Ex.9:-supersonic variable-geometiy inlet îs desngned2.17 The cnross-seetional areaofA the înlet isfora Mach n.theentrance, o-180m?atDeterwine,@ the throat oured when the normal shock waveis just swallowed.Q the throatatthe design tMach no.aared

for supersonic flow Mach no - 2.77 A = 0.180 m2 To find - a) Throat area when the normal flow is…

Ex. 9:- A supersonic variable-geometry inlet is designed The cross-sectional area 2.77 for a Mach no. 2 at the of the inlet is. 0-180m² entrance Determine, @ the throat area when the normal shock wave is just swallowed. the throat ared at the design Mach no.

Ex. 9:- A supersonic variable-geometry inlet is designed The cross-sectional area 2.77 for a Mach no. 2 at the of the inlet is. 0-180m² entrance Determine, @ the throat area when the normal shock wave is just swallowed. the throat ared at the design Mach no.

Structural Analysis

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ISBN:9781337630931

Author:KASSIMALI, Aslam.

Publisher:KASSIMALI, Aslam.

Chapter2: Loads On Structures

Section: Chapter Questions

Problem 1P

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Question

Ex.9:-
supersonic variable-geometiy inlet îs desngned
2.17 The cnross-seetional area
of
A the înlet is
for
a Mach n.
the
entrance
, o-180m?
at
Deterwine,
@ the throat oured when the normal shock wave
is just swallowed.
Q the throat
at
the design tMach no.
aared

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