The effect of shock impingement on the blunt leading edge of the inlet cowl of a scramjet engine is investigated numerically. The impinging shock is caused by the vehicle forebody. The interaction of this forebody shock with the cowl leading edge shock results in a very complex flowfield containing local regions of high pressure and intense heating. In the present investigation, this complex flowfield is calculated by solving the full Navier-Stokes equations using a finite-volume flux splitting technique due to Van Leer. Results are also obtained for the downstream effects into the inlet of the leading edge shock-shock interactions. Results of the present numerical investigation are compared with available experimental results.
Influence of shock-shock interactions on the blunt body flow field at hypersonic flight speeds
AIAA Applied Aerodynamics Conference ; 1989 ; Seattle, WA, United States
1989-01-01
Conference paper
No indication
English
Hypersonic Type-IV Shock/Shock Interactions on a Blunt Body with Forward-Facing Cavity
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