Wind-tunnel free-flight tests have been conducted in the Langley 30- by 60-Foot Wind Tunnel to examine the high-angle-of-attack stability and control characteristics and control law design of a supersonic persistence fighter (SSPF) at 1 g flight conditions. In addition to conventional control surfaces, the SSPF incorporated deflectable wingtips (tiperons) and pitch and yaw thrust vectoring. A direct eigenstructure assignment technique was used to design control laws to provide good flying characteristics well into the poststall angle-of-attack region. Free-flight tests indicated that it was possible to blend effectively conventional and unconventional control surfaces to achieve good flying characteristics well into the poststall angle-of-attack region.
Wind-Tunnel Free-Flight Investigation of a Supersonic Persistence Fighter
1993
63 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft , Aircraft stability , Control surfaces , Control systems design , Fighter aircraft , Flight characteristics , Free flight , Supersonic aircraft , Wind tunnel stability tests , Wing tips , Angle of attack , Control theory , Dynamic stability , Lateral stability , Longitudinal stability , Thrust vector control , Yaw