Accession Number : AD0615904

Title :   HYPERSONIC FLOW FIELD ABOUT A BLUNT NOSED CONE AT ANGLE OF ATTACK: PHASE II,

Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB

Personal Author(s) : Polutchko,Robert J. ; Hultgren,Bror O.

Report Date : DEC 1964

Pagination or Media Count : 62

Abstract : The report describes Phase II of an experimental research program to investigate the flow fields about blunt nosed wings and bodies at angle of attack. Phase II is an investigation of the inviscid three-dimensional flow field about a truncated 10 degree half-angle cone at Mach numbers of 4.07 and 7.6 and angles of attack up to 20 degrees. By traversing the flow between the body and the bow shock with a conical probe at various cross-flow planes the thermodynamic state variable and Mach number profiles are established for each angle of attack. Schlieren photographs of vertical meridian shock wave shapes were taken. Estimates of the three-dimensional shock locus are included. (Author)

Descriptors :   (*HYPERSONIC FLOW, NOSE CONES), (*NOSE CONES, HYPERSONIC FLOW), BLUNT BODIES, SHOCK WAVES, ANGLE OF ATTACK, WINGS, THERMODYNAMICS, SCHLIEREN PHOTOGRAPHY, PRESSURE, AERODYNAMIC LOADING, GRAPHICS

Distribution Statement : APPROVED FOR PUBLIC RELEASE