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.

Figure 1: Overview of the geometry of the RAE 2822 test case at Mach 0.729.

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.

Figure 2: Comparison of the Computational and Experimental results for the RAE 2822 airfoil at Mach 0.729 and angle of attack 2.31°.

Figure 3: Local Mach number prediction for the RAE 2822 airfoil at upstream Mach 0.729.

Figure 4: The overall residual as the solution converges.

Downloads

Geometry Data:

• Image of the RAE 2822 Airfoil
• rae2822.sur
• rae2822.bac
• rae2822.bco
• rae2822.con

• Computational Results
• Experimental Results
• Computational Residuals