Geometric Considerations of Hypersonic Inlet Integrability for Internal Flow-Path Combustion

The geometric approach to the integration of internal flow path inlets, with consideration for general hypersonic body conic sections, is presented. For the models considered, inlet parameters are maintained as non-dimensional values, and vehicle packaging constraints are imposed through simple geometric relationships. These relationships provide a first-order framework for evaluating the feasibility of integrating internal flow path inlets within slender hypersonic forebodies while reserving volume for cooling techniques, instrumentation, diagnostics, and structural requirements.