Accession Number : ADB085898
Title : AFWAL Advanced STOL Nozzle Test Results at Mach Numbers from 0.6 to 1.5.
Descriptive Note : Final rept. 11 Mar-7 Apr 82,
Corporate Author : ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
Personal Author(s) : Smith,C. L.
Report Date : JUN 1982
Pagination or Media Count : 56
Abstract : Wind tunnel data were obtained on a 1/8-scale model of an advanced fighter aircraft to measure the effect of simulated jet plumes from various advanced nozzles on the highly integrated airframe. Aerodynamic forces and thrust loads were measured on the entire model, excluding the vertical tail which was used to support the model. Wind surface pressure data were simultaneously obtained at selected test conditions. Four axisymmetric and nonaxisymmetric nozzle designs were tested in various configurations including afterburner and nonafterburner power settings and nozzle deflection angles up to 20 deg. High-pressure air was used to simulate exhaust plumes at nozzle pressure ratios up to 13 while model angle of attack varied from 0 to 10 deg. Free-stream test conditions included Mach numbers from 0.6 to 1.5 at a constant unit Reynolds number of 2.0 x million/ft. (Author)
Descriptors : *Exhaust nozzles, Axisymmetric, Deflection, Jet engine exhaust, Exhaust plumes, Jet flow, Aerodynamic forces, Coefficients, Afterburning, Thrust, Wind tunnel tests, Wings, Pressure distribution, Surface properties, Transonic characteristics, Supersonic characteristics, Short takeoff aircraft, Thrust vector control systems, Angle of attack, Wind tunnel models, Jet fighters
Subject Categories : Aerodynamics
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE