A design method for shape optimization in incompressible turbulent viscous flow has been developed and validated for inverse design. The gradient information is determined using a control-theory based algorithm. With such an approach, the cost of computing the gradient is negligible. An additional adjoint system must be solved which requires the cost of a single steady state flow solution. Thus, this method has an enormous advantage over traditional finite-difference based algorithms. The method of artificial compressibility is utilized to solve both the flow and adjoint systems. An algebraic turbulence model is used to compute the eddy viscosity. The method is validated using several inverse wing design test cases. In each case, the program must modify the shape of initial wing such that its pressure distribution matches that of the target wing. Results are shown for the inversion of both two dimensional wing sections and fully three dimensional wings.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Space and Planetary Science