Date of Award
12-15-2017
Degree Type
Report
Degree Name
Master of Science (MS)
Department
Mechanical and Aerospace Engineering
Committee Chair(s)
Douglas Hunsaker
Committee
Douglas Hunsaker
Committee
Stephan A. Whitmore
Committee
Geordie Richards
Abstract
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.
Recommended Citation
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, Spring 1920 to Spring 2023. 1149.
https://digitalcommons.usu.edu/gradreports/1149
Included in
Aerodynamics and Fluid Mechanics Commons, Other Aerospace Engineering Commons, Other Mechanical Engineering Commons
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