A computational investigation of predicting wind tunnel results for selected hypersonic wing test structures
Margraves, Charles; Newman, James C., III
College of Engineering and Computer Science
University of Tennessee at Chattanooga
Place of Publication
A CFD methodology for simulating various configurations of three selected wings in Purdue University’s Boeing Air Force Office of Scientific Research Mach 6 Quiet Tunnel (BAM6QT) is presented. The NASA-developed computational fluid dynamics (CFD) code, FUN3D, is used to calculate forces, moments, and temperature gradients. Wings with an attached elevon are also simulated, and the large wing with elevon case is used to study a moving elevon as well as static elevon deflections. A threshold frequency is found for the moving elevon where the moment imparted by the elevon increases with frequency. An attempt is made to detect unsteadiness around the 12 degree deflected elevon but it is likely more computational resources are needed for this study. Previous work from Alexander Snyder is built upon by attempting to model only the test section of the BAM6QT by using a boundary layer profile inlet condition, but results are not confirmed.
I want to acknowledge my advisor, Dr. Kidambi Sreenivas, for being an incredible teacher and mentor, and for having a seemingly unlimited amount of patience for helping me learn CFD. Also Dr. Ethan Hereth for teaching me how to create quality meshes in Pointwise, as well as my fellow graduate student researchers, Cannon Debardelaben, Jason DeHay, Nina Rice, and Alexander Snyder for their help and friendship. Further, thanks to Cadence Design Systems, Inc for the use of Pointwise meshing software; FieldView CFD Inc, and TecPlot, Inc, for their CFD post-processing tools; UTC’s SimCenter for the use of their HPC systems; and NASA for the use of their FUN3D flow solver. Funding was provided through the Reusable Hypersonic Vehicle Structures program by Air Force Research Laboratory, Aerospace System Directorate, High Speed Systems Division (AFRL/RQH), Prime Contract Number FA8650-18-C-2253.
M. S.; A thesis submitted to the faculty of the University of Tennessee at Chattanooga in partial fulfillment of the requirements of the degree of Master of Science.
Aerodynamics, Hypersonic; Hypersonic wind tunnels; Computational fluid dynamics
xiv, 69 leaves
Snuggs, James, "A computational investigation of predicting wind tunnel results for selected hypersonic wing test structures" (2023). Masters Theses and Doctoral Dissertations.
Dept. of Mechanical Engineering