Hypersonic lifting vehicles experience severe aerodynamic heating while on hypersonic flight regime during atmospheric reentry or unpowered glide. Complex flow interaction is observed in a certain range of flight conditions that results in high heat flux banded region on the windward surface, which should be taken into consideration for thermal protection designing. To obtain desirable surface heat flux distribution and aerodynamic efficiency of a lifting body, shape optimization to reduce the interaction intensity and increase the spanwise distance of the banded heating region on the windward surface was performed in this study. Both single- and multi-objective designs were developed with multiple constraints, including volume, lift-to-drag ratio, the heating rates in stagnation region, and the base section profile of the body. The free-form deformation method was employed for evaluating surface deformation followed by the transfinite interpolation method to update the computational mesh. The range of Pareto front obtained was consistent with the results of single-objective optimization. Additionally, a contradictory and non-linear correlation between the two objectives was elucidated. The optimal solutions exhibited superior comprehensive aerodynamic performance, and the aerothermodynamic shape optimization method was demonstrated to be efficient and practicable.


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    Title :

    Aerothermodynamic Shape Optimization of a Hypersonic Lifting Body


    Additional title:

    Lect. Notes Electrical Eng.


    Contributors:

    Conference:

    Asia-Pacific International Symposium on Aerospace Technology ; 2021 ; Korea (Republic of) November 15, 2021 - November 17, 2021



    Publication date :

    2022-08-31


    Size :

    11 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English




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