Publisher's Synopsis
In this paper we consider the solution of the compressible Navier-Stokes equations for a class oflaminar airfoil flows. The principal objective of this paper is to demonstrate that members of thisclass of laminar flows have steady-state solutions. These laminar airfoil flow cases are often used toevaluate accuracy, stability and convergence of numerical solution algorithms for the Navier-Stokesequations. In recent years, such flows have also been used as test cases for high-order numericalschemes. While generally consistent steady-state solutions have been obtained for these flows usinghigher order schemes, a number of results have been published with various solutions, includingunsteady ones. We demonstrate with two different numerical methods and a range of meshes witha maximum density that exceeds 8 × 106 grid points that steady-state solutions are obtained. Furthermore, numerical evidence is presented that even when solving the equations with an unsteadyalgorithm, one obtains steady-state solutions.
