Accession Number : AD0859847

Title :   Oblique Shock Interaction Experiments.

Descriptive Note : Final rept.,

Corporate Author : NAVAL ORDNANCE LAB WHITE OAK MD

Personal Author(s) : Merritt, David L. ; Aronson, Philip M.

Report Date : 29 MAY 1969

Pagination or Media Count : 125

Abstract : A description is given of a unique experimental technique for simulating the interaction between a re-entry vehicle and an oblique blast wave. The technique combines a ballistics range with a shocktube. Models fly down the range and through the shocktube at an oblique angle. As a model passes through the shocktube, it intercepts a plane shock wave moving down the tube. Sequential photographs show the interaction between the model and the shock wave. Experiments were done with 9- and 15-degree half-angle cone models. The Mach numbers of both the models and the shock waves ranged from 2 to 5. The peak transient pressure on the model resulting from the reflection of the shock wave was calculated using data measured from the photographs. The analysis technique was verified by direct measurements of reflected shock pressures on a stationary cone model. (Author)

Descriptors :   (*NUCLEAR EXPLOSIONS, REENTRY VEHICLES), (*REENTRY VEHICLES, SHOCK WAVES), SHOCK TUBES, SIMULATION, ATMOSPHERE ENTRY, CONICAL BODIES, MODEL TESTS, INTERACTIONS, SUPERSONIC CHARACTERISTICS, HYPERSONIC CHARACTERISTICS, PRESSURE, ANGLE OF ATTACK.

Subject Categories : Guided Missile Reentry Vehicles
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE