Frederik JACOBS, Johan STEELANT
DOI Number: 10.60853/j545-zk78
Conference Number: HiSST-2024-0029
As the development of hypersonic flight vehicles is rapidly accelerating, engineers are facing different challenges throughout the design cycle. One of these challenges is the avoidance of hot spots and induced boundary layer transition. Different correlations exist that could be used by designers, but they require specific parameters like boundary layer thickness and edge properties, streamline length, stagnation lines etc… which are not directly provided by the CFD solution. To extract these specific parameters, the Boundary Layer Identification and Transition Zone Detection (BLITZ) code was developed in a previous phase. This paper presents the further development of the BLITZ code and its application to the HEXAFLY-INT Experimental Flight Test Vehicle (EFTV). To extend its capabilities and improve its accuracy, a blending methodology between the laminar and turbulent field solution is developed based on an intermittency factor. Together with the implementation of a standalone monitoring property calculation algorithm, it is now possible to make an improved estimate of the reduced total heat load into the vehicle as well as the reduced aerodynamic forces exerted on it considering the evolution of the transitional flow regime. A comparison has been made between purely laminar, purely turbulent and transitional flow along the flight trajectory regarding boundary layer state, integrated heat load, aerodynamic force and critical roughness. This approach allows to assess different critical design parameters. Further evaluation of the complete trajectory is planned for the final manuscript.