REST SEMIANNUAL PROGRESS REPORT 1 JANUARY - 30 JUNE 1968. VOLUME 3. A SHOCK TUNNEL INVESTIGATION OF HYPERSONIC LAMINAR BOUNDARY LAYER SEPARATION ON A 15-DEGREE CONE AT ANGLE OF ATTACK
Abstract
A shock tunnel investigation of the pressure and heat transfer distributions on sharp and blunted 15-degree half angle cones at angle of attack was conducted. The test conditions were M infinity = 13.5 and Re infinity = 1.5 x1,000,000. Separation on a sharp cone with increasing angle of attack is a gradual process which is characterized by increasing heat transfer rates while the pressure is decreasing. The two base geometries tested (flat and spherical) indicated that separation was not influenced to a significant degree by base geometry. Limited experiments with X/R sub N in the range of 13.5 to 27.5 indicated that bluntness did not significantly affect separation in this range of X/R sub N. When X/R sub N was in the range of 2.1 to 6.4 there was no indication of separation at angles of attack up to 18 degrees.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1968
- Accession Number
- AD0842009
Entities
People
- Kenneth F. Stetson