Accession Number : AD0615008

Title :   HYPERSONIC FLOW FIELD ABOUT A BLUNT SLAB WING AT ANGLE OF ATTACK: PHASE I,

Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB

Personal Author(s) : Polutchko,Robert J.

Report Date : DEC 1964

Pagination or Media Count : 111

Abstract : This report describes an experimental research program to investigate the flow fields about blunt nosed wings and bodies at angle of attack. Phase I is an investigation of the inviscid two-dimensional flow field about a blunt nosed flat plate and a larger transverse cylinger-plate at a Mach number of 7.6 and angles of attack up to 40 degrees. By traversing the flow between the wing and the bow shock at various chordwise stations with a pitot probe, the streamline patterns and the flow property variations along them are established for each angle of attack. Also included are schlieren photographs of the shock wave shapes, estimates of the boundary layer thicknesses, and the results of a brief investigation to determine the feasibility or an experimental method of sonic line location. (Author)

Descriptors :   (*HYPERSONIC FLOW, BLUNT BODIES), (*BLUNT BODIES, HYPERSONIC FLOW), WING BODY CONFIGURATIONS, AERODYNAMIC CHARACTERISTICS, ANGLE OF ATTACK, TWO DIMENSIONAL FLOW, SHOCK WAVES, BOUNDARY LAYER, THICKNESS, SCHLIEREN PHOTOGRAPHY, FLOW VISUALIZATION, FLAT PLATE MODELS

Distribution Statement : APPROVED FOR PUBLIC RELEASE