SHOCK-SHOCK INTERACTION INSIDE THE MACH REFLECTION REGION FOR SLENDER SUPERSONIC BODIES,
Abstract
The transient pressure field produced behind a plane shock wave of arbitrary strength; which encounters (1) a thin supersonic wedge head-on, (2) a thin supersonic wedge yawed with respect to the plane shock wave, and (3) a slender supersonic cone head-on, is theoretically predicted where the intersection of the plane shock wave with the body bow shock occurs completely inside the Mach reflection region. Previous theoretical works have treated the cases where the intersection of the plane shock wave with the body bow shock occurs outside the Mach reflection region. The present analysis which utilizes a conical flow technique and conformal transformation treats small vertex angles (to ensure Mach reflection at the surface) and to inviscid flow. The small pressure perturbations that the thin wedges and slender cone create are determined. Ratios of the maximum transient pressure compared to the new steady state pressure on the surface of either cone or wedge are found to exceed unity. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1965
- Accession Number
- AD0626033
Entities
People
- Adolf Busemann
- Victor D. Blankenship
Organizations
- The Aerospace Corporation