F-15 Model Internozzle Dynamic Pressure Acquisition.

摘要

A dynamic pressure survey of a 4.7-percent model of the F-15 aircraft was conducted during buffeting of F-15 afterbody nozzle in the NASA LaRC's 16- foot tunnel to obtain insight into the internozzle dynamic pressure phenomena germane to closely spaced engine installations. This test consisted of varying the Mach number from 0.48 to 1.2, the nozzle pressure ratio from 1 to 5, and the angle of attack from 0 to 6 degrees. These conditions were measured at six locations on the afterbody using strain gauge pressure transducers. It was determined that the measured data were broadband random, strongly stationary, and correlated.