The Cessna Cardinal, a single-engine light plane, has a wing area of 16.2 m² and an aspect ratio of 7.31. Assume the span efficiency factor is 0.62. If the airplane is flying at standard sea- level conditions with a velocity of 290 km/h, what is the induced drag when the total weight is 9800 N? The induced drag when the total weight is 9800 N is N.
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- The drag polar equation of a light airplane in clean configuration can be written as Cp = 0.358 + 0.0405 C₁². It has a weight of 18,681 N. The wing area is 14.41 m². Calculate the minimum power required in watts. (Round off answer with no decimal places, No units, No commas) Answer given: 1461792 A 5,000 lbs. aircraft has an excess power of 75 hp at sea level. If the service ceiling is 3,657.6 m, determine the time to climb from sea level to absolute ceiling in minutes. (Round off answer with no decimal places. No units, No commas) Answer given: 173) 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.A helicopter is hovering at an altitude where the density of air is 1.165 kg/m³. The helicopter rotor disc has a diameter of 9 m and is rotating at 466 rpm, with the blades having a chord of 0.16 m. Estimate the drag force in newtons per unit span along an elemental strip at the mid-span of the blade. You may assume the drag coefficient of the blade at the mid-span is 0.025.
- What is the total coefficient of a drag if at the maximum CL/Cd, the lift created is 60 lbs? The speed of the aircraft is 20 mph, and the area of the elliptical wing is 70 ft^2. The span of the wing is 20 ft. Assume standard sea level conditions.31) Estimate the drag force on the fuselage shown below for a cruising speed of 200 m/s at 10,000 m. 8 m 5 m W m W = 20 m Hint 1: To calculate the drag force split the fuselage into 4 parts: front hemisphere, cylindrical body, vertical stabilizer, back hemisphere. Model the front and back hemispheres as flow over a sphere. For simplicity treat the cylindrical body and vertical stabilizer as flat plates Hint 2: Use Ca vs Reynolds number graphs for sphere and flat plate. If your Reynolds number is greater/smaller than the Cd vs Reynolds graph range, you can instead use the greatest/smallest number available on the graph.A NACA 2412 airfoil with a chord of 0.64m is flying in an airstream of standard sea level conditions. The freestream velocity is 70 m/s. Given the lift per unit span is 1,254 N/m. By using the experimental data for NACA 2412 data plot in Figure Q1c, investigatethe angle of attack of the airfoil and the analyze the value of drag per unit spanof the airfoil. Given that at standard sea level, ?=1.789×10-5 kg/m.s.
- 1. An airplane weighs 36,000 lb. and has a wing area of 450 fte. The drag equation is C, =0.014 + 0.05C} . It is desired to equip this airplane with turboprop engines with available power such that a maximum speed of 602.6 mph at sea level can be reached. The available power is assumed to be independent of flight speed. Calculate the maximum rate of climb and the speed at which it occurs. Given: W = 36,000 lb S = 450 ft² C, = 0.014+0.05C V = 602.6 mph max THPy = cons tan t THP AV constant Max EHP Point of THP, REQD. Flisht Speed. V Vmax 602.6 mph Required: Max R.C. and Vmax R.C. Horsepower, hpAircraft flying at an altitude of (3 Km) with a velocity of (100 m/sec). The planform area of the wing is (206 m² ). Find the overall drag force acting on this aircraft if you have the following data :- Aspect ratio= 10, Weight of the aircraft = 7.5 x 105 kg.m/s² Span efficiency factor = 0.95 Wing cross section is NACA 4412 airfoll Drag coefficient = 0.0066. For a wing of aspect ratio AR, having an elliptical lift distribution, the induced drag coefficient is (where CL is the lift coefficient) (b) TAR CL 2TAR (d) TAR2 (a) TAR 7. Laminar flow airfoil is used to reduce the (a) pressure drag (b) induced drag (c) skin friction drag (d) wave drag 8. Set the aerofoil your chosen angle of incidence is gives a good installed pressure distribution. (a) twelve degree (b) ten degree (c) eight degree 9. 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 airfoil 10. What is the dimension for Lift coefficient? (a) N/s (b) kg/N (c) Dimensionless
- The rectangular wings of a microlight aircraft have a combined spanwise length of 9.144 m and streamwise (direction of air flow) width of 0.9144 m The wings have a coefficient of form drag of 0.01 and a lift coefficient of 0.3 in cruise. When cruising at a speed of 150km/h and altitude of 3,000 feet, the temperature and absolute pressure of the atmospheric air are 5ºC and 90 kPa, respectively. a) Calculate the density of the air at cruising altitude. b) Calculate the form drag on the wings. c) Calculate the Reynolds number of the wings. d) Calculate the skin friction drag on the wings. e) If the fuselage of the microlight is spherical with a diameter of 1m and the total drag of the aircraft is represented by the contributio combined, and assuming the skin friction drag is negligible for the fuselage only, calculate the combined total drag force. fuselage and wings f) Calculate the power required to overcome total drag in cruise, using the value calculated in part e). g) Calculate the…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.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