E1.6 A 3.57 m diameter propeller (10 m2 swept area) on an airplane requires 581.6 kW...
Problem III A small airplane has a total mass of 1800 kg and a wing area of 42 m2. While cruising at arn altitude of 4000 m at a constant speed of 280 km/h this airplane generate 190 kW of power. At this altitude he air density ρ-0.82 kg/m3 a) Determine the thrust developed by this airplane b) Determine the lift and drag coefficients of this airplane
Question 10 4 pts If a 0.91 m diameter propeller is operating at an advance ratio (J) of 0.68, an efficiency of 0.75, and requires 684 kW of input mechanical power while spinning at 152 rpm. How much thrust is the propeller generating? Enter your answer in kilaNewtons to at least three significant figures.
Question 5 (14 marks) The following are the characteristics of a single-engine light aircraft 9.8 m Wing span Wing area 15.2 m2 Height of wing 1.20 m All up weight 19.2 kN Power plant: 150 kW (sea-level) Propeller efficiency: 85% Maximum lift coefficient: 1.32 Parasite drag coefficient: 0.022 Oswald's efficiency factor: 0.88 Using the above data calculate the: a. stalling speed in km/h, (39.53 m/s, 142.3 km/h) aspect ratio, induced drag coefficient and hence total drag at Lift-off Stalling Speed...
A small jet airplane has a total wing area of 62.5 m2 and a mass of 7.03 104 kg. (a) If this jet is in horizontal flight, determine the pressure difference between the lower and upper surfaces of the wings. (b) When the speed of air traveling over the wing is 237 m/s, determine the speed of air under the wing. Use 1.29 kg/m3 as the density of air.
A small jet airplane has a total wing area of 77.5 m2 and a mass of 7.03 x 104 kg (a) If this jet is in horizontal flight, determine the pressure difference between the lower and upper surfaces of the wings Pa (b) When the speed of air traveling over the wing is 237 m/s, determine the speed of air under the wing. Use 1.29 kg/m3 as the density of air. m/s (c) Why do all aircraft have a maximum...
Прr ср. For Questions 1-5 below, consider a propeller aircraft with the following properties. Please take into account whenever PA is used. W = 160,000 N c= 5 x 10-7 m-1 W = 120,000 N e = 0.6 g=9.81 m/s2 S = 60 m2 AR = 10 Po = 1.225 kg/m3 (PA)mazo 2,600 kW = 0.036 Ph=1000 = 1.110 kg/m3 Прr 0.8 Cumax = 1.75 1. (15 points) Find the maximum range of the aircraft at the altitude h =...
9 Required information An airplane has a mass of 48,000 kg, a wing area of 340 m*, a maximum lift coefficient of 3.2, and a cruising drag coefficient of O.03 at an altitude of 12.000 m. Take the density of standard air as p1-1225 kg/m3 at sea level and p2 0.312 kg/m at 12,000 m altitude. Determine the safe takeoff speed at sea level, assuming it is 20 percent over the stall speed The safe takeoff speed at sea level...
What is the net upward force on an airplane wing of area 24.9 m2 if the speed of air flow is 250 m/s across the top of the wing and 234 m/s across the bottom? (The density of air where the airplane flies is ρair = 1.16 kg/m3.)
An airplane has an effective wing surface area of 21.9 m2 that is generating the lift force. In level flight the air speed over the top of the wings is 70.0 m/s, while the air speed beneath the wings is 47.0 m/s. What is the weight of the plane?
Q7. Consider the twin-jet airplane described as follow: wing area = 47 m2, aspect ratio = 6.5, Oswald efficiency factor = 0.87, weight = 103,047N, and zero-lift drag coefficient = 0.032. The airplane is equipped with two jet engines with 40,298 N of static thrust each at sea level. The thrust-specific fuel consumption is 1.0 N of fuel per newton of thrust per hour, the fuel capacity is 1900 gal, and the maximum gross weight is 136,960 N. Calculate the...