Accession Number:

AD0669215

Title:

TEST RESULTS FROM THE BOUNDARY LAYER FACILITY - RESPONSE OF STRUCTURE TO THE PSEUDO-SOUND FIELD OF A JET (USING COMBINED CONTINUUM AND FINITE ELEMENT METHOD),

Descriptive Note:

Corporate Author:

BOEING CO RENTON WASH COMMERCIAL AIRPLANE DIV

Personal Author(s):

Report Date:

1968-01-02

Pagination or Media Count:

49.0

Abstract:

The response of a simple panel structure to a jet pseudo-sound field is investigated and a prediction method is presented. The mean square displacement is approximated quite closely but the modal energy distribution is shown to be more dependent on an accurate pressure field model being assumed. It is argued however, that the accuracy of the prediction method can only improve with increasing jet diameter, with the result that a full-scale situation would be more favorable to this combined method. The use of a finite element technique enables complex structures to be represented more realistically than with the normal mode assumption, although the latter is sufficient at the higher mode numbers, and probably more accurate. Author

Subject Categories:

  • Aerodynamics
  • Aircraft
  • Acoustics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE