LAMINAR SEPARATION IN SUPERSONIC AND HYPERSONIC FLOWS
Abstract
Static pressure, recovery temperature and heat transfer distributions were measured on flat plates with flaps at a Mach number of 2.02. A uniform amount of heat was dissipated at the surface of the models. The angle of the flaps was varied between 1.5 deg. and 21 deg. Laminar, transitional, and turbulent flows were considered. Well defined plateau pressures existed when reattachment was transitional and not in fully laminar flows. A large peak of recovery temperature existed, when transition was in the reattachment zone, followed by fairly low recovery temperatures. Heat transfer distributions were measured at a Mach number of 6.7 on a cone-cavity model with air injection into the separated flow region. The mass injection rate was varied between zero and a maximum equal to the mass flow in the boundary layer at separation. The effect of injection was to considerably reduce the heat transfer rate to the cavity floor and in the reattachment region of the flow. At an injection rate of about 0.25 at separation, the heat transfer was found to be reduced below the cone values over the whole surface of the body. At higher rates of injection, transition moved forward with correspondingly larger heat rates.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 30, 1966
- Accession Number
- AD0647819
Entities
People
- Jean J. Ginoux
Organizations
- von Kármán Institute for Fluid Dynamics