A computational investigation of predicting wind tunnel results for selected hypersonic wing test structures

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.

Grantor dc:publisher

University of Tennessee at Chattanooga

Author dc:creator

• Snuggs, James

Contributors dc:contributor

• Sreenivas, Kidambi
• Margraves, Charles; Newman, James C., III
• College of Engineering and Computer Science

• Aerodynamics, Hypersonic
• Hypersonic wind tunnels
• Computational fluid dynamics

Licence

• http://rightsstatements.org/vocab/InC/1.0/

Language dc:language

English, eng

Repository record dc:identifier

https://scholar.utc.edu/theses/819

OAI identifier oai:identifier

oai:scholar.utc.edu:theses-1990