Airfoil & Wing Theory

Subtopic: Finite Wing Theory & Induced Drag

The fundamental purpose of the Kutta condition in the thin airfoil theory is ________.

Subtopic: High-Lift Devices & Flaps

Shown below are qualitative illustrations of the lift curve for an airfoil when two different control surfaces are in their respective retracted and deployed configurations. Which of the following is/are TRUE?

Subtopic: Finite Wing Theory & Induced Drag

An elliptic wing has a span of 6 m and a planform area of 6 m^2. When generating a lift coefficient of 0.6, the induced drag it incurs is ________ × 10-3 (rounded off to 1 decimal place).

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

An experimental study is planned to map out the low-Reynolds number incompressible steady two-dimensional aerodynamic characteristics of a promising novel airfoil. The operational parameters of the problem are the speed, density and viscosity of the freestream, the chord of the airfoil and its angle of attack. If the objective is to achieve this with the minimum number of test runs Nmin while taking 10 equally-spaced test values of each independent parameter of the problem in a suitable range, then Nmin is ________.

Subtopic: Finite Wing Theory & Induced Drag

What is/are the use(s) of the single horseshoe vortex model of finite wing aerodynamic theory?

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

For an airfoil section the pitching moment coefficient is determined about a reference point that is 0.3 times the chord behind the leading edge. It varies with the lift coefficient as shown in the table below. The distance of the aerodynamic center from the leading edge of the airfoil as a fraction of the chord is ________ (rounded off to one decimal place). cl 0.2 0.4 0.6 0.8 cm - 0.02 0 0.02 0.04

Subtopic: Finite Wing Theory & Induced Drag

Consider a finite wing of aspect ratio 10 with span effectiveness factor 0.95. Its airfoil section has a lift slope of 0.106 per degree and a zero-lift angle of attack of -1.5°. The lift coefficient of the wing at an angle of attack of 3.5° is ________ (rounded off to 2 decimal places).

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

Thin airfoil theory predicts the zero-lift angle of attack $\alpha$L=0 of NACA 2412 airfoil as -2.1°. The corresponding prediction of $\alpha$L=0 for NACA 5410 airfoil is ________ degrees (rounded off to 1 decimal place).

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

For a NACA 4415 airfoil, the location of maximum camber, as a fraction of the chord length from the leading edge, is ______.

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

A positively cambered airfoil is placed in a uniform flow (velocity, U∞) at its zero-lift angle of attack. M is the corresponding pitching moment. Which one of the following representations accurately describes this scenario?

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

Consider a pair of point vortices with clockwise circulation $\Gamma$ each. The distance between their centers is a, as shown in the figure. Assume two-dimensional, incompressible, inviscid flow. Which one of the following options is correct?

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

The lift per unit span for a spinning circular cylinder in a potential flow is 6 N/m. The free-stream velocity is 30 m/s, and the density of air is 1.225 kg/m^3. The circulation around the cylinder is ____ m^2/s (rounded off to two decimal places).

Subtopic: Finite Wing Theory & Induced Drag

A lifting surface has a spanwise circulation distribution of $\Gamma(\theta) = A \sin 3\theta$ (where $A \neq 0$) over its span $-\frac{b}{2} \le y \le \frac{b}{2}$, and $y = -\frac{b}{2} \cos \theta$ is the spanwise coordinate. Furthermore, the downwash varies along the span as $w(\theta) = V_\infty \left(\frac{3A \sin 3\theta}{\sin \theta}\right)$, where $V_\infty$ is the freestream velocity. Which one of the following options represents the total lift ($L$) and induced drag ($D_i$)?

Subtopic: Finite Wing Theory & Induced Drag

A rectangular wing of 1.2 m chord length and aspect ratio 5 is tested in a wind tunnel at an air speed of 60 m/s. The density and the dynamic viscosity of air are 1.3 kg/m3 and 1.8×10-5 kg/m-s, respectively. A second rectangular wing of the same span, but with an aspect ratio of 6, is to be tested in the same tunnel at the same Reynolds number. The air speed at which the second test should be performed is _______ m/s (answer in integer).

Subtopic: Finite Wing Theory & Induced Drag

A jet-powered airplane is steadily climbing at a rate of 10 m/s. The air density is 0.8 kg/m^3, and the thrust force is aligned with the flight path. Using the information provided in the table below, the airplane's thrust to weight ratio is ______ (rounded off to one decimal place). Airplane speed 80 m/s Lift coefficient, CL 0.8 Aspect ratio 6 Oswald efficiency factor 0.8 Zero-lift drag coefficient 0.02

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

Consider steady, incompressible, inviscid flow past two airfoils shown in the figure. The coefficient of pressure at the trailing edge of the airfoil with finite angle, shown in figure (I), is CPI while that at the trailing edge of the airfoil with cusp, shown in figure (II), is CPII. Which one of the following options is TRUE?

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

Using thin airfoil theory, the lift coefficient of a NACA 0012 airfoil placed at 5 o angle of attack in a uniform flow is _____________ (rounded off to 2 decimal places).

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

The figure (not to scale) shows a control volume to estimate the forces on the airfoil with elliptic cross-section. Surfaces 2 and 3 are streamlines. Velocity profiles are measured at the upstream end (surface 1) and at the downstream end (surface 4) of the control volume. The drag coefficient for the airfoil is defined as Cd = D 1 2 $\rho$ U∞ 2 c , where D is the drag force on the airfoil per unit span and  is the density of the air. The static pressure, p , is constant over the entire surface of the control volume. Assuming the flow to be incompressible, two -dimensional and steady, the Cd for the airfoil is _________ (rounded off to 3 decimal places).

Subtopic: Finite Wing Theory & Induced Drag

An airplane of mass 1000 kg is in a steady level flight with a speed of 50 m/s. The wing has an elliptic planform with a span of 20 m and planform area 31.4 m^2. Assuming the density of air at that altitude to be 1 kg/m 3 and acceleration due to gravity to be 10 m/s^2, the induced drag on the wing is _________ N (rounded off to 1 decimal place).

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

A two-dimensional potential flow solution for flow past an airfoil has a streamline pattern as shown in the figure. Which of the following conditions is additionally required to satisfy the Kutta condition?

Subtopic: Finite Wing Theory & Induced Drag

An ideal glider has drag characteristics given by 0D D D i C C C=+ , where 2 DLi C KC= is the induced drag coefficient, LC is the lift coefficient, and K is a constant. For maximum range of the glider, the ratio 0DD i CC is

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

The figures shown in the options are schematics of airfoil shapes (not to scale). For a civilian transport aircraft designed for a cruise Mach number of 0.8, which among them is aerodynamically best suited as a wing section?

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

For studying wing vibrations, a wing of mass M and finite dimensions has been idealized by assuming it to be supported using a linear spring of equivalent stiffness k and a torsional spring of equivalent stiffness k as shown in the figure. The centre of gravity (CG) of the wing idealized as an airfoil is marked in the figure. The number of degree(s) of freedom for this idealized wing vibration model is _________. (Answer in integer)

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

For an airfoil, which of the relations given about the critical Mach number crM and drag divergence Mach number ddM is/are correct?

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

A thin cambered airfoil has lift coefficient 0lc = at an angle of attack o1.1 =- . Assuming that stall occurs at much larger  , the lc at o4 = is _______. (round off to two decimal places)

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

NACA 2412 airfoil has

Subtopic: Finite Wing Theory & Induced Drag

Consider a conventional subsonic fixed-wing airplane. $e$ is the Oswald efficiency factor and $AR$ is the aspect ratio. Corresponding to the minimum $\left( \frac{C_D}{C_L^{3/2}} \right)$, which of the following relations is true?

Subtopic: Finite Wing Theory & Induced Drag

Consider a circulation distribution over a finite wing given by the equation below: $\Gamma(y) = \begin{cases} \Gamma_0 \left(1 - \frac{2y}{b}\right) & \text{if } 0 \le y \le \frac{b}{2} \\[6pt] \Gamma_0 \left(1 + \frac{2y}{b}\right) & \text{if } -\frac{b}{2} \le y \le 0 \end{cases}$ The wingspan $b$ is $10\text{ m}$, the maximum circulation $\Gamma_0$ is $20\text{ m}^2/\text{s}$, density of air is $1.2\text{ kg/m}^3$ and the free stream speed is $80\text{ m/s}$. The lift over the wing is ______ $\text{N}$ (rounded off to the nearest integer).

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

Consider a thin symmetric airfoil at 2 degree angle of attack in a uniform flow at 50 m/s. The pitching moment coefficient about its leading edge is _____ (rounded off to three decimal places).

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

In an aerospace engineering analysis of Airfoil & Wing Theory (Thin Airfoil Theory & Camber Effects), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Subtopic: Finite Wing Theory & Induced Drag

In an aerospace engineering analysis of Airfoil & Wing Theory (Finite Wing Theory & Induced Drag), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Subtopic: High-Lift Devices & Flaps

In an aerospace engineering analysis of Airfoil & Wing Theory (High-Lift Devices & Flaps), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

A pair of infinitely long, counter-rotating line vortices of identical circulation strength $\Gamma$ are situated a distance $h$ apart in an inviscid fluid. The vortices will:

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

In an aerospace engineering analysis of Airfoil & Wing Theory (Thin Airfoil Theory & Camber Effects), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

The ratio of tangential velocities of a planet at the perihelion and the aphelion from the sun is 1.0339. Assuming that the planet's orbit around the sun is planar and elliptic, the value of the eccentricity of the orbit is _________ (round off to three decimal places).

Subtopic: Finite Wing Theory & Induced Drag

For a general aviation airplane with tail efficiency n = 0.95, horizontal tail volume ratio Vu = 0.453, downwash angle slope de = 0.35, wing lift curve slope C*a = 4.8 rad"', horizontal tail lift curve slope CLa= 4.4 rad"', shift in neutral point location as a percentage of mean aerodynamic chord is (round off to two decimal places).

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

The Mach number increases and the static temperature decreases. (C) The Mach number decreases and the static temperature increases. (D) Both the Mach number and the static temperature decrease. Q.7 For a NACA2415 airfoil of chord length c, which of the following is true?

Subtopic: Finite Wing Theory & Induced Drag

Which of the following statements about adverse yaw of an airplane is/are correct? P. It is caused by the difference in induced drag between the two wings when ailerons are deflected. Q. It causes the airplane to yaw in the direction of the roll. R. It can be counteracted using differential ailerons or Frise ailerons.

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

For a symmetric airfoil at an angle of attack of $10^\circ$, assuming thin airfoil theory, the magnitude of the section lift coefficient $C_l$ is _________ (round off to 2 decimal places).

Subtopic: Finite Wing Theory & Induced Drag

The span-wise distribution of circulation over a finite wing of span $b = 10$ m is given by $\Gamma(y) = \Gamma_0 \sqrt{1 - (2y/b)^2}$. If $\Gamma_0 = 20$ m$^2$/s and the freestream velocity is 50 m/s at an air density of 1.2 kg/m$^3$, the induced drag (in N) on the wing is _________ (round off to 1 decimal place).

Subtopic: Finite Wing Theory & Induced Drag

Consider an airplane with a weight of 8000 N, wing area of 16 m$^2$, wing zero-lift drag coefficient of $C_{D0} = 0.02$, Oswald efficiency factor $e = 0.8$, and wing aspect ratio $AR = 8$. At sea level with $\rho = 1.225$ kg/m$^3$, the maximum lift-to-drag ratio $(L/D)_{\max}$ divided by 10 is _________ (round off to 2 decimal places).

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

The pitching moment of a positively cambered NACA airfoil about its leading edge at zero- lift angle of attack is

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

An aircraft with mass of 400,000 kg cruises at 240 m/s at an altitude of 10 km. Its lift to drag ratio at cruise is 15. Assuming g as 9.81 m/s^2, the power (in MW) needed for it to cruise is _______ (accurate to two decimal places).

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

A pitot probe on an aircraft in a steady, level flight records a pressure of 55,000 N/m^2. The static pressure and density are 45,280 N/m2 and 0.6 kg/m^3, respectively. The wing area and the lift coefficient are 16 m2 and 2, respectively. The wing loading (in N/m^2) on this aircraft is _________ (accurate to one decimal place).

Subtopic: Finite Wing Theory & Induced Drag

An aircraft model was tested in a low speed wind-tunnel (Reynolds number based on mean chord $Re = 10^6$). The lift curve slope of the wing is $C_{L\alpha} = 4.5$ rad$^{-1}$. If the aspect ratio of the wing is 6 and Oswald efficiency factor is 0.9, the profile drag coefficient $C_{D0}$ is 0.015. At $C_L = 0.6$, the total drag coefficient $C_D$ of the wing is _________ (round off to 3 decimal places).

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

A conventional aircraft was analyzed to estimate the contribution of the vertical tail to the directional stability derivative $C_{n\beta}$. The vertical tail area is 2 m$^2$, moment arm is 5 m, wing area is 20 m$^2$, and wing span is 10 m. If the lift curve slope of the vertical tail is 4.0 rad$^{-1}$ and tail dynamic pressure ratio is 0.9, the contribution of the vertical tail $C_{n\beta, v}$ is _________ rad$^{-1}$ (round off to 2 decimal places).

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

The vector u is defined as y xeˆx eˆy u   , where xeˆ and yeˆ are the unit vectors along x and y directions, respectively. If the vector  is defined as u    , then      u ______.

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

The rate of change of moment coefficient with respect to the angle of attack, d dC m , at half chord point of a thin airfoil, as per approximations from the thin airfoil theory is

Subtopic: Finite Wing Theory & Induced Drag

An untwisted wing of elliptic planform and aspect ratio 6 consists of thin symmetric airfoil sections. The coefficient of lift (C L) at o10 angle of attack assuming inviscid incompressible flow is

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

An aerospace system operating under standard sea level conditions is governed by Airfoil & Wing Theory (Thin Airfoil Theory & Camber Effects). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Finite Wing Theory & Induced Drag

The value of definite integral    0 dx x sin x is _______.

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

A launch vehicle has a main rocket engine with two identical strap-on motors, all of which fire simultaneously during the operation. The main engine delivers a thrust of 6300 kN with a specific impulse of 428 s. Each strap-on motor delivers a thrust of 12000 kN with specific impulse of 292 s. The acceleration due to gravity is 9.81 m/s^2. The effective (combined) specific impulse of the vehicle is _______ s.

Subtopic: Finite Wing Theory & Induced Drag

For constant free stream velocity and density, a change in lift for a large aspect ratio straight wing, with thin cambered airfoil section at small angles of attack, leads to

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

As a candidate for a vertical tail, which one of the following airfoil sections is appropriate?

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

An aerospace system operating under standard sea level conditions is governed by Airfoil & Wing Theory (Thin Airfoil Theory & Camber Effects). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Finite Wing Theory & Induced Drag

An aerospace system operating under standard sea level conditions is governed by Airfoil & Wing Theory (Finite Wing Theory & Induced Drag). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: High-Lift Devices & Flaps

An aerospace system operating under standard sea level conditions is governed by Airfoil & Wing Theory (High-Lift Devices & Flaps). Compute the required parameter in standard SI units (rounded off to the acceptable range).

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

For inviscid, compressible flow past a thin airfoil, shown in the figure, free-stream Mach number and pressure are denoted by 𝑴𝑴∞ and 𝒑𝒑∞respectively. Ratio of pressure at point A and 𝒑𝒑∞is 0.8 and specific heat ratio is 1.4. If the Mach number at point A is 1.0 and rest of the flow field is subsonic, the value of 𝑴𝑴∞is

Subtopic: Finite Wing Theory & Induced Drag

Induced velocity w at a point zz = zz1 along the lifting line can be calculated using the formula ww(zz1) = - 1 4$\pi \pi$ ∫ dd$\Gamma$ ddzz ss -ss 1 zz-zz1 ddzz. Given $\Gamma$2 $\Gamma$oo2 + zz2 ss2 = 1, wherezz, $\Gamma$oo and sare given in figure below. For theabove semi-elliptic distribution of circulation, $\Gamma$, the downwash velocity at any point zz1,for symmetric flight can be obtained as, ww(zz1) = $\Gamma$oo 4$\pi \pi$ss [$\pi \pi$ + zz1II], where II = zz1 ∫ ddzz �ss2-zz2�zz-zz1� ss -ss . Which of the following options is correct if the induced drag is DDii (given ∫ �1 - zz2 ss2 ss -ss ddzz = $\pi \pi$ss 2 )

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

A gas turbine engine is operating under the following conditions: Stagnation temperature at turbine inlet 1350 K Stagnation pressure at the turbine inlet 10 bar Static temperature at turbine exit 800 K Velocity at turbine exit 200 m/s Total-to-total efficiency of turbine 0.96 $\gamma$ (ratio of specific heats) 1.33 CP(specific heat at constant pressure) 1.147 kJ/kgK The stagnation pressure (in bar) in the nozzle (considering isentropic nozzle) is equal to _______. AE 9/11 AE (GATE 2014) - AE

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

Consider a thin flat plate airfoil at a small angle to an oncoming supersonic stream of air. Assuming the flow to be inviscid, 2 d l C C is

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

The channel section of uniform thickness 2mm shown in the figure is subjected to a torque of 10 Nm. If it is made of a material with shear m odulus of 25 GPa, the twist per unit length in radians/m is _________ 300mm 600mm 300mm A 2013 AEROSPACE ENGINEERING - AE AE 8/19

Subtopic: Finite Wing Theory & Induced Drag

A glider is launched from a 500m high hilltop. Following data is available for the glider: Zero lift drag coefficient 0 0.02DC  , aspect ratio 10AR and Oswald efficiency factor e = 0.95. The maximum range of the glider in km is _________

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

Consider an airplane with rectangular straight wing at dihedral angle 010 . Lift curve slope of wing airfoil section (constant over the whole span of the wing) is 5.4 / .lcr a d  The roll stability derivative, lC in per radian is __________

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

A horizontal rectangular plate ABCD is hinged at points A, B and C. AC and BD are diagonals of the plate. Downward force P is applied at D. The upward reactions RA, RB, and RC at points A, B and C, respectively, are

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

If the circulation at the quarter chord (c/4) of the airfoil is 1 , the normal velocity is zero at

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

A second identical airfoil is placed behind the first one at a distance of c/2 from the trailing edge of the first. The second airfoil has an unknown circulation 2 placed at its quarter chord. The normal velocity becomes zero at the same chord-wise locations of the respective airfoils as in the previous question. The values of 1 and 2 are respectively

Subtopic: Finite Wing Theory & Induced Drag

For a wing of aspect ratio AR, having an elliptical lift distribution, the induced drag coefficient is (where CL is the lift coefficient)

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

An airfoil generates a lift of 80 N when operating in a freestream flow of 60 m/s. If the ambient pressure and temperature are 100 kPa and 290 K respectively (specific gas constant is 287 J/kg-K), the circulation on the airfoil in m^2/s is ____.

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

It is seen that the drag polar of a certain aerofoil is symmetric about the Cd axis. This drag polar could refer to

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

Consider a potential flow with free stream velocity V_inf, over a spinning circular cylinder of radius R and circulation Gamma. The lift per unit span is given by Kutta-Joukowski theorem as:

Subtopic: High-Lift Devices & Flaps

Modern warfare has changed from large scale clashes of armies to suppression of civilian populations. Chemical agents that do their work sllently appear to be suited to such warfare; and regretfully, there exist people in military establishments who think that chemical agents are useful tools for their cause. Which of the following statements best sums up the meaning of the alive passage:

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

A model airfoil in a wind tunnel that is operating at 50 m/s develops a minimum pressure co-efficient of - 6.29 at some point on its upper surface. The local airspeed at that point is

Subtopic: Finite Wing Theory & Induced Drag

A symmetrical airfoil section produces a lift coefficient of 0.53 at an angle of attack of 5 degrees measured from its chord line. An untwisted wing of elliptical planform and aspect ratio 6 is made of this airfoil. At an angle of attack of 5 degrees relative to its chordal plane, this wing would produce a lift coefficient of

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

J/kg-K respectively, the corresponding change in the temperature of the air is

Subtopic: Finite Wing Theory & Induced Drag

In an aerospace engineering analysis of Airfoil & Wing Theory (Finite Wing Theory & Induced Drag), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Subtopic: High-Lift Devices & Flaps

In an aerospace engineering analysis of Airfoil & Wing Theory (High-Lift Devices & Flaps), which one of the following statements is CORRECT regarding the governing aerodynamic and structural behavior?

Subtopic: Finite Wing Theory & Induced Drag

The variation of downwash along the span of an untwisted wing of elliptic planform is

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

Flow past an airfoil is to be modeled using a vortex sheet. The strength of the vortex sheet at the trailing edge will be

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

The geometrical features of a supercritical airfoil are:

Subtopic: Finite Wing Theory & Induced Drag

Consider an untwisted wing of elliptical planform in inviscid incompressible irrotational flow at an angle of attack of 4 degrees. The wing aspect ratio is 7 and the zero lift angle of attack is -2 degrees. The wing lift coefficient C_L is:

Subtopic: Finite Wing Theory & Induced Drag

For the same elliptic wing of aspect ratio 7 at 4 degrees angle of attack with zero-lift angle of -2 degrees, the induced drag coefficient of the wing C_Di is:

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

Mach number of an airfoil

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

The Joukowskii airfoil is studied in aerodynamics because

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

One of the criteria for high-speed airplanes is that the critical Mach number should be as high as possible. Therefore, high-speed subsonic airplanes are usually designed with

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

A 1 kg mass attached to a spring elongates it by 16mm. The mass is then pulled from its equilibrium position by 10mm and released from rest. Assuming the acceleration due to gravity of 9.81 m/s', the response of the mass in mm is given by

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

The ratio of the minimum pressure coefficient of the larger airfoil to the minimum pressure coefficient of the smaller airfoil is

Subtopic: Finite Wing Theory & Induced Drag

With-regard to this biplane, which of the following statements is true?

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

The lift curve slope of this wing is