Multiple shock-shock interference on a cylindrical leading edge
- Resource Type
- Authors
- Allan R. Wieting
- Source
- AIAA Journal. 30:2073-2079
- Subject
- Physics
Shock wave
Leading edge
Hypersonic speed
business.industry
Astrophysics::High Energy Astrophysical Phenomena
Aerospace Engineering
Mechanics
Mach wave
Moving shock
Shock (mechanics)
Physics::Fluid Dynamics
symbols.namesake
Optics
Mach number
Bow wave
Physics::Space Physics
Shock diamond
symbols
Oblique shock
Supersonic speed
Bow shock (aerodynamics)
business
Shock tube
Astrophysics::Galaxy Astrophysics
- Language
- ISSN
- 1533-385X
0001-1452
The details of an experimental study of shock wave interference heating on a cylindrical leading edge representative of the cowl of a rectangular hypersonic engine inlet are presented. This Mach 8 study has provided the first detailed pressure and heat transfer rate distributions on a cylinder resulting from a two-dimensional shockwave interference pattern created by two incident oblique shock waves intersecting the cylinder bow shock wave. The peak heat transfer rate was 38 times the undisturbed flow stagnation point level and occurred when the two oblique shock waves coalesced prior to intersecting the cylinder bow shock wave. Development of pressure deflection diagrams identified a new interference pattern consisting of concomitant supersonic jets separated from each other by a shear layer and submerged in the subsonic region between the bow shock wave and body.