Transonic Wind Tunnel Tests of a Base Drag Research Missile Model. Volume I.
CORNELL AERONAUTICAL LAB INC BUFFALO NY
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Tests were conducted in order to obtain data describing the effects of various simulated rocket exhaust plumes on the models external flow field. Data describing the flow in the nozzle exit plane and in the model boundary layer were also obtained. Model external static pressure measurements were made and Schlieren, shadowgraph and tuft photographs were taken. The tests were conducted at Mach numbers from 0.000 to 1.200 at angles of attack from -2 to 2 degrees. The report presents details of the test program, an outline of the test procedure and the results of the investigation in tabular form. Author
- Guided Missiles
- Fluid Mechanics