Abstract
Steady-state Computational Fluid Dynamic (CFD) analyses have been used to predict wing pressure distributions at a transonic maneuver condition for the Short Takeoff and Vertical Landing (STOVL) and the Carrier Variant (CV) versions of the F-35 Joint Strike Fighter (JSF). The transonic maneuver condition is characterized by strong streamwise vortex patterns and boundary-layer separation. This paper describes an approach to validate Lockheed Martin Aeronautics Company (LM Aero's) Falcon CFD code in predicting wing pressure distributions that are driven by these flowfield phenomena. Critical findings in the validation stage, focused on grid resolution, turbulence models, and limiter function changes, helped to improve the CFD correlation against experimental data and demonstrated an approach that will allow steady-state CFD to be applied to strong vortical and separated flowfields at transonic conditions.
Published Version
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