/Aircraft Cessna Cj-1 in climb stage, Climbing with angle of attack equal to 8º. Cj-1 has the following data Weight=2038.75 kg Wing area = 50 m² CDo = 0.018 Aircraft speed in climbing = 25m/s e = 0.75 p at 300 m = 0.909 And the variation of angle of attack with lift coefficient shown in figure. 1.8 Calculate 1.4 1.2 I. the thrust and power required for climbing to high 1.4 3000 m Climbing rate CL aspect ratio=7

/Aircraft Cessna Cj-1 in climb stage, Climbing with angle of attack equal to 8º. Cj-1 has the following data Weight=2038.75 kg Wing area = 50 m² CDo = 0.018 Aircraft speed in climbing = 25m/s e = 0.75 p at 300 m = 0.909 And the variation of angle of attack with lift coefficient shown in figure. 1.8 Calculate 1.4 1.2 I. the thrust and power required for climbing to high 1.4 3000 m Climbing rate CL aspect ratio=7

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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q: An aircraft is flying straight and level at a certain altitude with a velocity of 214 fps. Determine the power required if the wing area is 115 ft? and the total drag coefficient is 0.067. Assume SSLC (p=0.002377 slug/ft3). Provide answer in ft-Ib/s. and round off to the nearest whole number. Solve using standard English units.
19) You're flying a plane with a max speed of 267 ft/s and a wing area of 175ft^2 and a lift coefficient of 0.205, your plane weighs 2000lbs. What is the smallest radius turn you can make at 5000ft of altitude(where the air is 0.002048 slug/ft^3) at a constant speed without loosing altitude?
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 oC (Note: Take Air Density at 30 oC) Required: - Find Lift and Drag Coefficient at 15 Degree Attack Angle.
Discuss and comment on the effect of drag polar for Re 5003352.
Q1: Find the boundary layer thickness (6) equation, the shear stress (to) and the coefficient of drag (C₁) if the velocity distribution in the laminar boundary layer over the face of a spillway was observed to be: u 7- (C)-()*+C)*. U Then calculate the boundary layer thickness and drag force if the air flows over a sharp edged flat plate 0.25m long and 0.5m wide at a velocity 1 m/s, take the air density 1.23 kg/m³ and the kinematic viscosity is 1.46*10-5 m/s².
Strictly don't use chatgpt for this question.
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.
You are designing an airfoil for a new hobby RC plane. Because of your limited knowledge, you have mistakenly approximated your airfoil as an ellipse with a = 75mm and b = 12mm. Here, “a” is the depth of your wing and “b” is the thickness. Your plane travels through the air at approximately 20mph (8.9m/s). As it does so, skin friction produces a drag-induced heat of 800W on your wind, of length 1m. Properties of Air: k = 0.025 W/mK, Pr = 0.72, v = 1.847 x 10−5, u = 16.84 x 10−6, p = 1.2 kg/m3, B = 1/Tf (ideal gas), TInfinity = 25oC a) What is the Reynold’s number? Hint: “D” is taken to be the thickness for an elliptical crosssection. b) What is the Nusselt number? c) What is the convection coefficient? d) What is the average temperature of your wing? Assume an ellipse perimeter of approximately 200mm.
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