Accession Number : AD0450195


Title :   INVESTIGATION OF DRAG REDUCTION BY BOUNDARYLAYER SUCTION ON A 50-DEGREE SWEPT TAPERED WING AT M (FREE-STREAM) EQUALS 2.5 TO 4


Corporate Author : ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN


Personal Author(s) : Pate, S R


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/450195.pdf


Report Date : Oct 1964


Pagination or Media Count : 30


Abstract : Tests were conducted in the 40-in. supersonic Tunnel A of the von Karman Gas Dynamics Facility to determine the effectiveness of boundarylayer 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.


Descriptors :   *SWEPTBACK WINGS , ANGLE OF ATTACK , BOUNDARY LAYER , DRAG , INSTRUMENTATION , LAMINAR FLOW , MODEL TESTS , REYNOLDS NUMBER , SUPERSONIC CHARACTERISTICS , TURBULENCE , WAKE , WIND TUNNEL MODELS


Subject Categories : Aircraft
      Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE