Project Title:

A Unified Numerical Approach for Rotorcraft Aerodynamics

92-1-02.06-2021                                                   NAS02-13785
A Unified Numerical Approach for Rotorcraft
     Aerodynamics
Flow Analysis, Inc.
256 93rd Street
Brooklyn, NY  11212
Clin M. Wang                                         (718-875-2021)

Abstract:

     A new vorticity confinement method, which has been
demonstrated to convect vorticity on a coarse grid without
excessive numerical diffusion, is to be incorporated into an
efficient viscous flow solver to resolve complicated flow problems
encountered in rotorcrafts. The accuracy and the efficiency of the
new combined numerical approach will be demonstrated through pilot
computations of retreating blade dynamic stall and strong blade-
vortex interaction, including vortex impingement. The new code
will be able to treat realistic rotorcraft-type flows with
concentrated, thin vortical regions, as well as flows that may
involve continuous shedding of vorticity from the blade.

Potential Commercial Application:

Potential Commercial Applications:  The new code will be efficient
and accurate for solving vortex dominated flows. These flows are
involved in many different applications, including problems
encountered by the aerospace industry and by builders of wind-
mills, ships, and automobiles.

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