problem 1: Find out maximum range and endurance of an airplane weighing 12000 N. This is powered by 300 HP engine, has wing span of 7.4 m and wing area of 9.00 m^{2}. Take C_{DO} = 0.025, e = 0.85 and η_{p} = 0.80 Fuel, Weight factor is 0.15 AUW and c = 0.2 kg/hphr
problem 2: An airplane weighing 250 000 N has wing plan form area = 83 m^{2} and wing aspect ratio of 9 and parasite drag coefficient of 0.18. Its trailing vortex drag is 10 percent more than the minimum. Take the thrust power development to be as 2.6 MW at all speeds. Compute maximum speed and maximum rate of climb at sea level.
problem 3: Plot the climb performance hodograph for a twin jet airplane with given data at sea level W = 1,00,000 N wing span = 19.5 m. S = 45 m^{2}, T = 2 x 16,500 N, C_{DO} = 0.02, e = 0.85. Hence find out:
a) V for best climb,
b) max R/C,
c) Vmax . level
problem 4: Find out the tip-speed of a propeller used on an airplane flying at a speed of 560 kmph. The RPM of the propeller is 1050 and its advance ratio was found to be 2.10. Could you find out the diameter of the propeller from this data?
problem 5: prepare short notes on the given statements:
a) M_{critical}, M_{DD} and prevailing methods to reduce or postpone the same, by using laminar flow (6 digits NACA aerofoil) and super critical aerofoil. What do you mean by the term crest critical Mach number? As well describe ‘transonic area rule’.
b) Fixed pitch, variable pitch and constant speed propeller.