The subject of this paper is the unified aerodynamic and aeroacoustic analysis of transonic hovering rotors. The aerodynamic/aeroacoustic problem is stated in terms of the velocity potential, whereas the solution is determined by applying a shock-capturing boundary integral formulation. Particular emphasis is given to the analysis of the non-linear terms in the equation for the velocity potential, whose contribution cannot be neglected for the transonic flow case analysis. Their contribution is expressed in a conservative form. Starting from the solution for the potential, the Bernoulli theorem is used to determine both the pressure distribution on the body surface (aerodynamic solution) and the acoustic pressure in the field (aeroacoustic solution). Numerical results are presented in order to show the capability of the methodology in determining both the aerodynamic and aeroacoustic solutions for transonic rotor configurations.
A boundary integral method for unified transonic aerodynamic and aeroacoustic analysis of hovering rotors
Ein Grenzintegralverfahren zur einheitlichen schallnahen aerodynamischen und aeroakustischen Untersuchung von Rotorblättern im Schwebeflug
1995
10 Seiten, 14 Bilder, 32 Quellen
Aufsatz (Konferenz)
Englisch
British Library Conference Proceedings | 1995
|Aerodynamic and acoustic calculations of transonic nonlifting hovering rotors
Online Contents | 1996
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