Problem 1) A high speed subsonic airplane with wing span 10 m and a mean chord of 1.5 m is flying at the altitude of 5 km. a pitot tube at the wing leading edge measures the stagnation pressure as 70 Kpa. a) Assume isentropic flow and calculate the temperature at the stagnation point, and the aircraft true and calibrated airspeeds. b) The airplane wing is built of NACA 2415 airfoil and it has span efficiency factor of 0.9 and profile drag coefficient of 0.0045. Calculate the finite wing lift and drag forces at 60 angle of attack. Problem 2) Consider an airplane in steady level flight at the altitude of 3.0 km. the 700 kg airplane has reference area g1871 = 1:28918:3675=0 g45 8:90.02, and g1879= 1.4 a )assume that the aircraft has prop engines with relatively constant power of g184520 hg 18 thes altitude and the propeller efficiency is 80%. Assume small climb angle and calculate the maximum rate of climb b) if the airplane engines fail at 3 km altitude what would be the farthest distance that it can glide till it reaches the sea level. What is the maximum possible time that it can glide till it reaches the sea level? Assume standard atmospheric condition with no wind and small angle of descent. Problem 3) Consider a turboject transport aircraft at altitude of 4 km with weight g1849 =450,g1863g1840 wing aspect ratio g 1827g ference area g1845 = 109 918 efficiency factor g 1857 =.0186 8290.025, 8219268 327623299 a) Calculate the minimum thrust required for this aircraft to be able to perform steady level flight (SLF) at this altitude. Assuming the attached performance chart is for one engine, how many engines the aircraft needs to be able to fly in SLF at this altitude? b) If the aircraft has two engines and the pilot is using 50% of the "maximum cruise thrust" at constant airspeed 200 kt, estimate the climb or descent angle and the rate of fuel consumption in 1b/hr, (assume the angle is small) Problem 4) A 2500 kg helicopter is operating in level forward flight at 125 kts. The equivalent flat plate area and air density are g1858 andg 2025=1.03 g18689105/meters are: radius g1844 =6olig5 52026=00835 g1870,g:1839 911856/g1871 Calculate the total required power. Question 1) Draw a simple schematic for a Turbojet engine with after burners, name the major components of the engine, and write their function