سال انتشار: ۱۳۸۸

محل انتشار: هشتمین همایش انجمن هوافضای ایران

تعداد صفحات: ۶

نویسنده(ها):

Mohamad Hamed Hekmat – K.N Toosi University of Technology
Masoud Mirzaei – K.N Toosi University of Technology

چکیده:

In this paper, the continuous adjoint method is applied to the inverse pressure design and drag minimization problem for inviscid compressible flow over two-dimensional airfoils. The adjoint method is one of the gradient-based methods. In this method each cycle of design procedure requires the numerical solution to the fluid flow as well as the solution of the flow equations. The flow solver is an Euler solver which has employed the artificial dissipation method to approximate inviscid fluxes in a structured grid. Because of the similarity of the adjont equations to flow equations, the same numerical methods used to solve the flow equations, are used to solve the adjoint equations. The several test cases were carried out to evaluate the performance of the adjoint method in optimum aerodynamic design problem. In the inverse design, the optimum values of the design variables have been reached with an excellent accuracy. In the drag minimization problem, the optimization is performed in a fixed angle of attack with no geometric or aerodynamic constrains (non-constrained optimization). The investigated samples in drag minimization problem shows that a small variation on airfoil geometry has caused considerable decrease in drag coefficient. Based on the numerical results obtained in this work, we can state that the adioint method is an approach with low computational cost for calculation of functional gradients.