Problem 3. A supersonic airplane is cruising at a Mach number of Ma = 2.2 at an altitude of H= 17 km on a standard day. (a) Calculate the speed, V, of the airplane. (b) Calculate the Mach angle using the temperature at z = H and at sea level. (c) Estimate how long after the aircraft passes directly above a ground observer would hear the sound created by the airplane. Recall that for the U.S. Standard Atmosphere, the temperature distribution below H is given by: T = To + m z for 0 < z< 11 km where To = 288.15 K and m = -6.6 K/km; T = 216.65 K for 11 < z< 20.1 km.
Problem 3. A supersonic airplane is cruising at a Mach number of Ma = 2.2 at an altitude of H= 17 km on a standard day. (a) Calculate the speed, V, of the airplane. (b) Calculate the Mach angle using the temperature at z = H and at sea level. (c) Estimate how long after the aircraft passes directly above a ground observer would hear the sound created by the airplane. Recall that for the U.S. Standard Atmosphere, the temperature distribution below H is given by: T = To + m z for 0 < z< 11 km where To = 288.15 K and m = -6.6 K/km; T = 216.65 K for 11 < z< 20.1 km.
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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Transcribed Image Text:Problem 3. A supersonic airplane is cruising at a Mach number of Ma = 2.2 at an altitude of H = 17 km on a
standard day. (a) Calculate the speed, V, of the airplane. (b) Calculate the Mach angle using the temperature at 2 = H
and at sea level. (c) Estimate how long after the aircraft passes directly above a ground observer would hear the sound
created by the airplane. Recall that for the U.S. Standard Atmosphere, the temperature distribution below H is given
by: T = To + m z for 0 < z < 11 km where To = 288.15 K and m = -6.6 K/km; T = 216.65 K for
11 <z< 20.1 km.
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