Published in AIAA Journal, Volume 38, Issue 3, March 1, 2000, pages 480-486.
Copyright © 2000 Stephen M. Ruffin, Anurag Gupta and David Marshall. Published by American Institute of Aeronautics and Astronautics, Inc.. The definitive version is available at http://dx.doi.org/10.2514/2.985.
NOTE: At the time of publication, the author David Marshall was not yet affiliated with Cal Poly.
A proof-of-concept study is performed for a supersonic channel-airfoil concept,which can be applied to the leading edges of wings, tails, fins, struts, and other appendages of aircraft, atmospheric entry vehicles, and missiles in supersonic flight. It is designed to be beneficial at conditions in which the leading edge is significantly blunted and the Mach number normal to the leading edge is supersonic.The supersonic channel-airfoil concept is found to result in significantly reduced wave drag and total drag (including skin-friction drag) and significantly increased lift/drag although maximum heat-transfer rate was increased for the geometries tested.