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.
The airplane weighs 144100 lbs and flies at constant speed and trajectory given by 0 on the figure. The plane experiences a drag force of 73620 lbs. a.) If = 11.3°, determine the thrust and lift forces required to maintain this speed and trajectory. b.) Next consider the case where is unknown, but it is known that the lift force is equal to 7.8 times the quantity (Fthrust Fdrag). Compute the resulting trajectory angle - and the lift force in this case. Use the same values for the weight and drag forces as you used for part a. Уллу Fdrag 10. Ө Fthrust cc 10 2013 Michael Swanbom BY NC SA Flift Fweight The lift force acts in the y' direction. The weight acts in the negative y direction. The thrust and drag forces act in the positive and negative x' directions respectively. Part (a) The thrust force is equal to lbs. The lift force is equal to Part (b) The trajectory angle is equal to deg. The lift force is equal to lbs. lbs.
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)
The airplane weighs 144100 lbs and flies at constant speed and trajectory given by 0 on the figure. The plane experiences a drag force of 73620 lbs. 0 a.) If 11.3°, determine the thrust and lift forces = required to maintain this speed and trajectory. b.) Next consider the case where is unknown, but it is known that the lift force is equal to 7.8 times the quantity (Fthrust Fdrag). Compute the resulting trajectory angle and the lift force in this case. Use the same values for the weight and drag forces as you used for part a. 20. YAAY' Farag Ө Fthrust CC + BY NC SA 2013 Michael Swanbom Flift Fweight The lift force acts in the y' direction. The weight acts in the negative y direction. The thrust and drag forces act in the positive and negative x' directions respectively. Part (a) The thrust force is equal to 101,855 ☑ lbs. The lift force is equal to 141,282 ☑ lbs. Part (b) The trajectory angle 0 is equal to 7.31 ✓ deg. The lift force is equal to 143,005 ☑ lbs.
Give me right solution with clear calculations
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.

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