Airframe Noise Prediction Method

Abstract

A noise component method is presented for calculating airframe noise. Noise from clean wing and tail surface is represented as trailing edge noise caused by the turbulent boundary layer. Landing gear noise is given by an empirical representation of model data. Trailing edge flap noise is modeled as a lift dipole normal to the deflected flap, with amplitude and spectrum given by a correlation of flyover data. Measured flyover data for the Prue-2 sailplane, Aero Commander Shirke general aviation airplane, Lockheed JetStar business jet, Boeing 747 commerical jet, and Convair F-106B delta wing airplane are used as test cases. These spectra are compared with predictions by this method and the NASA ANOPP total aircraft method and drag element method. Methods for reducing various components of airframe noise are examined and evaluated.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1977
Accession Number
ADA039664

Entities

People

  • Martin R. Fink

Organizations

  • United Technologies Corporation

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Acoustics
  • Aerodynamic Configurations
  • Aircraft Equipment
  • Aircrafts
  • Airframes
  • Boundary Layer
  • Computer Programs
  • Doppler Effect
  • Frequency Bands
  • High Lift Devices
  • Horizontal Stabilizers
  • Jet Aircraft
  • Landing Gear
  • Nose Wheels
  • Spars
  • Three Dimensional
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Acoustics.
  • Aerodynamics/Aeronautics.
  • Aerospace Engineering