i need the answer quickly 6. For a wing of aspect ratio AR, having an elliptical lift distribution, the induced drag coefficient is(where CL is the lift coefficient)C.(a)TAR(b)TARC.2пAR(d)AR27. Laminar flow airfoil is used to reduce the(a) pressure drag (b) induced drag (c) skin friction drag (d) wave drag8. Set the aerofoil your chosen angle of incidence isgives a good installed pressure distribution.(a) twelve degree (b) ten degree (c) eight degree9. The critical Mach number for a thick airfoil will be(a) lesser than a thin airfoil. (b) greater than a thin airfoil.(c) equal to a thin airfoil.(d) cannot be related to thin airfoil10. What is the dimension for Lift coefficient?(a) N/s(b) kg/N(c) Dimensionless

Given Drag coefficient Laminar flow airfoil Angle of incident To find Aspect ratio to drag…

Answered: 6. For a wing of aspect ratio AR,…

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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For the shown continuously circular (i.e. not parabolic) arc airfoil with sharp corners of each 8 = 5°, at 0° angle of attack with Mo = 3 and assuming steady, two-dimensional flow, calculate the: a) pressure coefficient distribution; b) lift coefficient; c) drag coefficient. Moo 8 ********* 8
The original Flettner rotor ship was approximately 100 ftlong, displaced 800 tons, and had a wetted area of 3500 ft2. Assketched in Fig. , it had two rotors 50 ft high and 9 ft indiameter rotating at 750 r/min, which is far outside the range. The measured lift and drag coefficients for eachrotor were about 10 and 4, respectively. If the ship is mooredand subjected to a crosswind of 25 ft/s, as in Fig. whatwill the wind force parallel and normal to the ship centerlinebe? Estimate the power required to drive the rotors.
a)What is the impact of increasing Reynolds number on skin friction and pressure drags over an airfoil? What can be happened for separation in this case? b) What is an adverse pressure gradient and where does it occur on an airfoil (show that on a sketch)? c) Why lift-to-drag ratio is an important parameter for an aircraft? d)How can changing in altitude affect the aircraft power required, PR? Show thatmathematically and graphically?
3) An advertising sign mounted on the roof of a car is 33 inches tall, 15 inches wide and 54 inches long (airflow direction). The underside of the sign is flush with the top surface of the roof. Take air properties to be: p = 0.075 lbm/ft' and u= 1.22x10 lbm/ft.sec. Used a pressure drag coefficient of 1.2 for the advertisement sign. Calculate the total drag on the sign and the power required to overcome its effect if the car is travelling at a constant speed of a) 12 mph and b) 45 mph. Note: Provide a schematic diagram (sketch) of the problem configuration (if applicable). Every numerical calculation must be preceded by the appropriate equation. Do not forget units & dimensions during your calculations.
4. Write down the lift curve equation (lift coefficient versus angle of attack) according to the thin airfoil theory. What is the amount of the lift curve slope for a thin airfoil ? NACA 2412 airfoil Eg. (4,57) C 2.0 - 1.e 1.2 Lift coefficient 0.8 0.4 -0.4 Eg. (4,64) -0.1 Moment coefficient -0.8 -0.2 -1.2 -0.3 Re - 3.1 X 10 O Re- 8.9 x 10 -0.4 16 a, degrees de; = ? da
A wing of 2 percent camber, 5-in chord, and 30-in span istested at a certain angle of attack in a wind tunnel with sealevelstandard air at 200 ft/s and is found to have lift of 30 lbfand drag of 1.5 lbf. Estimate from wing theory (a) the angle ofattack, (b) the minimum drag of the wing and the angle of attackat which it occurs, and (c) the maximum lift-to-drag ratio.
The drag coefficient for a car with a frontal area of 26 ft? is being measured in an 8 ft x 8 ft wind tunnel. The density of air under the test conditions is 2.4 x 10 3 slugs/ft, When the air flow rate is, 500,000 ft/min, the drag force on the car was measured to be 170 lb. The drag coefficient under the test conditions is most nearly O 0.30 O 0.32 O 0.28 O 0.34
Consider the equation v (t) = " (1 – e-le/m)t) For the free-falling bungee jumper with linear drag, assume a first jumper is 73.5 kg and has a drag coefficient of 12.5 kg/s. If a second jumper has a drag coefficient of 14.5 kg/s and a mass of 85 kg, how long will it take him to reach the same velocity jumper 1 reached in 8 s? (Round the final answer to three decimal places.)
The drag polar for the ASW 27B high performance sailplane is: CD = 0.01 +0.02CL2. What is its maximum lift-to-drag (L/D) ratio? 18 25 35 70
For a 10 deg included angle wedge at 0 deg AOA, calculate the lift and drag coefficient (Cl = 0, Cd = 0.082). Then calculate the lift and drag at AOA=4 deg (Cl = 0.16, Cd = 0.093). Let M=2.
An aircraft has the drag polar, C_d=0.015+0.05C_l^2 For a lift coefficient of 0.5, find the value of the drag coefficient and lift drag ratio? I am asking It For Second Time. Please Read the Question Carefully.
A light combat aircraft weighs 75,000 N and has a wing area of 27 m?. The maximum lift coefficient with high-lift devices is 1.8, and the structural limit load factor is 6.0. While flying at 250 km/h, the aircraft makes a 90 deg turn in 8 s at sea level holding a constant altitude and at an angle of attack such that the lift-to-drag ratio is 8.0. Find (a) the bank angle, (b) load factor, (c) radius of turn, and (d) the thrust required. [Answer: (a) µ = 54.26 deg, (b) n = 1.7120, (c) R %3D 353.7665 m, and (d) T = 16,050 N.)

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