Accession Number : AD0863758

Title :   Measurements of Blast-Induced Transient Pressures at the Base of a Cone in Supersonic Flow,

Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s) : Baltakis, Frank P. ; Senechal, Gary D.

Report Date : 05 NOV 1969

Pagination or Media Count : 63

Abstract : Transient pressures, induced by a head-on blast wave, were measured at the base of a nine-degree half-angle cone in a supersonic stream using a wind-tunnel shocktube technique. Tests were conducted at free-stream Mach numbers of 3, 5 and 6.5 and at blast wave Mach numbers of 1.5 to 3, 2 to 5 and 4 to 8 at free-stream Mach numbers of 3, 5 and 6.5, respectively. Within the range of this experiment, shock-induced base pressure was found to increase approximately in proportion to the blast wave Mach number squared. When expressed in ratio to the free-stream static pressure, the induced base pressure was found to decrease, approximately, linearly with increasing free-stream Mach number. At the free-stream/blast wave Mach number conditions of 3/3, 5/5 and 6.5/8 the respective induced base pressure to initial free-stream static pressure ratios were 5, 8 and 18. (Author)

Descriptors :   (*NUCLEAR EXPLOSIONS, REENTRY VEHICLES), (*REENTRY VEHICLES, SHOCK WAVES), (*CONICAL BODIES, BASE PRESSURE), BASE FLOW, BLAST, WIND TUNNEL MODELS, MODEL TESTS, SUPERSONIC CHARACTERISTICS, ANGLE OF ATTACK.

Subject Categories : Guided Missile Reentry Vehicles
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE