Abstract
In order to solve the multi-objective multi-constraint design in aerodynamic design of flying wing, the aerodynamic optimization design based on the adjoint method is studied. In terms of the principle of the adjoint equation, the boundary conditions and the gradient equations are derived. The Navier-Stokes equations and adjoint aerodynamic optimization design method are adopted, the optimization design of the transonic drag reduction for the two different aspect ratio of the flying wing configurations is carried out. The results of the optimization design are as follows: Under the condition of satisfying the aerodynamic and geometric constraints, the transonic shock resistance of the flying wing is weakened to a great extent, which proves that the developed method has high optimization efficiency and good optimization effect in the multi-objective multi-constraint aerodynamic design of the flying wing.
Highlights
Multi⁃objective aerodynamic optimization of flying⁃wing configuration based on adjoint method
In order to solve the multi⁃objective multi⁃constraint design in aerodynamic design of flying wing, the aerodynamic optimization design based on the adjoint method is studied
The results of the optimization design are as follows: Under the condition of satisfying the aerodynamic and geometric constraints, the transonic shock resistance of the flying wing is weakened to a great extent, which proves that the developed method has high optimization effi⁃ ciency and good optimization effect in the multi⁃objective multi⁃constraint aerodynamic design of the flying wing
Summary
∫ ∫ δI = δM( w,S) dBξ + δP( w,S) dDξ (3) ∫ [ δM - ni ψTδ( Fi - Fvi ) ] dBξ + B ∫ δI = [ δMII - ni ψTδ( Fi - Fvi ) II ] dBξ + B 参考面积 Sref ,力矩参考点( xref ,yref ) ,易知 ∫ [ ( y - yref ) nx - ( x - xref ) ny ) ] δPdS BW
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