Flight tests were performed on an 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 conditions under which the tests were conducted are defined. The fluctuating buffet pressure data on the right wing of the aircraft were acquired by miniaturized semiconductor-type pressure transducers flush mounted on the wing. Processing of the fluctuating pressures and responses included the generation of the auto- and cross-power spectra, and of the spatial correlation functions. An analytical correlation procedure was introduced to compute the aircraft response spectra based on the measured buffet pressures.
Transonic buffet behavior of Northrop F-5A aircraft
1974-09-01
Report
Keine Angabe
Englisch
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 | 1975
|Transonic Buffet Behaviour of Northrop F-5A Aircraft
NTIS | 1974
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