Oil Flow Studies of Base Separation at Supersonic Speeds.
BALLISTIC RESEARCH LABS ABERDEEN PROVING GROUND MD
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Oil flow visualization tests were conducted on the base of a 10-degree half-angle cone model at Mach numbers 1.75 to 4.0. The cone was supported by a strut from the cone surface to the wind tunnel floor. Previous tests on a sting supported cone showed separation to occur on the cone base at distances on the order of 15 of the base radius from the trailing edge corner. Results of this test program show that separation occurs at slightly greater distances from the corner than for the sting supported model also, the separation line was irregular indicating large asymmetries in the base flow even though the model was at zero degrees attitude. Author
- Fluid Mechanics