Abstract
The flow path of a three ramp, external compression, 2D, hypersonic scramjet inlet is optimized through multi-objective aerodynamic optimization. The two objectives of the study are maximization of the total pressure recovery (TPR) and minimization of exit Mach number. Constraints on minimum mass flow ratio (MFR) are enforced. The design variables include the lengths and the angles of the three ramps. A novel parameterization strategy has been used to maximize the feasible design space. Numerical simulations of viscous flow at Mach 6 are carried out using the open-source RANS CFD solver SU2. Validation studies have been attempted using NASA wind tunnel test data. CFD simulations were carried out on 400 configurations obtained through design of experiments. The results were postprocessed to obtain the TPR, MFR, and exit Mach number. Surrogate models of these objectives and the mass flow ratio constraint were constructed using the regression. These regression models were used in the optimization using the fmincon function of MATLAB by optimizing one objective while keeping the other objective as a constraint for multiple values of the second objective. It was seen that the total pressure recovery and the exit Mach number are conflicting objectives. The Pareto optimal set is obtained and the characteristics of the optimal solution are analyzed.
Supported by Vikram Sarabhai Space Center, ISRO.
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Roy, L., Priyadarshi, P. (2020). Multi-objective Aerodynamic Optimization of a Hypersonic Scramjet Inlet. In: Salagame, R., Ramu, P., Narayanaswamy, I., Saxena, D. (eds) Advances in Multidisciplinary Analysis and Optimization. Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-15-5432-2_5
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