An Experimental Investigation of the Effects of a Blast Wave on a Vehicle in a Supersonic Flow
CORNELL AERONAUTICAL LAB INC BUFFALO NY
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A test was conducted to determine the effects of a blast wave on a delta-wing model in a supersonic flow M equals approximately 2. Pressure data were taken at various locations on the model using fast-response pressure transducers. The blast wave was generated by the detonation of a small explosive charge at the apex of a hollow cone normal to the flow direction. The variables of the test were model attitude relative to the charge and simulated altitude. This report presents details of the facility, blast generator and model, describes the development of instrumentation, and presents the results of the tests.
- Fluid Mechanics