Aerodynamic loads on a multibladed helicopter rotor in hovering flight are calculated by solving the three-dimensional thin-layer Reynolds-averaged Navier-Stokes equations in a rotating coordinate system on body-conforming curvilinear grids around the blades. The thin-layer Navier-Stokes equations are recast in the absolute-flow variables so that the absolute flow in the far field is uniform but the relative flow is nonuniform. Equations are solved for the absolute-flow variables by employing Jameson's finite-volume explicit Runge-Kutta time-stepping scheme. Rotor-wake effects are modeled in the form of a correction applied to the geometric angle of attack along the blades. This correction is obtained by computing the local induced downwash with a free-wake analysis program. The calculations are performed on a Cray-2 for a model helicopter rotor in hover at various collective pitch angles. The results are compared with experimental data.
Navier-Stokes calculations of the flowfield of a helicopter rotor in hover
Navier Stokes Berechnungen des Stroemungsfeldes eines Hubschrauberrotors im Schwebeflug
AIAA-Papers ; Jan ; 1-9
1988
9 Seiten, 8 Bilder, 1 Tabelle, 11 Quellen
Aufsatz (Konferenz)
Englisch
Flowfield analysis of modern helicopter rotors in hover by Navier-Stokes method
Tema Archiv | 1993
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