction and inventories. Anything that helps in the process of production comes under business investment. For example, machinery, office, plant, etc. It is the gross amount of investment that counts. Basically it subtracts the depreciation value from the value of the asset. Those assets which are replaced with the new ones, if they don’t produce any improvement in the outputs then they contribute nothing in addition to the country’s economy. Residential construction relates to the building of new houses in a period (year). Those houses which are already been constructed and are held for resale have already contributed in the GDP thus they won’t be included again. Inventories are stocked in anticipation of future sales. Changes in inventories contribute or affect the economy of a country. They are considered to be a small part that contributes to the GDP but changes in them can have great changes in the economy. For example when the inventory level increases the desired level then there may be a slowdown and producers might reduce their outputs. †¢ Government spending The government spending relates to all the items the government spends on with exception of interest paid on the debts and government transfers. Government spending mostly includes those items which are rarely sold in the market like space shuttles, aircrafts, etc. These items bear a large price that is why government pays for them (Kaplan). †¢ Net exports A net export is the difference between the total exports and imports of a country. When the exports exceed the imports, it is known as surplus export. While export deficit occurs when the imports increase from the export and when both export and import are equal it is a trade balance (Barnaby). B. Cross-border comparison As different countries have different currencies it is difficult to compare the GDPs in the respective countries currencies. For example comparing GDP of US in dollars with the GDP of India in Rupees would give a false reflection and therefore in order to have a correct comparison they are converted into national currency through current exchange rate or by purchasing power parity. †¢ Current currency exchange rates Current exchange rates are the international rates of the currency. It gives a better indication of the country’s international purchasing power and its growth. †¢ Purchasing power parity exchange rates Purchasing power parity exchange rates are those in which currency is purchasing power parity compared with that of a standard one which is usually US dollars. Non traded goods usually make use of this method rather than current currency exchange rate. It relates to prices of particular goods in the country and abroad. Therefore it can be misleading while considering the comparison of GDPs of countries due to different inflation rates, depreciation rate, etc. Mostly those countries which are less developed make use of this method to compare their GDPs. Therefore it differentiates between the high and low income countries and doesn’t forms a just comparison. C. Standards of living and GDP Standard of living can be calculated through a per capita GDP approach. There are advantages and disadvantages of calculating standard of living this way. As most of the countries on quarterly basis provide information to the authorities for calculating GDP, trends can be spotted through them on a regular basis. Most of the indicators used in GDP are widely used by other countries even therefore comparison becomes easy. The calculation of GDP is done on yearly basis that means it gives a consistent way. GDP per capita is not a very good way of calculating standard of living as it varies due to several reasons which GDP per capita might not take into account. For example a country with high exports and almost no imports would have a high GDP but a poor standard of living. Therefore GDP per capita should not be considered as the main indicator of standard of living, but just a way to it. As the standard of living increase, GDP per capita also increases. III. Conclusion To assess the effectiveness of a country’s economy GDP is widely used. But using GDP to calculate the standard of living proved a limited result. GDP does not take the wealth distribution into account which might mislead while judging the economy of a country. It doesn’t account for the inequality of the wealth. All those activities which do not occur through a market are excluded by GDP. All those activities which are free or as a volunteer are counted amongst those activities. Not counting these activities would be an understatement in the GDP. Even if the services are provided for free but there must have been a cost to provide the services. Therefore if they don’t contribute toward the GDP most of the organization would move towards free services rather than providing them on money. Another form of understatement of GDP is when those transactions which are illegal or tax avoiding activities are not taken into account. Barter system is also ignored in the calculation of GDP. Barter system is a very common system followed nowadays even through which people might exchange goods or services without any dealing of money. The improvement in products and quality are even those amongst the ignored items in GDP which does not reflect the real economic growth of a country. Computers have become more advanced but less expensive GDP will treat them as the old computers used in the past, rather than considering its worth. GDP rakes into account few things which should not be taken like the cost of rebuilding after an earthquake which might boost the GDP but would provide an unrealistic way to judge the country’s economic growth. Only those things which are economically ‘good’ are reflected in the calculation of GDP while the bad ones are excluded. All those negative effects to the environment which might be due to the production are ignored which is a bias way. Some of the things are sometimes included in GDP like cleaning up of oil spills and etc. GDP does not project the economy of a country but it just measures the economic activity. Therefore it cannot calculate the sustainable growth of a country. There are several ways a country can achieve a high GDP for a time being, for example by excessive use of natural resources, etc. But it can be very costly to pay back after if the natural resources are used badly (mistreated). As value of money changes with time comparing or determining the growth in different sorts of goods can be a difficult task to perform. While comparison of a country’s economy is done by other countries they can give inaccurate results as they might not take the local differences like change in quality, content, etc not into account which might not be a just form of judgment. There are many other limitations of using GDP to judge the economy of a country (Jackson,p63). Although GDP is a way to measure the market value of a country’s finished goods and services it should not be the key indicator to provide information about a country’s economy. It gives a rather flawed and biased way to compare things domestically as well as internationally. A country’s economy should be judged on its ability to provide the people of the country with what they need and what their basic necessities are, some of the basic necessities might include food, shelter, clothing, better place to live in, etc. Therefore things which are not included in the judging the standard of living should be considered. With a combination of indicators which can judge the conditions of the country environmentally as well as in terms of living and financial ways should be used as a way to judge the effectiveness of a country should be taken into consideration rather than just the use of GDP. Word Cited Page Barnaby, Meins. How the GDP is calculated and what it does not count. 2010, 5 May 2010, http://www. helium. com/items/1284362-the-gdp-how-the-gdp-is-calculated-and-what-it-does-not-count Jackson, Tim. Prosperity without Growth: Economics for a Finite Planet, Earthscan Publications Ltd. 1 edition, 2009 Kaplan, Jay, Components of GDP. 1999, 5 May 2010, http://www. colorado. edu/Economics/courses/econ2020/se

Mirror Dance :: essays research papers

Mirror Dance There are some paintings that simply capture the essence of life within their still frames such as the painting of the "Mirror Dance" in R.A. Salvatore’s novel Crystal Shard. The painting depicts two characters set in a darkened background. The faint light of the moon casts shadows down upon the grassy floor on which the sylvan warrior and human assassin battle. The glimmer of the moon reflects upon a small, nearby pool of water. A silver sparkle in the distance marks the nearby city of Silvery Moon. A sneer of hatred is etched upon the face of the human assassin. His eyes glimmer with a taint of red to depict his blazing internal rage. The clothing worn by the human is black as the night, much like the hooded garbs of ancient Japanese Ninja, the only hint of color coming from his weapons. One of his hands holds a vicious blade, blackened like the coal inside a fireplace. Small flecks of crimson blood decorate the tip of the blade, matching the fresh cut upon the arm of the elf. The legs of the human are crouched, as if he were ready any moment to leap savagely at his opponent. His secondary hand hosts a second blade, much smaller than the other sword, his hand holds the secondary blade inward, as if to flick it out at his adversary. The elven warrior casts an extremely different perspective upon the viewer. His eyes twinkle with the soft moonlight, and his smile welcomes the fierce battle. The warrior’s robes flutter in a soft breeze, shining in the glow of the night. Even with his arm bleeding red from a cut which must have been inflicted by the assassin, the warrior still maintains a look of regality. The crown adorning the top of his head, marks his royal heritage. The weapons commanded by the warrior seem to take on a life of their own, his sword dancing to meet the twin blades of the assassin while a radiance resonating from his shield, cast light upon the foe who prefers the stealth of night. Nature lies still for the battle between the two adversaries. The birds in flight, bend away from the loud clashing of swords, and the deer hide amongst the trees in the forest. The people of the distant town of Silvery Moon watch from their doorways, huddled close to keep the chill of the night from freezing their bones. They look upon the scene with deep interest, the smiles of the children obviously cast upon their elven hero.

Milpa Agriculture vs. Industrial Agriculture

â€Å"Milpa Agriculture vs. Industrial Agriculture† The Milpa agriculture and Industrial agriculture have many similarities and differences. Milpa agriculture is a form of swidden agriculture that is practiced in Mesoamerica. Traditional Milpa is planted with maize, beans, and corn. Industrial agriculture is a modern faming that produces a life stock, poultry, and crops. The methods that industrial agriculture use to techno scientific, economic, and political. In Milpa agriculture some farmers use a coa stick in order to plan their crops and industrial farming the farmers use different machines. Industrial agriculture makes their job easier and faster by using the machines and technology. In Milpa agriculture is the totally opposite thing they don’t use technology in order to grow their crops it takes them longer to plant their crops by using simple method and one of the methods is the coa stick. Milpa agriculture has more than one plant such as maize, beans, and squash. Industrial agriculture only focuses on one plant. For example if industrial agriculture wants to grow maize they focus only in that specific plant that is being planted. Milpa is traditional in Mesoamerica. What I mean by this is that when milpa is planted in Mesoamerica is passed down in the family generations. Mesoamericans try to keep their tradition of planting milpa. In industrial agriculture is not really traditional to pass it down into their families mostly it is done because of the money. Industrial agriculture uses lots of pesticides in order to keep their crops from danger. By using pesticides they won’t lose lots of their crops. Milpa agriculture doesn’t really rely on the use of pesticides. Milpa agriculture does have the advantage of losing crops because they don’t use pesticides. That’s the reason in milpa agriculture more than one crop is incorporated at the same time they have the other crops to rely on not just on the maize. If industrial agriculture loses all their crops they won’t have anything to rely on because they only focus on growing on type of crops.

Aerofoil Design Xflr5

Aashiq Zakir Hussain12108227 | Supervisor : | Dr. Patrick Frawley | Submission : Date | 26th October 2012 | ABSTRACT Airfoil is the main part of the airplane which contributes the lift required by the airplane to fly in the air. By varying the wing’s area and the angle of attack, different lift can be created and can be used to fly the airplane. This program named XFLR5 is used for determining the airfoil characteristics.It will help them to save a lot of time on computing the equations and on the trial and error method. The program can also be used as basic tool to show the users what will happen when some variables like Reynolds number, the AOA of the wings and the speed of the aircraft are changed and how it will affect the results and lift generated. This project report deals with the analysis of widely used airfoils in the modern aircrafts. In this analysis, the lift, drag, pressure profiles and their coefficients of the airfoils are been calculated using xflr5 program.Th ese are obtained in the form of graphical representation by feeding data such as Reynolds number, Mach number, Angle of Attack and dimensions of the airfoils to the program. The results such as maximum lift coefficient, stalling angle, maximum lift to drag ratio and such parameters are obtained and are been compared with each other.Re| Reynolds number| -| ?| Angle of Attack| -| M| Mach number| -| Cp | Pressure Coefficient| -| Cl| Lift Coefficient| -| Cd| Drag Coefficient| -| Cl / Cd| Glide Ratio| -| T| Thickness| mm| c| Chord| -| INTRODUCTION Airfoils are the primary shapes which allow streamlined flow over it when it is driven through air. These shapes do not produce much drag compared to other shapes as so it is used in all aircraft structural parts which is subjected to airflow. Basically airfoils can be divided into many types by slightly varying their thickness, length, camber area and so on without after the shape.In this analysis we deal with airfoil shapes known as NACA airf oils. The  NACA airfoils  are just  shapes of airfoils used for aircraft wings, which is developed by the  National Advisory Committee for Aeronautics  (NACA). The shape of the NACA airfoils is determined using a  series  of digits followed by the word â€Å"NACA. † The series is divided using digits from 1-8. We only deal with the 4-digit series of airfoils in this analysis. The 4 digit airfoils we are going to discuss in this analysis are 0004, 0008, 0012, 0016, 0020, 0312, 1312, 2312, 3312, 2112, 2512 and 2712.In this 4 digit series, 1st digit denotes the maximum  camber  as percentage of the  chord, 2nd digit denotes the distance of maximum camber from the airfoil leading edge in tens of percent's of the chord and this last 3rd and 4th digits denotes  maximum thickness of the airfoil as percent of the chord. The key features we are going to discuss about in this analysis are the effects of Angle of Attack, Reynolds number, Mach number, Camber and Thi ckness. The basic aerodynamic design is to obtain maximum lift and minimum drag which will be expressed in terms of coefficient of lift (Cl) and coefficient of drag (Cd).Using this program known as XFLR5, we are going to compare the characteristics of all the airfoils. As the operating valves such as Angle of Attack, Mach number, Reynolds number are to be fed in to the program and this will give us the required graph of the parameters such as Cl, Cd, alpha, Cp and so on. Using these results achieved from the program, it will be easier to find out the airfoil with highest Cl at various angles of attack, which has got highest stalling angle and the airfoil with best glide ratio and so on. OBJECTIVESThis report is basically done to find out airfoils with maximum lift to drag ratio by comparing many airfoils each other and allowing their camber area, thickness and the location of the camber to deviate to the small percentage of the chord. By doing this, we can achieve a best airfoil des ign that can be used in live aircrafts. LITERATURE REVIEW Introduction: * If an aircraft has to fly, force has to be counter balanced by the weight as it must be opposite to its magnitude. This force is known as lift. Lift plays a major factor on the airplane flight.The main plane (wings) generates more lift as it is the important load carrying member. * The aerofoil sections have been started to get developed in late 1800’s. In 1884 H. F. Phillips with the help of wind tunnel, tested and made series of airfoils. At the same time Otto Lilienthal with the help of the bird’s wings, designed airfoil shapes. It was found that the key factor is that the wing curvature or camber. The early airplanes were biplanes because, the airfoils were thin and cambered as shown in figure 2. 1. Figure 2. 1: Hanson http://www. biplanefun. om/assets/Image/Hanson_215217_001. jpg Nowadays these types of aircrafts are not used, as all airfoils are made by trial and error method. Airfoils used in 1920’s (NACA). ( http://www. desktop. aero/appliedaero/airfoils1/images/sections1. gif) Figure 2. 2: Ancient development in airfoils For the project, the NACA 4 digit airfoil format will be use for the program which is generating the airfoil’s shape and the thin airfoil theory will be use for computing the important parameters of the wing. * 1. ii Terminology for Airfoil and Airplane:Basic parts of an airfoil that must be known before getting in to the chapter of NACA 4 digit series. The diagram below describes the parts of an airfoil from which series are determined. Figure 2. 3: Airfoil Terminology airfoil (http://www. copters. com/aero/pictures/Fig_2-10. gif) Figure 2. 5: Plane Axes (http://www. allstar. fiu. edu/aero/images/fig25. gif) 1. iii Definitions: The line drawn midway between the upper and lower surfaces of the airfoil is known as mean camber.The straight line joining the leading and trailing edges of the airfoil is known as chord. Leading edge is the front of the airfoil. Trailing edge is the end of the airfoil. The angle between the chord and the line representing the relative airflow is known as the angle of attack (AOA). Camber of an airfoil is the upper and lower surfaces curvature. The airfoil’s thickness and amount of lift the airfoil will generate is determined by the cambered area. When the term upper camber is used, it is referring to the upper surface of the airfoil. When the term lower camber is used, it is referring to the lower surface of the airfoil.Span is the distance from a tip of the wing to the other tip of the wing. * 1. iv The Four Forces on the Airplane Figure 2. 6: Forces on an airplane (http://anjungsainssmkss. files. wordpress. com/2011/09/plane_forces. jpg) * The four main forces that maintain the aircraft in steady flight and helps fly are Lift, Drag, Weight and Thrust. Thrust is a forward pulling which is generated by the engine(powerplant). Thrust opposes the drag. Thrust depends upon the powe r of the engine as high power engines produce more thrust and the type of the engines with respect to their mounted location.Drag is a force which opposes the thrust as when the aircraft moves in high speed the air passes over and below the surface produce drag. It is a resistive force. The weight is a force of an airplane which is acting downwards due to the force of gravity. This force pulls down on the plane and opposes the lift force. This force mainly depends upon the weight of the aircraft and so it depends upon how much we load and the total weight we use to build the aircraft. Lift is an important force in the aircraft which tends the aircraft to fly.It is generated as aircraft moves at high speed and is generated below the airfoil surface of the main plane. At this time, there will be low pressure acting over the wing and high pressure under the wing. The four forces act on any airplanes in flight and are interconnected. In order for the airplane to take off, lift must over come weight and thrust must overcome drag. During landing, thrust must be reduced below the level of drag and lift must be reduced below the weight of the airplane. * * * 1. v Theory of Lift: * Lift is an important force as it sustains an airplane in ir and enables it to manoeuvre. The theory of lift has been debated for a long time and currently still debating. However this project is not about debating the theory of lift but to design the airfoil. Therefore to cover the theory of lift, the 2 more popular explanations which are the Newton’s Law and the Bernoulli’s Principle will be discuss briefly. * Principles of Physics such as the principle of conservation of momentum, the principle of the conservation of mass and the principle of the conservation of energy are the basic principles to be known and to be considered to understand lift force.The principle of the conservation of momentum is covered by Newton’s Law. And the principle of the conservation of energy is covered Bernoulli Principles. Both can be use to explain the basics principles on how lift is form and are compatible with each other. In the following explanations, air is assumed as an ideal fluid and therefore 3 major assumptions about the physical properties of the airflow are made: * The airflow over a wing is incompressible. The airflow is inviscid which means the viscosity of air is approaching zero. The airflow around the wing is steady. * * * 1. vi Newton’s Law Explanation: Lift is generated by a wing as it moves through the air at an angle of attack. This will turn the airflow downward and the wing itself will have the force acting in an upward direction. In order to make use of the Newton’s Law, we need to know a theory known as the Coanda Effect. Coanda Effect stated â€Å"A moving stream of fluid in contact with a curved surface will tend to follow the curvature of the surface rather than continue travelling in a straight line. † This states tha t, when the air hits the wing when it is subjected through air, the angle changes the wing dimension as it is tilted to an extent.At this stage air do not reflect back as it stays over the wing. From Coanda Effect, we know that the wing is changing the direction of the airflow and also changing the velocity. Since lift is a force, according to Newton’s 2nd law of motion: * Force = mass x acceleration (F=ma) * Acceleration is a change in velocity with respect to time and force will be: * Force = mass x (change in velocity / change in time) * Therefore a change in velocity will generate a force and a force will cause a change in velocity.Velocity has both a magnitude called speed and a direction is associated with it. It is a vector quantity. Therefore by changing the direction of the airflow, the wing is also causing an increase in velocity which results in an acceleration. This change in velocity also generates a reaction force on the wing acting in an upwards direction. * Th is principle of Newton’s 3rd law which states â€Å"Every action has an equal and opposite reaction† helps to explain the nature of lift. The reaction force experienced by the wing is the total reaction. Figure 2. : Forces on an airfoil (http://www. free-online-private-pilot-ground-school. com/images/forces_airfoil. gif) * 1. vii Bernoulli’s Principle: Bernoulli’s Principle can be referred to as the law of conservation of energy and the total energy in a moving mass of fluid consists of potential energy, kinetic energy and the fluid’s pressure energy. It states that sum of all energies result in a constant value for the steady flow of an ideal fluid. Bernoulli’s Principle shows that as the velocity of a fluid flow changes, the pressure will change as well.This means that when the fluid’s velocity increases, the pressure will decrease and vice versa. Using this principle of pressure variation with velocity change, lift force developed by the wing can be accurately predicted in the same way as Newton’s Law. Figure 2. 8: Example of Bernoulli’s Principle (http://images. rcuniverse. com/magazine/reviews/455/bernoulli. jpg) Using Bernoulli’s Principle, the kinetic energy of the air will be highest where the pressure energy is the lowest and lowest where the pressure energy is the highest.This will result in an increase of the airflow for the upper surface of the wing and decreases for the lower surface of the wing. Therefore there will be a lower pressure on the upper surface of the wing and a higher pressure on the lower surface of the wing. This will result in a force acting in an upwards direction. Using equation: Force = Pressure x Area The lift force will be proportional to the pressure differential across the wing multiplied by the wing’s surface area. For Bernoulli’s Principle, it does not provide any explanation on why the airflow is faster on the top surface of the wing.The Newton’s Law also did not explain why the air deflects downward. Both theories only explain how lift is created. * 1. viiiThe Factors affecting Lift: Lift is the main source of force which enables the airplanes to fly. In order to generate enough lift, several factors have to be taken into consideration as they affect the amount of lift the airplane can generate. The general equation for lift is Lift = lift coefficient x {(air density x velocity2)/2} x wing area Where the lift coefficient is given by: Lift coefficient = 2 x pi x (AOA – calculated AOA at zero lift) Therefore the factors affecting lift are: The Angle of Attack (AOA). * The airfoil shape. * Airspeed. * Wing size. * Air density. The air density depends on the height which the airplane is flying. As the height of the airplane decreases, the air density will increase which will also result in higher lift generated. Therefore to generate the same amount of lift when the air density increases, the velocity of the airplane must increase. The Angle of Attack (AOA) of the airplane’s wing which is denoted by the Greek letter alpha ?. AOA is the angle between the oncoming air or relative wind and a reference line on the wing which in this case is the chord.It is one of the important parameters for handling and designing of a plane as a typical wing only has a limited range of angles of attack As the AOA increases, the lift generated by the airfoil is also increased. However, once the AOA reaches a certain angle known as the Critical Angle, the airplane will stall as the airflow will separate from the upper surface, resulting in a loss of lift which means the airplane will stall. This will result in cavitations and lose in lift force. It will also produce drag force as shown in figure 2. 9. Figure 2. 9: Diagram of how AOA affects the air flow (http://www. ero-mechanic. com/wp-content/uploads/2008/12/2-8-283Ãâ€"300. jpg) The lift depends upon the airfoil and the force the air flows over it. Thus when airflow is more, lift produced is maximum. Comparing a cambered airfoil and a symmetric airfoil, a cambered airfoil produced more lift than a symmetric airfoil. Even a flat plate subjected to the air will produce lift. Thus the airfoil should be designed in such a way that it produces high lift to drag ratio. * 1. ix NACA 4 series: In the 1930s, the National Advisory Committee for Aeronautics (NACA) developed several sets of airfoils and camber lines.The â€Å"Characteristics of 78 Related Airfoil Sections from Tests in the Variable Density Wind Tunnel† report was published by the NACA. In this report, the authors discovered that the airfoils that are successful had many similarities. The two primary variables that affected the airfoil shapes are the slope of the airfoil mean camber line and the thickness distribution above and below the line. Many of this airfoil shapes have been in use as tails and wings of airplanes over the years. The first family of airfoi ls designed using this approached is the NACA 4 series.In the NACA 4 series, the 1st digit indicates the maximum camber (m) in percentage of the chord, the 2nd digit indicates the position of the maximum camber (p) in tenths of cord and the last 2 digits provide the maximum thickness (t) of the airfoil in percentage of chord. For example, the NACA 2412 airfoil will have a maximum camber of 2% located at 40% from the leading edge with maximum thickness of 12% cord. 4-digit series airfoils by default have a maximum thickness of 30% of the chord from the leading edge. Therefore with the first 2 digits 00, it indicates that there is no camber and is a symmetrical airfoil.To find the mean camber line, it can be calculated using: To calculate for the thickness distribution, equation 2. 3 is used. Currently in the market, there are several NACA 4 series airfoil generators. These generators calculate the coordinates of the airfoil shape. However, it does not take into consideration of the l oad that the airfoil will be taking, meaning the surface area of the wings are not taking into consideration. There is also not much program which enables the user to calculate the whole wing surface area and the lift generated by the wing with different airfoil design. 1. x Thin Airfoil Theory: For this project, the Thin Airfoil Theory will be use to compute the model airplane’s airfoil thickness and wing dimension as the thickness for the model airplane’s wing is not very thick. Thin airfoil theory was devised by German mathematician Max Munk and further refined by British aerodynamicist Hermann Glauert and others in 1920s. It is a simple theory of airfoils that relates the angle of attack to lift. The theory idealizes the flow around an airfoil as a 2 dimensional flow around a thin airfoil.At low angles of incidence, the boundary layer growth on an airfoil is thin and remains attached to the airfoil. Therefore the airflow is assumed to be inviscid and irrotational. Since the thickness of any lifting airfoil is less than a fifth of its chord length, the effect of the airfoil’s thickness can be neglected and the airfoil will be represented by its mean camber line. A mathematically conceived function in the form of a vortex sheet is then placed along the length of the camber line to simulate the airfoil. This essentially makes it a streamline of the flow.By applying the circulation theory of lift to this streamline, the aerodynamic properties of the airfoils are obtained. The airfoil is considered as having zero thickness and infinite wingspan. This the reason why the theory does not take into consideration the induced drag that arises from the wing tips of an airfoil. Therefore it is only good for approximating an airfoil with medium and large aspect ratio and only up to the stall angle which is usually 10 to 15 degree for typical airplane configuration. Any angle beyond 15 degree, the thin airfoil theory cannot be used to calculate the c oefficient of lift.Thin airfoil theory is important as it provided a theoretical basis for the important properties of the airfoils in 2 dimensional flows: * The centre of pressure lies exactly ? of the chord behind the leading edge on a symmetric airfoil. * The aerodynamic centre lies exactly ? of the chord behind the leading edge for cambered airfoil. * The slope of the lift coefficient versus angle of attack line is 2? units per radian. There are many formulae that states the derivation of the thon airfoil theory, but we don’t require those for our project and so its neglected. xi Flat Plate Airfoil Theory:Flat plate theory is applied to airfoils as the thickness is also the constituent of drag in the airfoil. The flat plate when it is subjected to airflow the drag minimum as compared to the other shapes with reasonable thickness. Thickness cannot be neglected as it also plays a vital role in the camber surface as it produces lift. The transition point can be pushed back a s we reduce the drag in an airfoil by which we can get a good lift curve for higher degrees. In case of boundary layer, the drag in a flat plate will be laminar for a certain period of time and it then become turbulent.There is no unique valve where the stream gets turbulent, but by keeping the laminar surface clean and free stream, one can delay the renolds number. Figure 2. 10: Velocity profiles for laminar and turbulent boundary layer EXPERIMENTAL PROCEDURE AND ANALYSIS Introduction: These experiments below are done using xflr5 program. NACA 4 digit series airfoils are been used in the analysis. In the final analysis, NACA airfoils ranging from 0 to 9% of camber magnitude, 10 to 70% of camber location and 3% to 30% of thickness airfoils are analysed to get an airfoil of better performance with high to lift to drag ratio.Exercise A: Effect of Angle of Attack Airfoil = NACA 0012 Re number = 1000000 M = 0. 00 Part 1: In this part, the pressure profiles for different angle of attack are to be discussed. AOA( Alpha ) : -4 to 16 degrees with a step of 4 degrees Figure 3. 1: Pressure profiles plot of NACA 0012 Angle of attack(alpha)| Cl| Cd| -4| -0. 429| 0. 007| 0| -0. 00| 0. 005| 4| 0. 429| 0. 007| 8| 0. 910| 0. 012| 12| 1. 242| 0. 020| 16| 1. 301| 0. 050| Part 2: In this part we discuss about the lift, drag and their coefficients. Angle of Attack (alpha) = -4 to 18 degrees with a step of 0. degrees Figure 3. 2: Drag coefficient and Angle of attack plot Figure 3. 3: Lift coefficient and Angle of attack plot Figure 3. 4: Glide ratio and Angle of attack plot Figure 3. 5: Lift coefficient and Drag coefficient plot Analysis: Part 1: In this part, the angle of attack is changed from -4 degrees to 16 degrees with fixed Reynolds number and Mach number. The pressure profiles seem to have gradual increase in both negative and positive values on Cp. As the angle of attack increases, the lift and drag increases to a certain limit and stalls.Maximum lift is at 14 degrees and thus stall occurs. Cl max is 1. 36. It is consistent as Bernoulli’s approach on analysis. Part 2: In this part, the angle of attack is varied from -4 degrees to 18 degrees. Re and M is same as above. The lift curve passes through the origin, so zero lift is at origin (0 degrees). Max Cl is at 1. 36 where the stall angle is at 4 degrees. The maximum glide ratio is 75. 86 and at this point the values of Cl is 0. 8685, value of Cd is 0. 0115 and the value of alpha is 7. 5 degrees. Exercise B: Effect of Reynolds number Airfoil = NACA 0012 Alpha (AOA) = 4 degrees M = 0. 00Part 1: In this part, we discuss about the effects due to change in Reynolds number in NACA 0012 airfoil. Re number = 100000 to 2. 1 million with an increment of 400000 Figure 3. 6: Pressure profiles plot Part 2: In this part, we discuss about the effects due to change in Reynolds number and Angle of attack in NACA 0012 airfoil. Re number = 100000, 500000, 900000, 2100000, 4000000. AOA (alpha) = -4 to 20 degrees with a step of 0. 5 degrees. Figure 3. 7: Glide ratio and alpha plot Figure 3. 8: Drag coefficient and alpha plot Figure 3. 9: Lift coefficient and alpha plot Figure 3. 10: Lift and Drag polarRe number| Max Cl| Stall angle(degrees)| Max Cl/Cd| Cl at Max Cl/Cd| Cd at Max Cl/Cd| Alpha at Max Cl/Cd| 100000| 0. 97| 10. 5| 36. 5| 0. 61| 0. 017| 5 degrees| 500000| 1. 21| 13. 5| 61. 9| 0. 72| 0. 012| 6 degrees| 900000| 1. 35| 14. 5| 73. 6| 0. 86| 0. 011| 7. 5 degrees| 2100000| 1. 57| 17| 92. 5| 0. 97| 0. 0105| 8. 5 degrees| 4000000| 1. 67| 18. 5| 107. 3| 1. 073| 0. 010| 9. 5 degrees| Analysis: Part 1: In this case there is an increase in the pressure values as increase in Re number and the transition is point is pushed backwards in the curve with Reynolds number 4000000 than the curves with Reynolds number less than that.Part 2: In this case, the transition point is brought backwards as there is an increase in the boundary layer. It just pushes the stall angle further towards the leading edge. For Re= 100000, drag is increased more at high angle of attack. For high Re number, lift coefficient is more than low Re number and the drag is minimised at high angle of attack in high Re number curves. Exercise C: Effect of Mach number Airfoil = NACA 0012 Re number = 2 million Part 1: In this part, we are discussing about the effects in forces due to change in Mach number. Alpha (AOA) = 4 degrees M = 0. 00, 0. 1, 0. 02, 0. 03 Figure 3. 11: Pressure plot of M=0. 00 Figure 3. 12: Pressure plot of M=0. 01 Figure 3. 13: Pressure plot of M=0. 2 Figure 3. 14: Pressure plot of M=0. 3 Part 2: In this part, we are going to see the difference in the curves for different Mach numbers mentioned in part 1 and also with Angle of attacks from -4 to 30 degrees with a step of 0. 5 degrees. Figure 3. 15: Lift coefficient and Alpha Figure 3. 16: Drag coefficient and Alpha Figure 3. 17: Glide ratio and Alpha Figure 3. 8: Lift and Drag polar M| Cl Max| Stall angle(degrees)| Cl/Cd Max| Cl at Cl/C d Max| Cd at Cl/Cd Max| Alpha at Cl/Cd Max| 0. 0| 1. 560| 17| 91. 5| 0. 975| 0. 0104| 8. 5 degrees| 0. 1| 1. 540| 16. 5| 91. 25| 0. 985| 0. 0105| 8. 5 degrees| 0. 2| 1. 475| 15. 5| 90. 3| 1. 00| 0. 0115| 8. 5 degrees| 0. 3| 1. 355| 73| 88. 4| 0. 97| 0. 0110| 8 degrees| Analysis: Part 1: In this analysis, there is a change in pressure (Cp). As the Mach number increases, the value of Cp increases in the negative values. Due to the increase in speed, the transition point in moved towards the leading edge and stall angle decreases.Part 2: In this part, the angle of attack is also changed with the Mach number. We can see the effect of lift and drag from the values in the table given above in part 2. At the highest AOA the Cl value is increased. As the Mach number increases, the value of Cl max and the stalling angle drops down as it tends to stall soon in high ach number. Exercise D: Effect of Thickness In this exercise, various airfoils of different thickness are used. The values are ta ken from the program and compared with each other. Re = 2000000, M = 0. 00, AOA(alpha) = -4 to 20 degrees with a step of 0. Airfoils = NACA 0004, NACA 0008, NACA 0012, NACA 0016, NACA 0020 Figure 3. 19: Drag coefficient and Alpha plot Figure 3. 20: Glide ratio and Alpha plotFigure 3. 21: Lift coefficients and Drag coefficient plot Figure 3. 22: Lift coefficient and Alpha plot NACA airfoils| Max Cl| Stalling angle(degrees)| Max Cl/Cd| Cl at Max Cl/Cd| Cd at Max Cl/Cd| Alpha at Max Cl/Cd| 0004| 0. 96| 20| 48. 1| 0. 325| 0. 007| 3 degrees| 0008| 1. 15| 11. 5| 79. 85| 0. 775| 0. 010| 7 degrees| 0012| 1. 563| 17| 91. 52| 0. 977| 0. 010| 8. 5 degrees| 0016| 1. 578| 18| 93. 10| 1. 228| 0. 013| 11 degrees| 0020| 1. 45| 18. 5| 92. 4| 1. 000| 0. 010| 9. 5 degrees| Analysis: Due to the thickness, there is a change in lift as it can be observed in figure 3. 13. As NACA 0004 is thin, it stalls soon. But NACA 0020 and NACA 0016 airfoils has high value of Cl and this attains at almost 18 degrees o f AOA. From this it can be said that, if thickness increases the lift increases, but its for certain limit as Cl max drops in NACA 0020. The curves given above for each airfoil cannot be believed till end. This is only applicable theoretically that if an airfoil begins to stall, it can regain its lift after some angle further.In practical application, it is false. The curves can be believed till the first major stall occurs which attains Cl max. Exercise E: Effect of camber, magnitude In this exercise, the airfoils of different camber are been discussed i. e. the first digit of the NACA 4 digit series is been changed and compared. Re number = 2000000, M = 0. 00, AOA (alpha) = -4 to 20 degrees with a step of 0. 5 degrees Airfoils = NACA 0012, NACA 0312, NACA 1312, NACA 2312, NACA 3312 Figure 3. 23: Glide ratio and Alpha plot Figure 3. 23: Drag coefficient and Alpha plot Figure 3. 24: Lift coefficient and Alpha plot Figure 3. 5: Lift and Drag coefficients plot NACA Airfoils| Max Cl| S talling angle(degrees)| Max Cl/Cd| Cl at Max Cl/Cd| Cd atMax Cl/Cd| Alpha at Max Cl/Cd| Zero Lift| 0012| 1. 546| 17| 91. 5| 0. 955| 0. 0105| 8. 5degrees| 0 degree| 0312| 1. 546| 17| 91. 5| 0. 955| 0. 0105| 8. 5degrees| 0degree| 1312| 1. 610| 17| 98. 4| 0. 901| 0. 0094| 7 degrees| -1degree| 2312| 1. 664| 17| 122. 3| 0. 865| 0. 0071| 5. 5degrees| -2degree| 3312| 1. 712| 16. 5| 140. 5| 1. 008| 0. 0072| 6 degrees| -3degree| Analysis: As the magnitude of the camber is changed, the lift is attained way before than a normal airfoil with less camber surface.Symmetrical airfoil is that in which upper and lower surface are same and asymmetrical has various shapes in it. In these two types, the symmetrical airfoil produces less lift-drag ratio than asymmetrical airfoils. Due to the camber in the airfoil, in NACA 1312, NACA 2312 and NACA 3312 has started producing lift at negative angles as other two produces only after 0 degrees. Hence the lift is acquired soon and as angle increases, the drag produced is also less than in airfoils NACA 0012 and NACA 0312. Exercise F: Effect of camber, locationIn this exercise, we change the location of the camber and analyse their changes in curves. Re number = 2000000, M = 0. 00, AOA (alpha) = -4 to 20 with a step of 0. 5 degrees Airfoils = NACA 0012, NACA 2112, NACA 2312, NACA 2512, NACA 2712 Figure 3. 26: Drag coefficient and Alpha plot Figure 3. 27: Lift coefficient and Alpha plot Figure 3. 28: Glide ratio and Alpha plot Figure 3. 29: Lift coefficient and Drag coefficient plot NACA Airfoils| Max Cl| Stall angle(degrees)| Max CL/Cd| Cl at Max Cl/Cd| Cd at Max Cl/Cd| Alpha at MaxCL/Cd| Zero lift(degrees)| 0012| 1. 563| 17| 91. 5| 0. 55| 0. 0103| 8. 5degrees| 0| 2112| 1. 726| 17| 117. 0| 1. 145| 0. 0128| 12degrees| -1. 85| 2312| 1. 675| 17| 122. 3| 0. 865| 0. 0072| 5. 5degrees| -2. 02| 2512| 1. 694| 17| 111. 0| 0. 769| 0. 0068| 4. 5degrees| -2. 37| 2712| 1. 741| 17| 102. 5| 0. 962| 0. 0093| 6 degrees| -3. 056| Analysis: In this analysi s, the location of the camber is changed in each airfoil and hence so, we can find the change in Cl max and glide ratio which are key factors here. Fluctuation in the glide ratio can be seen, as it increases in NACA 2312 and decreases when going further increase in camber location.There are minor deflections in the stalling angle as that cannot be accurately calculated. Thus changing the camber location increases lift to some extend as further increase in camber value may cause drag. Exercise G: Finding the best values of a NACA airfoils In this section of analysis, we are using the airfoils of wide range with about 0-9%c camber magnitude, with 10-70%c of camber location and with 3-30% thickness range. We are yet to find the best airfoil with Cl max, largest stalling angle and Cl/Cd(Glide ratio). Re = 2000000, M = 0. 00, AOA(alpha) = -4 to 20 degrees with a step of 0. degrees. Graphs: Figure 3. 30: Lift coefficient and Alpha plot Figure 3. 31: Glide ratio and Alpha plot Figure 3. 32 : Glide ratio and Alpha(Re= 200000) Analysis: From the graph 3. 30, we can figure out the maximum Cl value is given by NACA 9318 of about 2. 3. And maximum Cl value when alpha(AOA) is 0 is given by NACA 9718 as per the figure. And hence the airfoil with largest stalling angle also can be seen, as it is NACA 9718. This airfoil though it has less Cl max, it stalls late compared to other airfoils. Its stall angle is going more than 20 degrees.

24 formas de sacar permiso de residencia green card

24 formas de sacar permiso de residencia green card Son muchas las formas para emigrar legalmente  a Estados Unidos y obtener el permiso de residencia permanente, tambià ©n conocida como la green card o tarjeta verde. Esta tarjeta de residencia autoriza a  vivir y trabajar en Estados Unidos sin là ­mite de tiempo e, incluso, da la opcià ³n de solicitar  convertirse en ciudadano americano por medio de la naturalizacià ³n. Los caminos para obtener la preciada green card  son muy variados. A continuacià ³n se describen las opciones de las que se dispone, pero hay que tener en cuenta que los trmites, los requisitos,  y los tiempos de demora de todo el proceso son muy diferentes. Se finaliza este artà ­culo con una explicacià ³n de dà ³nde pueden surgir los problemas que retrasan o hacen imposible sacar la green card. 1- Green card por matrimonio con ciudadano americano   El  matrimonio con un ciudadano americano es una de las formas ms comunes y rpidas de obtener la residencia permanente. Sin embargo, sà ³lo casarse no significa que se obtenga la residencia de forma automtica sino que el cà ³nyuge ciudadano debe solicitarla. Adems, la presentacià ³n de la peticià ³n  tampoco significa que siempre se pueda sacar. La residencia permanente por matrimonio es tanto en los casos de matrimonios heterosexuales como los formados por dos personas del mismo sexo. Aclarar que no se puede obtener la ciudadanà ­a americana por casarse con ciudadano, lo que se saca es la residencia y, al cabo de tres aà ±os de tiempo casado con un ciudadano, entonces el residente puede solicitar la naturalizacià ³n y, asà ­, hacerse ciudadano. Finalmente seà ±alar que los ciudadanos tienen a su alcance la opcià ³n de solicitar una  visa K-1 para traer a sus novios o prometidas  y, una vez en Estados Unidos, casarse y aplicar por un  ajuste de estatus  como paso para obtener la residencia.   2- Green card solicitada por ciudadano para hijos solterosmenores de 21 aà ±os Estos casos aplican a hijos biolà ³gicos o adoptados y tambià ©n a  hijastro de ciudadano americano, si bien, en este à ºltimo, caso aplican reglas especiales. Estas peticiones son rpidas, tomando generalmente menos de 1 aà ±o. 3-Green card para viudos de ciudadanos Los viudos de ciudadanos americanos pueden solicitar, en determinados casos, la green card para sà ­ mismos.   4- Green card para hijastrosde ciudadanos fallecidos Para beneficiarse los hijastros de ciudadanos fallecidos deben cumplir con varios requisitos, entre ellos, ser solteros y de 21 aà ±os.   5- Green card para padre o madre de ciudadano Los hijos de ciudadanos deben de tener 21 aà ±os cumplidos para poder solicitar la green card para cualquiera de sus padres.  El simplemente  ser padre o madre de un nià ±o ciudadano  no da derechos migratorios. 6- Green card para hijo de ciudadano que est soltero y es mayor de 21 Es lo que se conoce como un F1. Las demoras en estas tramitaciones est entre los 6 y los 20 aà ±os, dependiendo del caso,  y se pueden verificar en el boletà ­n de visas. 7-Green card para hijo casado de ciudadano, sin importar su edad Esta peticià ³n, tambià ©n llamada categorà ­a F3,  se demora por aà ±os, incluso dà ©cadas, siendo mayor la espera para el caso de los mexicanos que para el resto de Latinoamà ©rica y Espaà ±a.   8-Green card para hermanos de ciudadanos Esta tarjeta de residencia que se conoce como categorà ­a F4  se encuentra entre las que tienen una demora mayor. Sà ³lo los ciudadanos mayores de 21 aà ±os pueden pedir a sus hermanos. 9- Green card para cà ³nyuge de residente permanente Estas peticiones, que se conocen como categorà ­a F2A, son muy parecidas a las que pueden presentar los ciudadanos, sin embargo, su tramitacià ³n se diferencia en puntos importantes. Por ejemplo, se demoran ms las solicitudes de residentes. Otra diferencia importante es que los cà ³nyuges de residentes que estn como indocumentados en Estados Unidos en ningà ºn caso pueden ajustar su estatus, sin embargo, en el caso de los cà ³nyuges de ciudadanos, à ©stos pueden hacerlo siempre y cuando hubieran ingresado legalmente a EE.UU. En la prctica esta diferencia tiene importantes consecuencias legales ya que los indocumentados que no pueden ajustar su estatus y deben salir del paà ­s para ir a la entrevista consular se encuentran con que les aplica el castigo de los 3 o de los 10 aà ±os por presencia ilegal. 10- Green card para hijos solteros de residentes permanentes Estos son los tiempos de demora para este tipo de peticiones.  En este caso caben dos situaciones: para menores de 21 aà ±os, que se conoce como categorà ­a F2A, y para mayores de dicha edad, que son los F2B. En ningà ºn caso los residentes pueden pedir a sus hijos casados. 11- Green card por suerte por medio de la loterà ­a Al ganar una de las 50,000 visas de inmigrante que se sortean cada aà ±o fiscal en la  loterà ­a de la diversidad. Participar en este sorteo es gratuito y se abre la inscripcià ³n en el mes de octubre, permaneciendo abierta por un mes y producià ©ndose el sorteo al aà ±o siguiente en primavera. 12- Green card por inversià ³n que cree puestos de trabajo Invirtiendo un mà ­nimo de medio millà ³n de dà ³lares, mediante la visa EB-5. Se admite una inversià ³n directa creando una empresa o una indirecta, siendo posible  diversas modalidades. A diferencia de lo que ocurre en otros paà ­ses, en Estados Unidos la inversià ³n en una casa u otro bien raà ­z por sà ­ misma no es causa para obtener la tarjeta de residencia. Ya que es necesario que se trate de inversià ³n en un negocio. 13- Green card por autopatrocinio Peticià ³n para uno mismo sin necesidad de patrocinador de la tarjeta de residencia mediante una visa EB-1 en el caso de profesionales con una habilidad extraordinaria en Arte, Ciencias, Deporte, Educacià ³n o Negocios. Ejemplo: ganadores de premios Oscar, olimpiadas, premios Pulitzer o semejantes. Realmente el standard para cumplir con estos requisitos es muy alto. 14- Green card por trabajo en las categorà ­as EB 1, EB2 y EB3 En estos casos es necesario que una empresa o institucià ³n de los Estados Unidos patrocine ante las autoridades de inmigracià ³n al empleado extranjero. Mediante la visa EB-1 para profesores e investigadores de extraordinaria capacidad y gerentes o ejecutivos de multinacionales.Por la EB-2 para licenciados con al menos cinco aà ±os de experiencia laboral o con una habilidad excepcional en Arte, Negocios o Ciencias.Mediante la EB-3 para licenciados, trabajadores con formacià ³n profesional que requiere al menos dos aà ±os de estudios prcticos o de experiencia laboral y tambià ©n para trabajadores sin ningà ºn tipo de formacià ³n profesional pero que desarrollan una labor que no es temporal y para la que no hay trabajadores disponibles en Estados Unidos.   15- Green cardpor categorà ­a de inmigrantes especiales Mediante este camino instituciones y empresas estadounidenses pueden patrocinar mediante una EB-4 a las siguientes categorà ­as de trabajadores: Sacerdotes, monjas, ministros religiosos que lleven al menos dos aà ±os como tales.Periodistas, reporteros, escritores, traductores, productores y trabajadores semejantes que trabajen para el BBG (Radio Free Asia, Radio Liberty, etc).Mà ©dicos.Miembros de las Fuerzas Armadas de los Estados Unidos.Trabajadores de organizaciones internacionales.Traductores afganos e iraquà ­es.Iraquà ­es que han ayudado de alguna manera a los Estados Unidos.Empleados de la Zona del Canal de Panam.Trabajadores jubilados de la OTAN o, si han fallecido, sus viudos e hijos. 16- Green card para cubanos Obviamente, los cubanos pueden obtener la green card de todas las formas admitidas para otros nacionales, pero adems y por aplicacià ³n de la Ley de Ajuste Cubano, pueden solicitar la green card  despuà ©s de un aà ±o en Estados Unidos. Desde que se puso fin a la polà ­tica de pies secos, pies mojados es siendo imprescindible que el ingreso se hubiera realizado  de forma legal. En otras palabras, porque en el control migratorio se le permitià ³ el ingreso como admitido o recibià ³ un parole. 17- Green card para asilados Las personas que han ganado un caso de asilo pueden solicitar una tarjeta de residencia para sà ­ mismo y tambià ©n para su familia inmediata. 18-Green card para refugiados Las figuras de refugiado y de asilado son muy parecidas, pero hay importantes diferencias entre ellas. Los refugiados que solicitan la tarjeta de residencia para sà ­ mismos tambià ©n pueden solicitarla para familiares inmediatos. 19- Green card para và ­ctimas de violencia Se pueden beneficiar de esta opcià ³n las personas extranjeras và ­ctimas de violencia a las que previamente se les ha aprobado una visa U. En este punto hay que entender muy bien los requisitos de dicha visa, ya que da lugar a muchas confusiones.   El ser và ­ctima de violencia no da derecho, por ese mero hecho, a obtener la visa U. 20- Green card para và ­ctimas de violencia domà ©stica El programa VAWA abre el camino para la green card para los cà ³nyuges de ciudadanos o de residentes permanentes que han sufrido violencia domà ©stica. 21-Green card para và ­ctimas de trata de personas Para poder solicitar la tarjeta de residencia es necesario tener previamente aprobada la visa T. 22- Green card porradicar en Estados Unidos por mucho tiempo Por vivir de forma continuada en EEUU desde el uno de enero de 1972 o antes y poder demostrarlo. Es lo que se denomina residencia por el registry. En contra de lo que muchos migrantes creen, por vivir 10 aà ±os en Estados Unidos no se obtiene la green card. En algunos casos de migrantes con procedimientos de deportacià ³n abiertos, serà ­a posible obtener una cancelacià ³n de la deportacià ³n. 23-Green card por ser inmigrantes juveniles especiales: SIJ Los menores de 21 aà ±os que estn solteros a los que el gobierno de Estados Unidos ha colocado bajo la custodia de un guardin o de una institucià ³n pà ºblica o privada porque han sido abusados o abandonados por uno de sus padres o los dos. A este grupo de muchachos se les conoce como Inmigrantes Juveniles Especiales o SIJ, por sus siglas en inglà ©s. 24- Green card por orden judicial de un juez en Corte migratoria En un caso de deportacià ³n, un juez de inmigracià ³n puede sentenciar que el extranjero se puede quedar, ajustar su estatus y, asà ­, conseguir una tarjeta de residencia. Tiempos de demora en la tramitacià ³n de la green card Cada categorà ­a tiene sus propios tiempos. En la actualidad ms de un millà ³n de personas obtienen la green card cada aà ±o fiscal. Algunos han esperado solamente unos meses, mientras que otros han tenido que esperarse incluso ms de 25 aà ±os para que hubiera una visa de inmigrante disponible para ellos. Esto se debe a que en muchas categorà ­as existen là ­mites anuales al nà ºmero de peticiones que pueden ser aprobadas y el nà ºmero de solicitudes es superior al de visas disponibles, En estos casos se produce al demora que, cada aà ±o, aumenta ms. Cundo es posible no pagar por aplicacià ³n para la residencia En casos de residencia por circunstancias especiales (inmigrantes juveniles con este estatus reconocido, registry, visa T, visa U, etc) serà ­a posible calificar para estar exento de pagar la tarifa de este trmite migratorio para obtener la residencia. Causas por las que la tramitacià ³n no acaba bien A pesar de cumplir los requisitos para calificar para un camino para la obtencià ³n de la green card el proceso puede no completarse por diversas causas. Por ejemplo, en el caso de peticiones de familia porque no se tengan recursos suficientes para patrocinar. Pero los problemas suelen surgir porque la persona que aspira a la green card es considerada inadmisible para los Estados Unidos. Las causas pueden ser muy distintas, desde rà ©cord de delitos a estancia ilegal en el paà ­s. Dependiendo de las razones y de las circunstancias del caso, puede que sea posible solicitar un perdà ³n, tambià ©n conocido como waiver o permiso. Pero en otros casos ser imposible. Lo mejor es asesorarse con un buen abogado. Por su frecuencia, es muy importante saber cà ³mo puede afectar la presencia ilegal en Estados Unidos, actual o en el pasado y tambià ©n los fraudes migratorios. De interà ©s para potenciales migrantes Estados Unidos es un paà ­s diferente. En muchos casos, hay leyes, costumbres, impuestos, derechos, deberes, etc se desconocen.  Y como consecuencia de esa ignorancia, en ocasiones se acaban teniendo  problemas  muy serios aun cuando no se tenà ­a la intencià ³n. Por ello, no hay nada mejor que conocer las cosas bsicas que se deben conocer y las que se deben evitar.  Si es posible  se recomienda  informarse antes de emigrar.   Es tambià ©n importante saber que vez que una persona se convierte en residente tiene que esperar un tiempo antes de aplicar por la ciudadanà ­a por naturalizacià ³n. La espera depende de varios factores . Adems, es necesario tomar un examen de inglà ©s y de conocimientos cà ­vicos y de historia. Numerosas organizaciones en todo el paà ­s brindan clases gratuitas para preparar el examen para la ciudadanà ­a. Finalmente, si se est abierto a emigrar a un paà ­s que no sea Estados Unidos, estos son 20 paà ­ses en los que es posible comprar la ciudadanà ­a o/y la residencia. Las cantidades y las condiciones varà ­an entre los distintos programas. Test de respuestas mà ºltiples sobre la residencia permanente Se recomienda tomar este quiz o test de respuestas mà ºltiples, con sus respuestas correctas, para garantizar el conocimiento esencial sobre la green card. Este es un artà ­culo informativo. No es asesorà ­a legal.

Dos and Donts of Writing a Law School Resume

Dos and Donts of Writing a Law School Resume Some schools require that applicants submit a law school resume, but even if not requested, you should most likely send one anyway. Why? Because a resume can give you an added chance to show the admissions officers that you’re prepared to come into their school and make a difference. Indeed, this short summary of your professional and personal qualifications can end up being a very important component of your file, so you want to dedicate some time to putting forth the best law school resume you can. What follows are some tips for preparing your law school resume, namely what you should and shouldn’t do. What You Should and Shouldnt Do 1. DO set aside a couple hours to sit down and think about all the things you’d like to include on your law school resume. Start by asking yourself these questions for information-gathering purposes. 2. DO organize your resume using the sections Education, Honors Awards, Employment, and Skills Achievements.   3. DO emphasize activities, hobbies, interests, or experiences that demonstrate personal drive, responsibility, determination, dedication, language proficiency, compassion, extensive travel (especially international), cultural experiences, and community involvement. 4. DO proofread your resume several times and ask someone you trust to do so as well. 5. DO worry about presentation. For example, if you’re putting periods at the ends of bullet points, make sure you do so for each and every one. For more tips on what you should be looking for besides spelling and grammar errors, see the Law School Resume Style Guide. 6. DON’T simply use a work resume that you’ve been using and updating for years. You need to gear your resume to law school admissions officers, who are looking for different things than potential employers are. 7. DON’T include â€Å"Objective† or â€Å"Summary of Qualifications† sections. These are great in work resumes, but they serve absolutely no purpose in a law school resume and only take up valuable space. 8. DON’T include activities from high school unless they are extremely significant, like winning a national debate competition or performing at a very high athletic level. 9. DON’T include activities you only did for a short time or a long list of insignificant summer jobs. You can sum up such things in just a sentence or so if you really want to include them. 10. DON’T go longer than two pages. For most law school applicants, one page is plenty, but if you’ve been out of school for a considerable amount of time or have an unusual number of significant life experiences, a second page is fine. Very few people should go to that third page, though.