Rotating Detonation Rocket Engine (RDRE) Nozzle

Key Technical Challenges: Applying codes of varying dimensionality (quasi-1D, 2D, quasi-2D and full 3-D), and varying complexity (finite rate vs global chemistry, turbulent vs. laminar, etc.) that are used at different points in the design and analysis process - lower complexity, lower dimensionality for initial concept development and higher dimensionality and complexity for detailed design.\nApproach/Research Plan: Develop unsteady boundary conditions from RDRE simulation to use for nozzle simulation; Complete initial simulation of baseline RDRE nozzle validation case; Complete CFD nozzle evaluations; and, Complete drawings for AFRL-Edwards nozzle fabrication.\nDifferent/Complementary: A number of different operating points for several different RDRE combustors will be considered to develop a generalized methodology for nozzle design. To date, no such comprehensive approach to RDRE nozzle design has been attempted.\nNext Step: The completed design will be passed to the AFRL-Edwards team who has agreed to manufacture the nozzle and test it (at their own cost) to validate the design approach.\n

Goal: To design an optimized nozzle for the AFRL/GHKN RDRE; and, develop a general methodology for designing nozzles for RDRE's with various combustor outflow characteristics.\nCapability Need/Knowledge Gap: When nozzles have been included in RDRE combustor tests, simple constant cone angle aerospike-type nozzles have been used with no prefabrication analysis.\nState-of-the-Art/Knowledge: While the RDRE combustor has been demonstrated by a number of organizations, no custom designed RDRE nozzle has ever been tested.

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