Investigation of Boundary-Layer Suction on a 20-Caliber Orgive Cylinder at Mach Numbers 2.5, 3.0, 3.5, and 4.0
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Report Number: AEDC TN 61-66
Author(s): Strike, W. T., Pate, S.
Corporate Author(s): VKF, ARO, Inc.
Date of Publication: 1961-06
Pages: 30
Contract: AF 40(600)-800
DoD Project: 1366
DoD Task: 14080
Identifier: AD0257381
Abstract:
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.
Provenance: IIT
Author(s): Strike, W. T., Pate, S.
Corporate Author(s): VKF, ARO, Inc.
Date of Publication: 1961-06
Pages: 30
Contract: AF 40(600)-800
DoD Project: 1366
DoD Task: 14080
Identifier: AD0257381
Abstract:
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.
Provenance: IIT