Abstract
With the development of supersonic/hypersonic vehicles, the influence of non-uniform flow has attracted increasing attention. Non-uniform flow exists everywhere in a scramjet, which is a potent engine for supersonic/hypersonic vehicles. Most flows entering the isolator, combustor, and nozzle exhibit high non-uniformity. Thus, several design methods for generating non-uniform flow have been proposed. However, these design methods cannot simulate flow distortion with high accuracy, especially the non-uniform flow caused by shock wave interaction. Thus, a design method for distortion generators, which can generate non-uniform flow associated with flow deflection angles, is proposed in this study to mimic the shock wave-dominated non-uniform flow with shock wave interaction. Numerical simulation and experiment are adopted to verify the effectiveness and reliability of the proposed method. The Mach number on the outlet and the surface pressure distribution on the upper wall of the distortion generator obtained in the experiment show a good agreement with the target one.
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Acknowledgements
We would like to acknowledge the continued support of the NSFC (National Natural Science Foundation of China) for contract numbers 11802123, 11672346, and the Aeronautics Power Foundation (Grant No. 6141B09050383). In addition, this research is funded by the Hong Kong Scholars Program.
Funding
National Natural Science Foundation of China (11802123, 11672346), Aeronautics Power Foundation (6141B09050383), Hong Kong Scholars Program.
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Yu, K., Su, P., Chen, Y. et al. Inverse Design of Flow Distortion Dominated by Shock Wave Interaction with Experimental Verification. Int. J. Aeronaut. Space Sci. 22, 866–873 (2021). https://doi.org/10.1007/s42405-021-00363-1
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DOI: https://doi.org/10.1007/s42405-021-00363-1