A solution procedure is presented for the prediction of unsteady, transonic flow past helicopter rotor blades in forward flight. This procedure solves the three-dimensional, unsteady, compressible full potential equation in conservation form in a body-fitted coordinate system using a Strongly Implicit Procedure (SIP). It is assumed that the structure of the unsteady wake, as well as the structural deformation of the rotor blade due to the aerodynamic loads are known independently from a free wake - aeroelastic analysis. These effects are accounted for as corrections to the section angle of attack at several radial stations. Numerical results are presented for a number of rotor configurations in forward flight, and compared with available experimental data.
Solution of transonic flow past rotor blades using the conservative full potential equation
Loesung der Gleichung fuer die Ueberschallstroemung an Rotorfluegeln mit Hilfe der konservativen Potentialgleichung
AIAA-Papers ; Okt ; 1-10
1985
10 Seiten, 3 Bilder, 15 Quellen
Conference paper
English