  Main    Overview    Validation    Benchmark    FAQ's    Links    
Steady Validation Data for a Transonic RAE 2822 Airfoil This page presents a set of steady validation data obtained for the simulation of a transonic flow over a rae2822 airfoil with an angle of attack of 2.31°. The supersonic flow on the upper surface develops a shock. The results will be compared to the experimental solution found at the NPARC Alliance Validation Archive. The simulation has a upstream Mach number of 0.729. 
Geometry The geometry of the RAE 2822 test case takes advantage of the symmetry surface designation in the STARS code. The test case consists of a wing section with an upper and lower surface. These two surfaces are bound by planes of symmetry on either side. This allows the solver to simulate an infinite wing span. The solver then proceeds to solve this two dimensional test case as if it were still a three dimensional problem. Figure 1 shows the geometry of the test case. Surfaces 1,2,3 and 4 are planes of symmetry. Planes 5 and 6 are far field, surfaces that the free stream can move through, planes. Surfaces 7 and 8 are wall planes, or solid planes that the flow can not move through. The trailing edge of the airfoil is also set as a singularity point. The geometry has 198,528 elements and 38,571 nodes.

Computational Results The test case required 8.679 hours, 31245 seconds, to run on an AMD Athlon 1 GHz with 256 Megs of RAM. Figure 2 shows the computational results for C_{p} verses the experimental values. The euler3d solution captures the shock point well. Figure 3 predicts the local Mach number along the surface of the airfoil. Figure 4 shows the residuals as the solution converged.

Downloads Geometry Data: Solution and Experimental Data: 
 
URL: http://www.caselab.okstate.edu/research/validation/rae2822.html Revised: May 15, 2001 [AB] Webmaster: caselab@gmail.com 