This paper deals with some recent developments of a BEM (boundary element methodology) for the unified aerodynamic/aeroacoustic analysis of subsonic and transonic potential flows past helicopter rotors in hover and forward flight. In this methodology, first the potential solution is derived on the rotor-blade surfaces. Then, the boundary integral representation gives the potential everywhere in the field, and the Bernoulli theorem yields the acoustic pressure. Numerical results are presented for helicopter rotors in hover and forward flight at both subsonic and transonic rotor speeds. Comparisons with existing numerical results and experimental data are included.
BEM for aerodynamics and aeroacoustics of rotors in subsonic/transonic forward flight
Grenz-Elemente-Methodologie für die Aerodynamik und Aeroakustik von Rotoren im Horizontalflug unterhalb und nahe der Schallgeschwindigkeit
1996
8 Seiten, 19 Bilder, 12 Quellen
Aufsatz (Konferenz)
Englisch
Aerodynamics and Aeroacoustics of Subsonic and Transonic Rotors in Hover and Forward Flight
British Library Conference Proceedings | 1997
|An Integral Method for Transonic Aerodynamics and Aeroacoustics of Rotors in Forward Flight
British Library Conference Proceedings | 1995
|Subsonic/Transonic Configuration Aerodynamics
NTIS | 1980