High-accuracy aerodynamic optimization of hypersonic vehicles based on continuous adjoint

GAO Chang; LI Zhengzhou; HUANG Jiangtao; HE Yuanyuan; WU Yingchuan; LE Jialing; GUI Feng

doi:10.7527/S1000-6893.2020.24490

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2021 , Vol. 42 >Issue 7: 124490 - 124490

DOI: https://doi.org/10.7527/S1000-6893.2020.24490

Fluid Mechanics and Flight Mechanics

High-accuracy aerodynamic optimization of hypersonic vehicles based on continuous adjoint

GAO Chang ,
LI Zhengzhou ,
HUANG Jiangtao ,
HE Yuanyuan ,
WU Yingchuan ,
LE Jialing ,
GUI Feng

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1. Science and Technology on Scramjet Laboratory, China Aerodynamics Research and Development Center, Mianyang 621000, China;
2. China Aerodynamics Research and Development Center, Mianyang 621000, China;
3. AECC Sichuan Gas Turbine Establishment, Chengdu 610500, China

Received date: 2020-07-03

Revised date: 2020-07-16

Online published: 2020-08-17

Supported by

Foundation of Science and Technology on Scramjet Laboratory (STS/MY-ZY-2018-007)

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Abstract

High-accuracy aerodynamic optimization is an essential approach to the improvement of the aerodynamic performance of hypersonic vehicles. The continuous adjoint equations considering the variations of laminar viscous transport coefficients, boundary conditions and surface sensitivity of aerodynamic force objective functions are derived based on the Navier-Stokes equations. The continuous adjoint solver applicable to hypersonic flows is built and the adjoint convective flux discretized based on a 2-order Roe scheme with entropy corrections. Based on the Free Form Deformation (FFD) methods and the Sequential Quadratic Programming (SQP) algorithm, a high-accuracy adjoint gradient optimization sketch is established, verified and applied to a 2D airfoil and Sanger wing under hypersonic free streams. Results indicate that the adjoint convective scheme possesses strong robustness and low dissipation. The aerodynamic force objective function gradients obtained by the continuous adjoint solver are valid. The lift-drag ratio of the optimized Sanger vehicle increases by 5.0% due to the second shock wave. Verification and optimization confirm the feasibility of the high-accuracy aerodynamic optimization of hypersonic vehicles based the continuous adjoint methods.

Key words： hypersonic vehicles; high-accuracy aerodynamic optimization; continuous adjoint method; FFD methods; SQP algorithm

Cite this article

GAO Chang , LI Zhengzhou , HUANG Jiangtao , HE Yuanyuan , WU Yingchuan , LE Jialing , GUI Feng . High-accuracy aerodynamic optimization of hypersonic vehicles based on continuous adjoint[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021 , 42(7) : 124490 -124490 . DOI: 10.7527/S1000-6893.2020.24490

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