Oblique Shock Interaction Experiments.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 29, 1969
- Accession Number
- AD0859847
Entities
People
- David L. Merritt
- Philip M. Aronson
Organizations
- Naval Ordnance Laboratory