Accession Number : AD0682956

Title :   PRESSURE DISTRIBUTION ON A 5.6 DEGREE BLUNT CONE AT MACH 14.

Descriptive Note : Final rept.,

Corporate Author : AEROSPACE RESEARCH LABS WRIGHT-PATTERSON AFB OHIO

Personal Author(s) : Friberg,Eric G.

Report Date : NOV 1968

Pagination or Media Count : 77

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)

Descriptors :   (*CONICAL BODIES, HYPERSONIC CHARACTERISTICS), (*BLUNT BODIES, PRESSURE), DISTRIBUTION, REYNOLDS NUMBER, ANGLE OF ATTACK, INTERACTIONS, CORRELATION TECHNIQUES, VISCOSITY, PITCH(MOTION), MOMENTS

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE