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. (Author)
Airframe Noise Prediction Method
1977
142 pages
Report
Keine Angabe
Englisch
Aircraft , Aircraft noise , Airframes , Turbulent boundary layer , Noise(Sound) , Intensity , Power spectra , Deflection , Computer programs , Mathematical prediction , Fourier transformation , Leading edges , Trailing edges , Flaps(Control surfaces) , Wings , Landing gear , Noise reduction , Aerodynamic noise
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