Results of a recent low-speed wind-tunnel investigation conducted to define the forebody flow on a 16-percent scale model of the NASA High Angle-of-Attack Research Vehicle, an F-18 configuration, are presented with analysis. Measurements include force and moment data, oil-flow visualizations, and surface pressure data taken at angles of attack near and above maximum lift (36 to 52 deg) at a Reynolds number of one million (based on mean aerodynamic chord). The results presented identify the key flow-field features on the forebody including the wing-body strake.
Wind-tunnel investigation of the forebody aerodynamics of a vortex-lift fighter configuration at high angles of attack
Aerospace Technology Conference and Exposition ; 1988 ; Anaheim, CA, United States
1988-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
SAE Technical Papers | 1988
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