Investigation of drag reduction by boundary layer suction on a 50-deg swept tapered wing at M (free-stream) = 2.5 to 4 /

Tests were conducted in the 40-in. supersonic Tunnel A of the von Karman Gas Dynamics Facility to determine the effectiveness of boundary layer suction for laminar flow control on a tapered, three-dimensional, 50-deg swept supersonic wing. Test Mach numbers were 2.5, 3, 3.5, and 4 with a Reynolds number range (based on boundary-layer rake location) from 4.3 to 19.5 million for angles of attack of zero and =3 deg. Wake drag, suction drag, and total drag coefficients and the corresponding suction coefficients are presented, along with fully turbulent wake drag coefficients for the no-suction case."October 1964."Includes bibliographic references (page 8).Tests were conducted in the 40-in. supersonic Tunnel A of the von Karman Gas Dynamics Facility to determine the effectiveness of boundary layer suction for laminar flow control on a tapered, three-dimensional, 50-deg swept supersonic wing. Test Mach numbers were 2.5, 3, 3.5, and 4 with a Reynolds number range (based on boundary-layer rake location) from 4.3 to 19.5 million for angles of attack of zero and =3 deg. Wake drag, suction drag, and total drag coefficients and the corresponding suction coefficients are presented, along with fully turbulent wake drag coefficients for the no-suction case.Report prepared by ARO, Inc., under Air Force Contract No.Mode of access: Internet