Project Title:
Simulation of Helicopter Rotor-Body Interaction Flow Fields by Navier-Stokes Method
02.06-7722
910805
Simulation of Helicopter Rotor-Body Interaction Flow Fields by Navier-Stokes Method
JAI Associates, Inc.
465 Fairchild Drive, Suite 111
Mountain View
CA
94043
G.R.
Srinivasan
415-967-7722
ARC
NAS2-13534
019
02.06-7722
910805
Abstract:
Simulation of Helicopter Rotor-Body Interaction Flow Fields by Navier-Stokes Method
A three-dimensional, unsteady Navier-Stokes numerical methodology to calculate economically
and accurately the flow field of multi-bladed helicopter rotor and fuselage in hover
and forward flight will be developed. Ad hoc wake models will not be used to model
the vortex wake; instead, the complete vortical wake will be captured as a part of
the overall flow field solution. A Navier-Stokes upwind scheme will be used in conjunction
with a Chimera grid for preserving and convecting concentrated vortices. Phase I
will demonstrate a calculation for a rotor-body combination in hover which would
provide a solid foundation for realistic calculations in hover and forward flight
in Phase II. The individual items to be completed in Phase I are the gridding of
a two-bladed rotor and fuselage for a Chimera scheme; implementation of Chimera and
Pegasus schemes into the Navier-Stokes numerical method; and a demonstration calculation
of rotor-body flow in hover and comparing the results with experiments.
Commercial applications include the design of advanced technology helicopters with
efficient aerodynamics and aeroacoustics performance, including the selection process
of rotor blade shapes and planforms and the interaction of multiple moving bodies
relative to each other such as the main rotor and tail rotor and engine turbines
and compressors.
viscous flow, Navier-Stokes equations, unsteady, hover, forward flight, helicopter
rotor, wake, interaction flow, transonic, three-dimensions