Aerothermodynamic Shape Optimization ofHypersonic Blunt Bodies

Date

2013-06-27

Author

Yumusak, Mine
Eyi, Sinan

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The aim of this study is to develop a reliable and efficient design tool that can be used in hypersonic flows. The flow analysis is based on the axisymmetric Euler and the finite rate chemical reaction equations. These coupled equations are solved by using Newton’s method. The analytical method is used to calculate the Jacobian matrix. A gradient based numerical optimization is used. Sensitivities are calculated by using the adjoint and direct differentiation methods. The objective of the design is to generate a hypersonic blunt geometry that produces the minimum pressure drag while keeping the maximum temperature smaller than the baseline value. Bezier curves are used for geometry modification. The performance of the optimization method is demonstrated for different hypersonic flow conditions.

URI

https://arc.aiaa.org/doi/pdf/10.2514/6.2013-2693
https://hdl.handle.net/11511/79932
https://arc.aiaa.org/doi/abs/10.2514/6.2013-2693

DOI

https://doi.org/10.2514/6.2013-2693

Conference Name

21st AIAA ComputationalFluid Dynamics Conference(2013)

Collections

Department of Aerospace Engineering, Conference / Seminar

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Citation Formats

M. Yumusak and S. Eyi, “Aerothermodynamic Shape Optimization ofHypersonic Blunt Bodies,” Ankara, Türkiye, 2013, vol. 2013, Accessed: 00, 2021. [Online]. Available: https://arc.aiaa.org/doi/pdf/10.2514/6.2013-2693.