PRESSURE DISTRIBUTION ON A 5.6 DEGREE BLUNT CONE AT MACH 14.
Abstract
The pressure distribution around a 5.6 deg half-angle cone with various nose bluntness ratios was measured in a 20-inch hypersonic wind tunnel at Mach 14 and Re 160,000. An empirical expression for the circumferential pressure distribution at small angles of attack is derived which allows the integration of normal pressure components in closed form. Correlation of the pressure data along the most windward ray at angle of attack by means of the tangent cone concept is shown to be possible if viscous interaction is negligible. For the most windward ray of the 5.6 deg cone this is the case for positive angles of attack only. At negative angles of attack the viscous effects dominate and prevent the correlation. The pitching moment derivative was calculated for several noses on the basis of the measured pressure distributions at angles of attack. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1968
- Accession Number
- AD0682956
Entities
People
- Eric G. Friberg
Organizations
- Air Force Research Laboratory