Comparisons Between Experiment and an Approximate Transonic Calculative Method.
ARMY MISSILE COMMAND REDSTONE ARSENAL ALA AEROBALLISTICS DIRECTORATE
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TICS DIRECTORATEComparisons Between Experiment and an Approximate Transonic Calculative Method.Technical rept.,Spring,Donald J. RD-73-34DA-1-M-262303-A-214Artillery rockets, Model tests, Ogives, Wind tunnel models, Rocket exhaust, Transonic characteristics, Flow fieldsA method has been developed by Wu and Aoyama 1 to predict the surface pressures over tangent ogive bodies at zero angle of attack. To verify the usefulness and the accuracy of the method, an experimental program was conducted over the Mach number range between 0.7 and 1.2. The data obtained during the test program are in the form of pressure coefficients and are presented as plots of surface pressure distribution over the body. Modified author abstract
- Fluid Mechanics