AOE 3104 Aircraft Performance Problem Sheet 2 (ans) 6. The ...

12. A high-speed subsonic Boeing 707 airliner is flying at a pressure altitude of 12 km. A Pitottube on the vertical tail measures a pressure of 2.96x10 4 N/m 2 . At what Mach number is theairplane flying?@ 12 km the pressure in a standard atmosphere is 19320 N/m 2The pitot tube read stagnation pressure that is P 0 = 29600 N/m 2We can use the compressible form of Bernoulli’s equation:orM = 0.80513. A high-speed aircraft is flying at Mach 0.95 in a standard atmosphere at 30,000ft.Determine: a) True airspeedb) indicated airspeed on a incompressibly calibrated airspeed indicatorc) indicated airspeed on a compressibly calibrated airspeed indicatord) equivalent airspeed@ 30,000 ft, P = 628.50 lbs/ft 2 , T = 411.77 deg R, , = 0.000890 sllugs/ft 3a) The true airspeed can be obtained by finding the speed of sound, since the Mach number isgiven.The true airspeed is thenb) The first thing we need to do is to calculate the total pressure since all airspeed indicators onlyuse P 0 - P. Since at high subsonic speed we need to use the compressible form of Bernoulli’sequation.