A Computational Fluid Dynamics (CFD) analysis was performed on a C-135 aircraft with a side-mounted splitter plate at the request of the Airborne Laser SPO at Kirtland AFB, and the 4950 Test Wing at Wright-Patterson AFB. The data collected from the analysis was provided to the Test Wing to augment wind tunnel tests and to provide loading and stability information on the modified aircraft. This work was a precursor to a planned flight test program in which a splitter plate will be tested on a Test Wing aircraft. Four flight conditions were analyzed with a modified and unmodified C-135 aerodynamic model, and incremental stability and aerodynamic derivatives were determined. Additionally, pressure coefficient data were tabulated for use in a structural analysis by the Test Wing. (AN).
Computational Fluid Dynamics (CFD) Analysis of a C-135 Aircraft with a Side-Mounted Splitter Plate (With Comparison to Wind Tunnel Data)
1994
114 pages
Report
No indication
English
Aerodynamics , Aerodynamic stability , Computational fluid dynamics , Transport aircraft , Test and evaluation , Velocity , Flight testing , Experimental data , Structural analysis , Comparison , Air flow , Angle of attack , Flow fields , Aerodynamic loading , Wind tunnel tests , Mach number , Wing body configurations , Pressure distribution , Aerodynamic lift , Gas surface interactions , Transonic flow , C-135 aircraft
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