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
Technical rept. 1 Jan-30 Jun 1968
AVCO GOVERNMENT PRODUCTS GROUP WILMINGTON MA AVCO MISSILE SYSTEMS DIV
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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 XR sub N in the range of 13.5 to 27.5 indicated that bluntness did not significantly affect separation in this range of XR sub N. When XR 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.
- Test Facilities, Equipment and Methods
- Fluid Mechanics