Accession Number : AD0606472

Title :   PRESSURES ON THE BLUNT PLATE WING AT SUPERSONIC AND HYPERSONIC SPEEDS,

Corporate Author : OHIO STATE UNIV RESEARCH FOUNDATION COLUMBUS AERODYNAMIC LAB

Personal Author(s) : Lee,John D.

Report Date : 11 JUL 1964

Pagination or Media Count : 36

Abstract : Over wide ranges in Mach number, sweep angle and attack angle, simple adjusted forms of Newtonian, Prandtl-Meyer, and blast wave theories may be used to accurately predict the pressure distributions on blunt-edged flat plates, in cluding the leading edge regions. On the leading edge, Newtonian-Prandtl-Meyer flow may be adjusted with an empirical factor to fit available experimental data. For the plate surface, the blast wave equation is modified by matching to the pressures at the cylinder-plate junction and on the infinite wedge, corresponding to the proper sweep and attack angle. (Author)

Descriptors :   (*BLUNT BODIES, AERODYNAMIC LOADING), (*SWEPT WINGS, AERODYNAMIC LOADING), PRESSURE, SUPERSONIC FLOW, HYPERSONIC FLOW, SURFACES, LOAD DISTRIBUTION, TWO DIMENSIONAL FLOW, DELTA WINGS, ANGLE OF ATTACK, CYLINDRICAL BODIES, ENTHALPY, AERODYNAMIC CHARACTERISTICS, NUMERICAL METHODS AND PROCEDURES, SHOCK (MECHANICS), MATHEMATICAL ANALYSIS

Distribution Statement : APPROVED FOR PUBLIC RELEASE