Evaluation of Wind Tunnel Nozzle Afterbody Test Techniques Utilizing a Modern Twin Engine Fighter Geometry at Mach Numbers from 0.6 to 1.2

摘要

Analyses of surface pressure data from wind tunnel tests conducted in the Propulsion Wind Tunnel (16T) on the 0.1- and 0.2-scale models of the YF-17 aircraft and flight tests conducted at the NASA Dryden Flight Research Center with the prototype YF-17 were conducted to substantiate the effectiveness of the subscale wind tunnel test techniques currently used at AEDC to provide data to evaluate throttle-dependent effects. The data were obtained at Mach numbers 0.6, 0.9, and 1.2 at characteristic Reynold numbers based on fuselage length from 14 million to 250 million. The data obtained at Mach numbers 0.6 and 0.9 indicate that valid techniques are available to obtain subscale wind tunnel data that are directly applicable to aft-end throttle-dependent flight performance prediction. The wind tunnel plume simulation techniques, however, do not provide data for directly predicting the flight vehicle, aft-end, calculated loads at Mach number 1.2. Additional corrections must be applied to the data to compensate for temperature effects associated with afterburning operations, such as that encountered at Mach 1.2. (Author)