Investigation of Drag Reduction by Boundarylayer Suction on a 50-degree Swept Tapered Wing at M (free-stream) Equals 2.5 to 4

Download or read book Investigation of Drag Reduction by Boundarylayer Suction on a 50-degree Swept Tapered Wing at M (free-stream) Equals 2.5 to 4 written by S. R. Pate and published by . This book was released on 1964 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.