Accession Number : AD0282268

Title :   INVESTIGATION OF DRAG REDUCTION BY BOUNDARY-LAYER SUCTION ON A FLAT PLATE AND A 36-DEG SWEPT WING AT SUPERSONIC SPEEDS,

Corporate Author : ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE STATION TENN

Personal Author(s) : Pate ,S. R. ; Deitering,J. S.

Report Date : AUG 1962

Pagination or Media Count : 36

Abstract : Tests were conducted in a 40-in. supersonic tunnel to determine the effectiveness of boundary-layer suction for laminar flow control on a two-dimensional, biconvex, 36-degree swept wing and on a flat plate with and without shock impingement. Test Mach numbers were 2.5, 3, 3.5, and 4 with a Reynolds-number/in. range from 0.17 to 0.66 x 10 to the sixth power. With suction, full chord laminar flow was maintained on the flat plate at free stream Mach number of 2.5 and 3 at length Reynolds numbers of 22 and 26.5 x 10 to the sixth power, respectively, which resulted in a total drag reduction of 77 and 74%. With suction and shock impingement across the plate resulting from a 1-degree shock generator angle, full chord laminar flow was maintained at free stream Mach number of 2.5, 3, and 3.5 at length Reynolds numbers of 19.7, 18.9, and 21.7 x 10 to the sixth power, respectively. On the 36-degree swept wing, full chord laminar flow was maintained with suction up to a length Reynolds number of 11.3 x 10 to the sixth power at free stream Mach number of 3. (Author)

Descriptors :   *LAMINAR BOUNDARY LAYER, *SHEETS, *SWEPTBACK WINGS, AERODYNAMIC CHARACTERISTICS, AERODYNAMIC CONFIGURATIONS, AREA SUCTION, BOUNDARY LAYER CONTROL, CONTROL, DRAG, EFFECTIVENESS, METAL PLATES, MODEL TESTS, SHOCK WAVES, SUPERSONIC FLOW, TEST EQUIPMENT, TEST METHODS, TURBULENT BOUNDARY LAYER, WIND TUNNEL MODELS

Distribution Statement : APPROVED FOR PUBLIC RELEASE