Design and experimental verification of an equivalent forebody representation of flowing inlets
| Autor: | David S. Miller, Check M. Louie, Davy A. Haynes, John R. Klein |
|---|---|
| Rok vydání: | 1989 |
| Předmět: |
Flow visualization
Engineering Supersonic wind tunnel geography geography.geographical_feature_category business.industry Flow (psychology) Aerospace Engineering Mechanics Structural engineering Inlet Physics::Fluid Dynamics symbols.namesake Mach number Range (aeronautics) symbols business Choked flow Wind tunnel |
| Zdroj: | Journal of Aircraft. 26:1059-1066 |
| ISSN: | 1533-3868 0021-8669 |
| DOI: | 10.2514/3.45881 |
| Popis: | A 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 1.6-2.16 for angles of attack of -4-16 deg. Test results show that, for the purposes considered here, the equivalent forebody simulates the original flowfield disturbances to an acceptable degree of accuracy. |
| Databáze: | OpenAIRE |
| Externí odkaz: |
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