Analytical Computation of Leading-Edge Truncation Effects on Inviscid Busemann-Inlet Performance

An approach is presented to analytically predict the conservation-averaged inviscid Busemann-inlet performance properties at the throat, accounting for the effect of leading-edge truncation. A control volume is drawn such that the calculation of throat-inlet performance relies on the accurate predic...

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Veröffentlicht in:Journal of propulsion and power 2008-07, Vol.24 (4), p.655-661
Hauptverfasser: O'brien, Timothy F, Colville, Jesse R
Format: Artikel
Sprache:eng
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Zusammenfassung:An approach is presented to analytically predict the conservation-averaged inviscid Busemann-inlet performance properties at the throat, accounting for the effect of leading-edge truncation. A control volume is drawn such that the calculation of throat-inlet performance relies on the accurate prediction of the pressure integral along the surface. The pressure integral is predicted by assuming a leading-edge total pressure loss and a Mach number distribution similar to a nontruncated Busemann inlet. The resulting surface profiles can also be used to predict the bow and terminating shock wave shapes. The pressure-integral-prediction approach is compared with a set of inviscid axisymmetric computational fluid dynamics solutions on the same geometries. The comparisons show that the pressure-integral-prediction approach compares favorably with the computational fluid dynamics solutions for inlets with a moderate contraction ratio and truncation angles no greater than 5 deg.
ISSN:0748-4658
1533-3876
DOI:10.2514/1.30178