Navier-Stokes Computations About Complex Configurations Including a Complete F-16 Aircraft

Abstract

IntroductionC OMPUTATIONAL fluid dynamics (CFD) algorithm and computer hardware developments have been rapidly advancing over the last decade. CFD computer codes have been used in many applications to improve the design of aircraft. For example, linear panel methods have been used to improve the design of complex aircraft configurations providing the flow does not contain shock waves or significant separation. Nonlinear potential methods have been used to remove the adverse characteristics caused by shock waves in the transonic regime with the limitation that vorticity and entropy production are not large. The problem of solving the Euler/Navier-Stokes equations about reasonably complete aircraft configurations is now the central issue facing the CFD research community, and, in fact, many significant results demonstrating the power of this approach have already been produced.There are many reasons for pursuing this line of research. First, the large computer costs associated with the numerical solution of the Euler/Navier-Stokes equations in three dimensions is rapidly decreasing. This is a direct result of new improved algorithms and fast vector computers such as the Cray XMP and YMP, the Cray 2, and the CDC Cyber 205. Second, there Downloaded by UNIVERSITY OF NEW SOUTH WALES on July 30, 2015 | http://arc.aiaa.org | Downloaded by UNIVERSITY OF NEW SOUTH WALES on July 30, 2015 | http://arc.aiaa.org | Downloaded by UNIVERSITY OF NEW SOUTH WALES on July 30, 2015 | http://arc.aiaa.org | Downloaded by UNIVERSITY OF NEW SOUTH WALES on July 30, 2015 | http://arc.aiaa.org | Downloaded by UNIVERSITY OF NEW SOUTH WALES on July 30, 2015 | http://arc.aiaa.org |