3916

3694

كارشناسي ارشد

تبديل انرژي

اصفهان: دانشگاه صنعتي اصفهان، دانشكده مكانيك

1386

دوازده، 79،[II]ص: مصور، جدول، نمودار

ص.ع.به: فارسي و انگليسي

مهندسي مكانيك

ID3694

به فارسي و انگليسي: قابل رويت در نسخه ديجيتال

۸۰ Abstract One of the efficient methods in aerodynamic shape optimization is the adjoint method This method can be applied in continuous or discrete form In this research the continuousand discrete adjoint equations have been derived for two dimensional viscous compressibleflows This method has been used to optimize airfoils in subsonic and transonic flows Each design cycle requires the numerical solution of both the flow and the adjointequations leading to a computational cost roughly equal to the cost of flow solver In thisstudy two approaches for parameterizing the airfoil are utilized One approach employs thesurface mesh points and the other one uses the definition of NACA 4 digit airfoil series Inpresent work the adjoint method has been used for the two deign problems usually arisenin aerodynamic shape optimization inverse pressure design and drag minimization withthe specified lift constraint In inverse design problem the optimum value of designvariables was obtained successfully In drag minimization problem the angle of attack wasvaried to fix the lift coefficient In presented problems small changes in airfoil geometryhave decreased the drag coefficient considerably For a sample problem the gradientscomputed using the adjoint approach have been compared to finite difference gradients toexamine the correctness of program in gradients calculation

احمد رضا پيشه ور

ابراهيم شيراني

محسن ثقفيان، احمد صداقت