Large-scale wind-tunnel investigation of a close-coupled canard-delta-wing fighter model through high angles of attackData obtained through very high angles of attack from a large-scale, subsonic wind-tunnel test of a close-coupled canard-delta-wing fighter model are analyzed. The canard delays wing leading-edge vortex breakdown, even for angles of attack at which the canard is completely stalled. A vortex-lattice method was applied which gave good predictions of lift and pitching moment up to an angle of attack of about 20 deg, where vortex-breakdown effects on performance become significant. Pitch-control inputs generally retain full effectiveness up to the angle of attack of maximum lift, beyond which, effectiveness drops off rapidly. A high-angle-of-attack prediction method gives good estimates of lift and drag for the completely stalled aircraft. Roll asymmetry observed at zero sideslip is apparently caused by an asymmetry in the model support structure.
Document ID
19830067155
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Stoll, F. (NASA Ames Research Center Moffett Field, CA, United States)
Koenig, D. G. (NASA Ames Research Center Moffett Field, CA, United States)