Date of Award
Master of Science (MS)
Mechanical and Aerospace Engineering
Stephan A. Whitmore
It is known that the aerodynamic center changes from quarter chord to half chord from incompressible to compressible flows on airfoils. Compressible corrections are derived and implemented in a vortex panel code. These results will be used to find the aerodynamic centers for the specified Mach range of 0.1 to 0.8 in 0.1 increments within - 6 to 6 degrees angle of attack. OpenFOAM 5 cases will be created with specific meshes and settings. The results calculated from OpenFOAM 5 will be compared to the results obtained from the compressible corrections.
Weaver, Dustin, "A Comparison of the Aerodynamic Centers for Panel Code Compressible Corrections and OpenFOAM 5 FOR Mach 0.1 to 0.8" (2017). All Graduate Plan B and other Reports. 1149.
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