Validation of HyperCODA for reactive solid rocket motor plumes

Kurzfassung

One European effort to improve the solver basis in Europa is based on a initiative of Airbus, DLR and ONERA to develop the next generation CFD solver CODA (short for "CFD for ONERA, DLR and Airbus") that supports both RANS and LES/DES models as well as multi-disciplinary analysis and optimization (MDAO). The flow solver HyperCODA2, 3 is extending the modular flow solver CODA towards simulation capabilities for reactive, multi-species flows at high Mach numbers; conditions typically found in space-craft applications. The simulation of reactive plumes is a crucial part of many (solid propellant) space propulsion devices as it combines high Mach number flows with stiff chemistry. One application is the plumes of solid rocket engines for which the hydrogen/oxygen/chlorine chemistry effects in the plume have to be resolved. These afterburning reactions may have an influence on the infrared irradiance signature of the propulsion system and are, thus, crucial for the design of such thrusters. In this contribution we validate the flow solver HyperCODA using the reactive mix plume flow test case from Ecker.1 This test case includes the complex interaction of the hydrogen/oxygen/chlorine chemistry in the plume using a skeletal reaction mechanism, a widely used validation test case in literature.