1993•Unpublished venueRequires access

Supersonic Aerodynamic Characteristics of an Advanced F-16 Derivative Aircraft Configuration

C Fox Mike, K Forrest Dana

Abstract

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 planform shape and similar twist distribution.

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Key concepts: Supersonic speed, Aerodynamics, Wind tunnel, Mach number, Supersonic wind tunnel, Derivative (finance), Angle of attack, Aerospace engineering