COMMUNICATION BETWEEN BASE AND LEEWARD REGION OF A CONE AT ANGLE OF ATTACK IN A HYPERSONIC FLOW.
Abstract
The results of a wind tunnel investigation of separated flow over a 5.6 degree half-angle cone at angle of attack are presented. Surface pressure and oil flow data were obtained at a free stream Mach number of 14.2 and a free stream Reynolds number per foot of 650,000. It was observed that separated flow on the cone at angle of attack occurred while the cone leeward pressures were significantly larger than the base pressure. This large pressure difference indicated there was no subsonic communication between base and leeward region. The separated flow field for this case was then analogous to that of an infinitely long cone. At angles of attack greater than that which was required to equalize base and leeward pressures a new flow feature was observed. The cone leeward flow expanded to pressure levels below base pressure. A secondary separation occurred on the rear portion of the cone leeward surface, which appeared to contain subsonic reverse flow. In the neighborhood of this secondary separation, the leeward surface pressures increased and the separation line moved further away from the leeward meridian. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1969
- Accession Number
- AD0696584
Entities
People
- Eric G. Friberg
- Kenneth F. Stetson
Organizations
- Air Force Research Laboratory