Loss of directional stability in a post-stall flight environment has become a major design issue for future fighter aircraft. Numerous studies have addressed this issue, either from an aerodynamics perspective or through use of propulsive forces generated by vectoring exhaust nozzles. The X-29 aircraft, with its forward swept wing and other advanced technologies, suffers loss of directional power above 40 degrees angle of attack (AOA). An exploratory development program was undertaken on this configuration to regain the lost stability through use of a pneumatic system on the aircraft nose which influenced the external flow field, generating significant side forces useful for control. Wind tunnel test results were inserted into the X-29 flight simulator at NASA Dryden Flight Research Facility and the simulator was used to support a critical flight experiment of this technology. This experiment is the subject of this paper.
Flight Evaluation of Forebody Vortex Control in Post-Stall Flight
1995
10 pages
Report
No indication
English
Flight Evaluation of Forebody Vortex Control in Post-Stall Flight
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