Navier-Stokes computational fluid dynamics calculations are presented for isolated, half-span, and full-span V-22 tiltrotor hover configurations. These computational results extend the validity of CFD hover methodology beyond conventional rotorcraft applications to tiltrotor configurations. Computed steady-state, isolated rotor performance agrees well with experimental measurements, showing little sensitivity to grid resolution. However, blade-vortex interaction flowfield details are sensitive to numerical dissipation and are more difficult to model accurately. Time-dependent, dynamic, half- and full-span installed configurations show sensitivities in performance to the tiltrotor fountain flow. As such, the full-span configuration exhibits higher rotor performance and lower airframe download than the half-span configuration. Half-span rotor installation trends match available half-span data, and airframe downloads are reasonably well predicted. Overall, the CFD solutions provide a wealth of flowfield details that can be used to analyze and improve tiltrotor aerodynamic performance.
CFD Simulations of Tiltrotor Configurations in Hover
2002
16 pages
Report
No indication
English
Aerodynamics , Meetings , Navier-stokes equation , Computational fluid dynamics , Aerodynamic characteristics , Aerodynamic configurations , Tilt rotor aircraft , Flow distribution , Aerodynamic loads , Tilting rotors , Time dependence , Structural design , Computer programs , Grid generation(Mathematics) , Blade-vortex interaction
CFD Simulations of Tiltrotor Configurations in Hover
NTIS | 2002
|CFD Simulations of Tiltrotor Configurations in Hover
NTRS | 2002
|CFD Simulations of Tiltrotor Configurations in Hover
Online Contents | 2005
|Tema Archive | 1993
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