Investigation of Boundary-Layer Suction on a 20-Caliber Orgive Cylinder at Mach Numbers 2.5, 3.0, 3.5, and 4.0

Item

Title
Investigation of Boundary-Layer Suction on a 20-Caliber Orgive Cylinder at Mach Numbers 2.5, 3.0, 3.5, and 4.0
Date
1961
Index Abstract
Coming Soon
Photo Quality
Incomplete
Report Number
AEDC TN 61-66
Creator
Strike, W. T.
Pate, S.
Corporate Author
VKF, ARO, Inc.
Extent
30
Identifier
AD0257381
Distribution Classification
1
Contract
AF 40(600)-800
DoD Project
1366
DoD Task
14080
DTIC Record Exists
Yes
Distribution Change Authority Correspondence
None
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.
Report Availability
Full text available by request
Date Issued
1961-06
Publisher
Arnold Air Force Station, TN : Arnold Engineering Development Center, Air Force Systems Command, USAF
Provenance
IIT
Type
report
Format
30 pages ; 28 cm.