Accession Number : ADA182394

Title :   Prediction of High-Speed Rotor Noise with a Kirchhoff Formula,

Corporate Author : ARMY AVIATION RESEARCH AND TECHNOLOGY ACTIVITY MOFFETT FIELD CA AEROFLIGHTDYNAMICS DIRECTORATE

Personal Author(s) : Purcell,Timothy W ; Strawn,Roger C ; Yu,Yung H

PDF Url : ADA182394

Report Date : Jan 1987

Pagination or Media Count : 9

Abstract : A new methodology has been developed to predict the impulsive noise generated by a transonic rotor blade. The formulation uses a full potential finite-difference method to obtain the pressure field close to the blade. A Kirchhoff integral formulation is then used to extend these finite-difference results in o the far field. This Kirchhoff formula is written in a blade fixed coordinate system. It requires initial data across a plane at the sonic radius. This data is provided by the finite difference solution. Acoustic pressure predictions show excellent agreement with hover experimental data for two hover cases of 0.88 and 0.90 tip Mach number. The latter of which has delocalized transonic flow. These results represent the first successful prediction technique for peak pressure amplitudes using a computational code.

Descriptors :   *ROTOR BLADES, *TRANSONIC FLOW, *FLOW NOISE, FINITE DIFFERENCE THEORY, HOVERING, IMPULSE NOISE, METHODOLOGY, PEAK VALUES, PREDICTIONS, PRESSURE, SOLUTIONS(GENERAL), SOUND PRESSURE, AMPLITUDE, COORDINATES, FAR FIELD, SOUND PRESSURE

Subject Categories : Acoustics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE