AEROSPACE 410

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AEROSPACE 410 AEROSPACE PROPULSION Lecture
( ) SUPERSONIC INTAKES FOR PROPULSION SYSTEMS
part-a

Dr. Cengiz Camci
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Normal shock relations
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OBLIQUE SHOCK ANGLE In function of deflection and
upstream Mach number
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Stagnation pressure ratio across an oblique shock
wave
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EXIT MACH NUMBER OBLIQUE SHOCK
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