A supersonic wind tunnel consists of C-D nozzle, constant area test...

A supersonic wind tunnel consists of a C-D nozzle, constant area test section, and C-D diffuser. The conditions are such that the sonic flow exists at each throat of the nozzle and diffuser (M_{th, nozzle} = M_{th, diffuse} =1). The Mach number measured at the middle section of the duct is 1.8. Calculate the following:

i. Mach numbers M₂, M_3, and M₄

ii. The throat areas for both nozzle and diffuser (A_tn, A_td)

iii. The stagnation pressure at nozzle inlet and diffuser exit (P_O4, P_O1)

iv.  The air mass flow rate, m_a

v.   The power Required to drive the compressor [Power =m_a*C_P*(T_O1-T_∞)]

Assume that, To1=T∞*(Po1/P∞)(γ-1)/γ

 

Transcribed Image Text:

P..=100 kPa wwww 100 500 K- 1 compressor M<1 Isentropic 2 M>1 Mid section Test section L=3m f=0.02 D=0!3m 3 M<1 Isentropic 4 _P=100kPa D₂=0.3m P..=100 kPa wwww 100 500 K- 1 compressor M<1 Isentropic 2 M>1 Mid section Test section L=3m f=0.02 D=0!3m 3 M<1 Isentropic 4 _P=100kPa D₂=0.3m

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a Calculate the stagnation pressure of ... View the full answer