Flight tests were performed on an extensively instrumented F-5A aircraft to investigate the dynamic buffet pressure distribution on the wing surfaces and the responses during a series of transonic maneuvers called wind-up turns. The maneuvers to maximum lift were performed at three Mach number-altitude combinations. The fluctuating buffet pressure data at 24 stations on the right wing of the F-5A were acquired by miniaturized semiconductor-type pressure transducers flush-mounted on the wing. The data acquired in this manner were found adequate to trace the shock origin, the movement of the shock front, and the development of the separated flow (shock-induced or leading edge-induced) on the wing surface during the transonic maneuver corresponding to various flap settings. Specifically, the transonic maneuver was a transient behavior where the pressure and response data were nonstationary in nature. To simulate the aircraft behavior, a mathematical model was created representing a multimodal system excited by nonstationary random forces.
Transonic Buffet Behaviour of Northrop F-5A Aircraft
1974
33 pages
Report
No indication
English
Transonic buffet behavior of Northrop F-5A aircraft
TIBKAT | 1974
|Transonic buffet behavior of Northrop F-5A aircraft
AIAA | 1975
|Transonic buffet behavior of Northrop F-5A aircraft
NTRS | 1974
|Transonic buffet behavior of Northrop F-5A aircraft
NTRS | 1975
|