Qs: A two-dimensional supersonic inlet is to be designed to operate at Mach 2.4. Deceleration is to occur through a series of oblique shocks followed by a normal shock, as shown in Figure. Determine the loss of stagnation pressure for the cases of two, three, and four oblique shocks. Assume the wedge turning angles are each 6°. M. - 2.4 V, pu P.- 50 kPa 12 V. Pu T.-0C

Qs: A two-dimensional supersonic inlet is to be designed to operate at Mach 2.4. Deceleration is to occur through a series of oblique shocks followed by a normal shock, as shown in Figure. Determine the loss of stagnation pressure for the cases of two, three, and four oblique shocks. Assume the wedge turning angles are each 6°. M. - 2.4 V, pu P.- 50 kPa 12 V. Pu T.-0C

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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Question

Qs: A two-dimensional supersonic inlet is to be
designed to operate at Mach 2.4. Deceleration is
to occur through a series of oblique shocks
followed by a normal shock, as shown in Figure.
Determine the loss of stagnation pressure for the
cases of two, three, and four oblique shocks.
Assume the wedge turning angles are each 6°.
M. = 2.4
Vi, Pai
P.- 50 kPa
12°
Vi, Pai
T.-0° C

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