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- is the drag coefficient 2 or 0.2?A 17,000-kg tractor-trailer rig has a frontal area of 9.2 m2, a drag coefficient of 0.96, a rolling resistance coefficient of 0.05 (multiplying the weight of a vehicle by the rolling resistance coefficient gives the rolling resistance), a bearing friction resistance of 350 N, and a maximum speed of 110 km/h on a level road during steady cruising in calm weather with an air density of 1.25 kg/m3. Now a fairing is installed to the front of the rig to suppress separation and to streamline the flow to the top surface, and the drag coefficient is reduced to 0.76. Determine the maximum speed of the rig with the fairing.A small aircraft has a wing area of 37 m2, a lift coefficient of 0.45 at takeoff settings, and a total mass of 4300 kg. Determine the following: The takeoff speed of this aircraft at sea level at standard atmospheric conditions The wing loading The required power to maintain a constant cruising speed of 300 km/h for a cruising drag coefficient of 0.036
- 13.94. A body travels through 60° standard air at 60 mph, and 5.5 hp is required to maintain this speed. If the projected area is 13.5 ft2 , find the drag coefficient. Ans. 0.28, A small aircraft has a wing area of 40 m2a lift coefficient of 0.45 at takeoff settings, and a total mass of 4000 kg. Determine (a) the takeoff speed of this aircraft at sea level at standard atmospheric conditions, (b) the wing loading, and (c) the required power to maintain a constant cruising speed of 360 km/h for a cruising drag coefficient of 0.035.A commercial airplane has a total mass of 70,000 kg and a wing planform area of 150 m2. The plane has a cruising speed of 558 km/h and a cruising altitude of 12,000 m, where the air density is 0.312 kg/m3. The plane has double-slotted flaps for use during takeoff and landing, but it cruises with all flaps retracted. Assuming the lift and the drag characteristics of the wings can be approximated by NACA 23012 , determine (a) the minimum safe speed for takeoff and landing with and without extending the flaps, (b) the angle of attack to cruise steadily at the cruising altitude, and (c) the power that needs to be supplied to provide enough thrust to overcome wing drag.
- 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.A jet airplane weighs 160,000 N and has a zero-lift drag coefficient of 0.008 and a wing area of 42 m^2. At 100 m/s at sea level, the rate of climb is 11.5 m/s. The thrust developed by the engines is equal to 27,000 N. Determine the maximum rate of climb and the corresponding flight speed at sea level .An airplane is cruising at a velocity of 950 km/h in air whose density is 0.526 kg/m3. The airplane has a wing planform area of 90 m2. The lift and drag coefficients on cruising conditions are estimated to be 2.0 and 0.06, respectively. The power that needs to be supplied to provide enough trust to overcome wing drag is (a) 21,500 kW (b) 19,300 kW (c) 23,600 kW (d ) 25,200 kW (e) 26,100 kW
- How does the Reynolds number effect the lift and drag coefficient for a symmetrical airfoilHow does a winglet on the wing tip reduce induced drag? Which drag is higher if an aircraft is flying at 100knts and the L/Dmax is 120knts? How do you know this?Fairings are attached to the front and back of a cylindrical body to make it look more streamlined. What is the effect of this modification on the (a) friction drag, (b) pressure drag, and (c) total drag? Assume the Reynolds number is high enough so that the flow is turbulent for both cases.