Publisher's Synopsis
A supersonic wind tunnel investigation was conducted in the NASA Langley Unitary Plan Wind Tunnel on an advanced derivative configuration of the United States Air Force F-16 fighter. Longitudinal and lateral directional force and moment data were obtained at Mach numbers of 1.60 to 2.16 to evaluate basic performance parameters and control effectiveness. The aerodynamic characteristics for the F-16 derivative model were compared with the data obtained for the F-16C model and also with a previously tested generic wing model that features an identical plan form shape and similar twist distribution. Fox, Mike C. and Forrest, Dana K. Langley Research Center AERODYNAMIC CHARACTERISTICS; AIRCRAFT CONFIGURATIONS; AIRCRAFT MODELS; DELTA WINGS; F-16 AIRCRAFT; MACH NUMBER; WIND TUNNEL MODELS; WIND TUNNEL TESTS; CONTROLLABILITY; SUPERSONIC WIND TUNNELS...
