Title: Inverse Waverider Design for Inward Turning Inlets
Abstract: *† ‡ A method for the design of an integrated forebody-inlet waverider structure using an isentropic compression inlet in an inviscid flow is presented. This method seeks to provide geometries based on inward-turning inlets by prescribing the waverider’s defining shockwave such that desired throat flow conditions are delivered by the inlet. Inlet designs with circular throat cross-sections are found by streamtube tracing through the flowfield within an isentropic nozzle in which flow direction is reversed and terminated at the location of a shock surface suitable for converting upstream conditions to those of the isentropic inlet/nozzle flow. The leading shockwave surface for waverider design is formed by extending the shock surface within the inlet laterally in the Y dimension and as a tangent plane above and below the inlet capture area. Isentropic compression inlet designs and corresponding leading shockwave structures developed in this way are presented for 20 separate cases. Solutions are found for flight Mach numbers of 5, 7, 10, 12, and 15 and area ratios of 5-, 10-, and 20-to-1. Captured flow properties for a representative case show the internal flow to be well-behaved. An examination of the changes in inlet shape caused by altering flight Mach number, free stream pressure, and area ratio demonstrates the applicability of the method to a wide variety of design conditions.
Publication Year: 2005
Publication Date: 2005-07-10
Language: en
Type: article
Indexed In: ['crossref']
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Cited By Count: 11
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