INVESTIGATION OF BOUNDARY-LAYER SUCTION ON A 20-CALIBER OGIVE CYLINDER AT MACH NUMBERS 2.5, 3.0, 3.5, AND 4.0
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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A second investigation was conducted in the 12in., intermittent, supersonic wind tunnel of the von Karman Gas Dynamics Facility to measure the effectiveness of boundary-layer suction on a 20 caliber ogive cylinder. The application of suction type boundary-layer control on the ogive was investigated at Mach numbers 2.5, 3.0, 3.5, and 4.0 over a unit Reynolds number range from 0. 07 to 1.03 x 10 to the 6th power per inch with the model at zero angle of attack. Some additional data were obtained at 2-deg angle of attack at Mach number 3. As a result of improving the design of the suction system a significant gain was made in reducing the net drag of the model at Mach number 3 by boundary-layer suction. The presence of the suction slots with no suction when compared with the sealed slot configuration that is, smooth model had some influence on the boundary-layer characteristics at all Mach numbers.
- Fluid Mechanics