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.
Wind-Tunnel Investigation of Paraglider Models at Supersonic Speeds
1961
18 pages
Report
No indication
English
Wind-tunnel investigation of paraglider models at supersonic speeds
Engineering Index Backfile | 1961
|Wind Tunnel Investigation of a Rigid Paraglider Reference Wing
Online Contents | 2015
|