Accession Number : AD0883047

Title :   Shock Interaction Surface Pressures for Hemispherical and Conical Bodies,

Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s) : Baltakis, Frank P.

Report Date : 16 FEB 1971

Pagination or Media Count : 118

Abstract : Transient pressures, induced by wind-tunnel simulated head-on blast wave interactions, have been measured on a hemisphere and on cones of 9-, 15- and 30-degree semivertex angles. Blast wave Mach numbers of 1.6 to 2.2, 2.2 to 5.85 and 2.7 to 4.4 were simulated at the free-stream Mach numbers of 3.1, 5.1 and 7, respectively. Measured pressure-time histories for the hemisphere were compared and found in agreement with histories predicted by McNamara's FLAME code. Peak overpressures for the cones were tested for agreement with values predicted by a simple theoretical method in which an assumption is made that the blast wave forms a Mach stem moving along the surface at a velocity whose axial component equals the velocity of the main blast wave. The effects of angle of attack and of nose blunting were also investigated with the nine-degree cone at a free-stream Mach number of 5.1. (Author)

Descriptors :   (*GUIDED MISSILE WARHEADS, BLAST), (*REENTRY VEHICLES, NUCLEAR EXPLOSIONS), MATHEMATICAL MODELS, SUPERSONIC CHARACTERISTICS, HYPERSONIC CHARACTERISTICS, WIND TUNNEL MODELS, NOSE CONES, SIMULATION, SHOCK WAVES, COMPUTER PROGRAMMING, HEMISPHERICAL SHELLS, CONICAL BODIES, STAGNATION POINT, BLUNT BODIES.

Subject Categories : Guided Missile Reentry Vehicles

Distribution Statement : APPROVED FOR PUBLIC RELEASE