Design and experimental verification of an equivalent forebody to produce disturbances equivalent to those of a forebody with flowing inletsA method by which a simple equivalent faired body can be designed to replace a more complex body with flowing inlets has been demonstrated for supersonic flow. An analytically defined, geometrically simple faired inlet forebody has been designed using a linear potential code to generate flow perturbations equivalent to those produced by a much more complex forebody with inlets. An equivalent forebody wind-tunnel model was fabricated and a test was conducted in NASA Langley Research Center's Unitary Plan Wind Tunnel. The test Mach number range was 1.60 to 2.16 for angles of attack of -4 to 16 deg. Test results indicate that, for the purposes considered here, the equivalent forebody simulates the original flowfield disturbances to an acceptable degree of accuracy.
Document ID
19880034916
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Haynes, Davy A. (NASA Langley Research Center Hampton, VA, United States)
Miller, David S. (NASA Langley Research Center Hampton, VA, United States)
Klein, John R. (NASA Langley Research Center Hampton, VA, United States)
Louie, Check M. (McDonnell Aircraft Co. Saint Louis, MO, United States)