Solve d 6.33 A normal-shock inlet operates in a Mach 1.86stream with ambient static pressure of po = 30 kPa.Neglecting total pressure loss in the subsonic diffuser,%3Dcalculate(a) inlet total pressure recovery with the shock atthe lip, i.e. the best backpressure da an obom(b) inlet total pressure recovery when the shock isinside the duct at A,/A, = 1.2, i.e. the super-critical mode%3D%3DM (6)(c) inlet total pressure recovery in subcritical0 mode with 10% spillage, i.e. Agpillage/A, = 0.1(d) flight dynamic pressure qo%3D

given; mach number(M)=1.86static pressure(P0)=30KPaspecific heat ratio of air (k)=1.4dynamic…

6.33 A normal-shock inlet operates in a Mach 1.86 stream with ambient static pressure of Po = 30 kPa. Neglecting total pressure loss in the subsonic diffuser, calculate %3D (a) inlet total pressure recovery with the shock at = the lip, i.e. the best backpressure (b) inlet total pressure recovery when the shock is inside the duct at A,/A, = 1.2, i.e. the super- critical mode da an ,obom %3D M (6 (c) inlet total pressure recovery in subcritical mode with 10% spillage, i.e. Agpillage/A1 = 0.1 (d) flight dynamic pressure qo %3D

6.33 A normal-shock inlet operates in a Mach 1.86 stream with ambient static pressure of Po = 30 kPa. Neglecting total pressure loss in the subsonic diffuser, calculate %3D (a) inlet total pressure recovery with the shock at = the lip, i.e. the best backpressure (b) inlet total pressure recovery when the shock is inside the duct at A,/A, = 1.2, i.e. the super- critical mode da an ,obom %3D M (6 (c) inlet total pressure recovery in subcritical mode with 10% spillage, i.e. Agpillage/A1 = 0.1 (d) flight dynamic pressure qo %3D

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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