A numerical study has been conducted to investigate the unsteady nature of afterbody vortices shed from an upswept region of a simple fuselage configuration. The upsweep angle considered is , the Reynolds number based on the body’s diameter is , and the freestream Mach number is . These conditions have been selected following recent experimental measurements that serve as validation for the numerical study. The results here also complement the experimental investigation by expanding upon the unsteady aspects of the flow and uncovering details of the full three-dimensional flow structure both on and off the body, which are otherwise unattainable through planar particle image velocimetry and point measurements alone. Details of the wake vortices’ unsteady formation, their interaction on the aft surface, and subsequent mutual interaction are explored. The comparative study of the numerical results and the experimental measurements provides an extremely favorable match between the time-mean vortex size, strength, and position in the wake, along with its surface pressure signature on the body’s aft ramp. Spatial resolution effects are also extensively investigated and effectively eliminated for all quantities of interest. This, in conjunction with the experimental validation, provides strong confidence in the numerical results for future and expanded studies.
High-Fidelity Simulations of Afterbody Vortex Flows
AIAA Journal ; 57 , 9 ; 3980-3990
2019-09-01
Conference paper , Article (Journal)
Electronic Resource
English
High-Fidelity Simulations of Afterbody Vortex Flows
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