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Benchmark: Inviscid NACA0012 Aerofoil(2d)

The results for a small unstructured mesh are presented below. A NACA0012 aerofoil is subjected to inviscid flow at M=0.95, with a zero degrees angle of attack. Farfield vortex correction is applied. The results presented are in excellent agreement with Pulliam and Barton AIAA-1985-0018. In the paper, the AGARD03 test case matches the described situation. Their simulations predicted a lift and drag coefficient of 0.0000 and 0.1103 respectively. Even on this small scale mesh, CBSFlow predicts a lift and drag coefficient of 0.0003 and 0.1104.

The Input zip file contains only the files necessary to run the specified program, the All zip file also contains the output files generated by the program.

M =0.95, α=0

CBSFlow(2d) Explicit Inviscid Solver. The unstructured mesh: 7351 linear triangular elements, 3753 nodes.

Figure: The O Mesh

Figure: Vertical Velocity Component

Figure: Pressure Contour Plot