LAMINAR, TRANSITIONAL AND TURBULENT FLOW WITH ADVERSE PRESSURE GRADIENT ON A CONE-FLARE AT MACH 10.
Abstract
An experimental investigation of the boundary layer on a cone-flare body at Mach 10 is presented. Measurements of pressure, heat transfer and boundary layer thickness are made in regions of zero and adverse pressure gradient. Several noses are fitted to the cone to produce blunted cone-flares, which are used to study separation. The experimental results are compared to some recent analytical investigations. The results showed a small amount of blunting can lower the Reynolds number sufficiently to produce separation. The experiment results also showed that a small amount of crossflow (produced by placing the model at small angles of attack) was capable of eliminating separation.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1965
- Accession Number
- AD0629094
Entities
People
- Alan Bos
- Paul F. Jensen Jr.
- Victor Zakkay
Organizations
- New York University