Investigation of Drag Reduction by Boundary Layer Suction on a 72.5-deg Swept Wind at M 2 and 2.25

Download or read book Investigation of Drag Reduction by Boundary Layer Suction on a 72.5-deg Swept Wind at M 2 and 2.25 written by S. R. Pate and published by . This book was released on 1963 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in the 40-Inch Supersonic Tunnel (A) of the von Karman Gas Dynamics Facility to determine the effectiveness of boundary layer suction for laminar flow control on a two-dimensional, 72.5-deg swept wing having a subsonic leading edge. Test Mach numbers were 2 and 2.25 with a Reynolds number range based on wing chord from 3 to 14 million for angles of attack of 0.15, 0.45, and 0.75 deg. With suction, full chord laminar flow was maintained at M 2, alpha 0.15, 0.45, and 0.75 deg up to a length Reynolds number of approximately 9 million. At M 2.25 and alpha 0.15 deg, full chord lam inar flow was maintained up to a Reynolds number of 6.5 x 10 to the 6th power and for alpha 0.45 and 0.75 deg, up to a Reynolds number of 3 x 10 to the 6th power. Selected data are presented.