Simulations of a Low-Boom, Axisymmetric, External Compression Inlet
| Autor: | D. Davis, Eric Loth, Timothy R. Conners, Donald C. Howe, T. Coyne, J. Koncsek |
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| Rok vydání: | 2009 |
| Předmět: |
020301 aerospace & aeronautics
Supersonic wind tunnel geography Materials science geography.geographical_feature_category Shock (fluid dynamics) Rotational symmetry Aerospace Engineering 02 engineering and technology Mechanics Compression (physics) Inlet 01 natural sciences Boom 010305 fluids & plasmas Diffuser (thermodynamics) symbols.namesake 0203 mechanical engineering Mach number 0103 physical sciences symbols Oblique shock Supersonic speed Stagnation pressure Geology |
| Zdroj: | 39th AIAA Fluid Dynamics Conference. |
| DOI: | 10.2514/6.2009-4210 |
| Popis: | Computational simulations have been used to study a new low-boom, axisymmetric, external compression supersonic inlet with an on-design Mach number of 1·7. The inlet incorporates a relaxed compression surface with a near-zero cowl angle to help reduce external oblique shock waves due to spillage and cowl geometry. To reduce mechanical complexity the inlet is designed with zero-bleed. To understand the impact on performance and shock overpressure caused by the inlet itself, several throat and diffuser designs were simulated. The computations utilised a Reynolds-averaged Navier-Stokes code. Inflow properties were held consistent with the operational characteristics of the NASA GRC 8′ × 6′ Supersonic Wind Tunnel (SWT) for experimental testing of the inlet of Mach 1·67 at a Reynolds number of 5·4 × 106. Stagnation pressure recovery performance for the baseline condition exceeded 94% at design mass flow rates, and reduced only slightly with increases in Mach number (consistent with theoretical predictions) and extension of cowl position. The simulations also showed that the relaxed compression surface combined with the near-zero cowl angle helps to significantly reduce external oblique shocks This is partly due to the reduced inlet spillage in combination with a reduced overall turning angle placed on the free-stream flow relative to the cowl shape. |
| Databáze: | OpenAIRE |
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