Calculate lift, drag and (T/W) for an aeroplane with velocity 500 m/s, wing area 45 m2 , a drag coefficient 0.05 and a lift coefficient 0.9
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Calculate lift, drag and (T/W) for an aeroplane with velocity 500
m/s, wing area 45 m2
, a drag coefficient 0.05 and a lift
coefficient 0.9
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- 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 0.34In the vertical wind tunnel used in paratrooper training, find the wind tunnel free speed required to keep a 75 kg person suspended in the air in a horizontal position. The height of this person is 1.7m and the width is 38cm and the front drag coefficient is around 1. Atmospheric pressure and temperature inside the tunnel are Patm = 85kPa and T = 25C, respectively.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.)
- Calculate lift, drag and (T/W ratio) for an aeroplane with velocity 500 m/s, wing area 45 m2 , a drag coefficient 0.05 and a lift coefficient 0.9A 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.)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.
- A 3 inch diameter steel sphere achieve a terminal velocity of 122 inch per seconds when dropping through it all column of liquid is 87 lbm/ feet cube. The density of steel is 488 lbs per feet cube. The final drag coefficient of the square is most nearly? a. 0.22 b. 0.34 c. 0.40 d. 0.48Consider a 1200 kg car presenting a front-end area 2.60 m2 and having a drag coefficient 0.385. It can achieve instantaneous acceleration 3.00 m/s2 when its speed is 10.0 m/s. Ignore any force of rolling resistance. Assume that the only horizontal forces on the car are static friction forward exerted by the road on the drive wheels and resistance exerted by the surrounding air, with density 1.20 kg/m3. (a) Find the friction force exerted by the road.(b) Suppose the car body could be redesigned to have a drag coefficient of 0.165 If nothing else changes, what will be the car's acceleration?(c)Assume that the force exerted by the road remains constant. Then what maximum speed could the car attain with D = 0.385?(d) What maximum speed could the car attain with D = 0.165?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…
- 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 ********* 8What is the f (equivalent drag area) for an aircraft that creates 600 lbs of parasite drag at 10,000 ft STP and 250 KTAS?Alight aircraft with a wing area of 114 m^2 and a span of 29 m is flying at an altitude of 3,550 m when the engine suddenly fails. If the parasite drag coefficient is 0.0325, determine the maximum distance over the ground that the aircraft can cover. Assume elliptical lift distribution. Provide answer in km, nearest hundredths.