Accession Number : AD0266701

Title :   WIND-TUNNEL INVESTIGATION OF PARAGLIDER MODELS AT SUPERSONIC SPEEDS

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s) : TAYLOR,ROBERT T.

Report Date : NOV 1961

Pagination or Media Count : 1

Abstract : An investigation was made in the Langley Unitary Plan wind tunnel to determine the behavior of paraglider models at moderate to high supersonic speeds. The models were deployed from a sting in the supersonic stream and steady-state aerodynamic performance data were obtained. Maximum values of the lift-drag ratio were about 1.4 at a Mach number of 2.65 and about 1.2 at a Mach number of 4.65. The angles of attack over which the models could be flown were limited by unsteady behavior of the canopy. (Author)

Descriptors :   *HYPERSONIC VEHICLES, *SUPERSONIC FLOW, *WINGS, AERODYNAMIC CHARACTERISTICS, DRAG, GLIDERS, LIFT, MEASUREMENT, MODEL TESTS, WIND TUNNEL MODELS, WIND TUNNELS

Distribution Statement : APPROVED FOR PUBLIC RELEASE