If area ratio is 1.110 then, at which mach number flow is flowing?(a) 0.68(b) 1.89(c) 2(d) 0.21This question was addressed to me in an internship interview.This question is from Propulsion topic in portion Propulsion and Fuel System Integration of Aircraft Design

If area ratio is 1.110 then, at which mach number flow is flowing?(a)

1.	If area ratio is 1.110 then, at which mach number flow is flowing?(a) 0.68(b) 1.89(c) 2(d) 0.21This question was addressed to me in an internship interview.This question is from Propulsion topic in portion Propulsion and Fuel System Integration of Aircraft Design
Answer» RIGHT answer is (a) 0.68 To explain: Given, area ratio A/A* = 1.110 Now, as we KNOW, A/A* = (1/M)(1+0.2M2)30.5787 For given problem, we will substitute different VALUES of MACH number from the options. Let’s consider M = 0.68 Hence, for assumed value of Mach number, A/A* = (1/0.68)(1+0.20.68^2)^30.5787 A/A = 0.8510*1.09248^3 = 1.110. The evaluated area ratio is equal to the given area ratio. Hence, correct value of Mach number is 0.68.

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If area ratio is 1.110 then, at which mach number flow is flowing?(a) 0.68(b) 1.89(c) 2(d) 0.21This question was addressed to me in an internship interview.This question is from Propulsion topic in portion Propulsion and Fuel System Integration of Aircraft Design

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