SEMIEMPIRICAL AIRFRAME NOISE PREDICTION MODEL AND EVALUATION WITH FLIGHT DATA

A semiempirical maximum overall sound pressure level (OASPL) airframe noise model was derived. Noise radiated from aircraft wings was modeled on the trailing edge diffractes quadrupole sound theory. The acoustic dipole sound theory was used to model noise from the landing gear. The model was correlated with maximum OASPL flyover noise measurements obtained for three jet aircraft. One third octave band sound pressure level flyover data was correlated and interpreted.

  • Corporate Authors:

    NASA Dryden Flight Research Center

    P.O. Box 273
    Edwards, CA  USA  93523-0273
  • Authors:
    • Hersh, A S
    • Burcham, FWJ
    • Putnam, T W
    • Lasagna, P L
  • Publication Date: 1976-12

Media Info

  • Pagination: 36 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00154333
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: NASA-TM-X-56041, H-951
  • Contract Numbers: NAS4-2250
  • Files: TRIS
  • Created Date: May 31 1977 12:00AM