Abstract
Wind-tunnel tests to measure buffeting flow characteristics and dynamic wing response on a 10% scale model of the F-4 airplane have provided an empirical basis for the prediction of transonic buffet pressure distribution on high performance fighter wings. Angle-of-attack and Mach number were primary variables in the test that incorporated wide-band pressure transducers, accelerometers, and strain gages. Sensor arrangement indicated the'nature of pressures at discrete points and also the correlation between pressures at different locations. Data were compared with full scale flight measurements, and results include root mean square pressure distributions as well as spectral characteristics.
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