Wind-tunnel investigation of the forebody aerodynamics of a vortex-lift fighter configuration at high angles of attackResults 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.
Document ID
19890063987
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Banks, Daniel W. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1988
Subject Category
Aerodynamics
Report/Patent Number
SAE PAPER 881419
Meeting Information
Meeting: Aerospace Technology Conference and Exposition