A potential-flow panel method has been modified to calculate the effects of a rotor wake on the time-averaged surface pressure and velocity distributions on a helicopter fuselage. The rotor-induced velocities are calculated by using a vortex-tube wake model. The calculated pressure distributions are found to compare well with experimental data obtained from tests of a wind-tunnel model. (Jensen)
Development and validation of a combined rotor-fuselage induced flow-field computational method
Entwicklung und Geltungsbereich einer Komputermethode zur Berechnung des Stroemungsfeldes der Kombination von Rumpf und Rotor
US Government Research Reports ; Jun ; 1-61
1980
61 Seiten
Report
Englisch
Evaluation of Isolated Fuselage and Rotor - Fuselage Interaction Using Computational Fluid Dynamics
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