4) Calculate the thrust reduction due to the existence of a shock wave at the exit of the rocket no: given below, compared to the no shock case. P=200kPa I M=1.4 MCI M = 1 T=mle A₂ = 3m²
4) Calculate the thrust reduction due to the existence of a shock wave at the exit of the rocket no: given below, compared to the no shock case. P=200kPa I M=1.4 MCI M = 1 T=mle A₂ = 3m²
Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)
8th Edition
ISBN:9781305387102
Author:Kreith, Frank; Manglik, Raj M.
Publisher:Kreith, Frank; Manglik, Raj M.
Chapter6: Forced Convection Over Exterior Surfaces
Section: Chapter Questions
Problem 6.14P
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Transcribed Image Text:4) Calculate the thrust reduction due to the existence of a shock wave at the exit of the rocket no:
given below, compared to the no shock case.
P=200kPa
I
M=1.4
MCI
M = 1
T=mle
A₂ = 3m²
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