given below:A rectangular wing with wing twist yields the spanwise circulation distributionkbV1roy) = kbv. (2)where k is a constant, b is the span length and V. is the free-stream velocity. The wing has anaspect ratio of 4. For all wing sections, the lift curve slope (ag) is 2 and the zero-lift angle ofattack (a=0) is 0.a. Derive expressions for the downwash (w) and induced angle of attack a distributionsalong the span.b. Derive an expression for the induced drag coefficient.c. Calculate the span efficiency factor.d. Calculate the value of k if the wing has a washout and the difference between thegeometric angles of attack of the root (y = 0) and the tip (y = tb/2) is:a(y = 0) a(y = ±b/2) = /18Hint: Use the coordinate transformation y = cos (0)

Approach to solving the question: Detailed explanation:(a) Downwash (wi)The downwash at any…

Answered: given below: A rectangular wing with…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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The following equation may be used to estimate the take-off ground run for an aircraft: Equation has been attached as an image. Calculate the take-off ground run, from a runway at ISA-SL conditions, for a twin engine aircraft for which the following data may be assumed Aircraft lift-off speed 155 knots Max take-off gross weight 220 tonnes Wing planform area (S) 358 m Wing CL (t/o flaps deployed, a = 0) 1.1 Wing span 53.18 m Oswald efficiency factor, e 0.7 KGE = CD(IGE) / Co(OGE) 0.4 Co sum (fuselage, wing, tailplane and nacelle) 0.015 Co for undercarriage 0.021 Co for flaps at taking-off setting 0.0073 Coefficient of rolling friction, u 0.02 Engine thrust (assumed constant) 310 kN per engine It may be assumed that 1knot = 0.51444 m/s It may be assumed that 1knot = 0.51444 m/s
2. The table below shows experimental data for the shape and pressure distribution on the upper and lower surface of an airfoil at zero angle of attack. X 0 0.25 0.5 0.75 1 Yu 0 0.0952 0.0922 0.0588 0 Fx = dYu dx 5 Y₁ 0 -0.0254 -0.0144 -0.0052 0 PL Pd) d: dx Y = Yu (x) Calculate the drag and lift force on the airfoil by numerically evaluating the integrals = S₁² ( P₂₁ = ['(P₁ - F (P₁ - Pu)dx 0 y = Y₂ (x) Pu 1.000 -1.640 -0.786 -0.212 0 Fy x Pi 1.000 0.589 0.426 0.322 0 Use finite difference approximations of the derivatives and the composite Simpson's rule to evaluate the integrals. Hint: Use central differences to estimate the derivatives wherever possible since they are more accurate than forward or backward differences.
5.2 Consider the following aircraft flying in straight and level unaccelerated trimmed flight at M 0.2 at sea level. MAC 12 ft Xeg W Xcg 0.5cwing Macail Macit = -5000 ft lb = 0 ac wing T = 3000 lb W = 12,000 lb Ctail =4 ft bwing = 30 ft Cwing = 8 ft (a) Find the lift of the wing and the lift of the tail. Assume Lwing and Ltail act at the quarter chord points. (b) Find the aircraft drag. (c) Assuming a rectangular wing, what is the total aircraft C,? (d) What is the pitching moment coefficient for the entire aircraft?
P
What is the maximum power generated by the wind farm with wind speed of 4 m/s? Typical wind turbines have rotor diameters from 40 m to 90 m (Assume increment of 5 m for this problem)-40 m is 80% efficient and efficiency decreases by 5% for every 5 m increase in diameter (i.e. 45 m=75%, 50=70...)-The ridge is 10 km long and wind turbines will be spaced in a single row. •Power in the wind per unit area of circular area is 1/2ρv3W/m2 (v is the wind speed, ρ is 1.3 kg/m3 for air) •Wind turbines cannot be spaced closer than 5 times its diameter without loosing power also there are no partial turbines.
6.10 A sphere advancing at 1.5 m/s in a stationary mass of water experiences a drag of 4.5 N. Find the flow velocity required for dynamic similarity of another sphere twice the diameter, placed in a wind tunnel. Calculate the drag at this speed if the kinematic viscosity of air is 13 times that of water and its density is 1.25 kg/m³. Ans. (9.75 m/s, 0.951 N)
I want the solution in detail and in handwriting, thank you very much
I need help with my MATLAB code. There is an error in the following code. The error says my orbitaldynamics function must return a column vector. Can you help me fix it? mu_earth = 398600.4418; % Earth's gravitational parameter (km^3/s^2) R_earth = 6378.137; % Earth's radius (km) C_d = 0.3; % Drag coefficient (assumed) A = 0.023; % Cross-sectional area of ISS (km^2) m = 420000; % Mass of ISS (kg) % Initial conditions: position and velocity (ISS state vector) % ISS initial state vector (km and km/s) - sample data state_ISS =[-2.1195e+03, 3.9866e+03, 5.0692e+03, -5.3489, -5.1772, 1.8324]; % Time span for 10 revolutions T_orbit = 2 * pi * sqrt((norm(state_ISS(1:3))^3) / mu_earth); time_span = [0, 10 * T_orbit]; % Step 3: Numerical integration using ODE solver options = odeset('RelTol', 1e-12, 'AbsTol', 1e-12); [t, state] = ode45(@orbitalDynamics, time_span, state_ISS, options); % Step 4: Plot the results figure; plot3(state(:, 1), state(:, 2), state(:, 3)); xlabel('X…
Aerodynamic Model: - Circular Disk Inside Dia= 40 mm Outside Dia= 80 mm • Angle of Attack= 15 Degree • Lift Force= 0.38 N • Drag Force=0.40 N • Wind Velocity= 20 m/sec Air Temperature= 30 °C (Note: Take Air Density at 30 °C) Required: - Find Lift and Drag Coefficient at 15 Degree Attack Angle.
A student team is to design a human-powered submarine for a design competition. The overall length of the prototype submarine is 95 (m), and its student designers hope that it can travel fully submerged through water at 0.440 m/s. The water is freshwater (a lake) at T = 15°C. The design team builds a one-fifth scale model to test in their university’s wind tunnel. A shield surrounds the drag balance strut so that the aerodynamic drag of the strut itself does not influence the measured drag. The air in the wind tunnel is at 25°C and at one standard atmosphere pressure. At what air speed do they need to run the wind tunnel in order to achievesimilarity?
Hello, please solve part b accurate and exact please.
5.25 A finite wing of area 1.5 ft² and aspect ratio of 6 is tested in a subsonic wind tunnel at a velocity of 130 ft/s at standard sea-level conditions. At an angle of attack of -1°, the measured lift and drag are 0 and 0.181 lb. respectively. At an angle of attack of 2°. the lift and drag are measured as 5.0 and 0.23 lb, respectively. Calculate the span efficiency factor and the infinite-wing lift slope.

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