Author: Odell Morris

Publisher:

Published: 1962

Total Pages: 26

ISBN-13:

An investigation was conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.2 to determine the aerodynamic characteristics of several ring-wing--body configurations. This investigation included tests for the bodies alone and for the ring-wing--body combinations; these tests were conducted through an angle-of-attack range from about -4 to 11 degrees. The data indicated that sizable reductions in body wave drag were obtained for the concaveafterbody configuration as a result of the favorable interference produced by the ring wing. However, a large percentage of the total drag was produced by the ring wing and struts, and thus the ring-wing configurations of these tests appear to offer no drag advantage over a conventional wing-body configuration. Of the three configurations tested, the half-ring wing in combination with a body having a parabolic afterbody had the lowest drag (0.35) and the highest maximum liftdrag ratio (4.9).