Accession Number:

ADA050467

Title:

Theoretical Determination of Subsonic Oscillatory Airforce Coefficients,

Descriptive Note:

Corporate Author:

AERONAUTICAL RESEARCH COUNCIL LONDON (ENGLAND)

Personal Author(s):

Report Date:

1976-05-01

Pagination or Media Count:

117.0

Abstract:

The theoretical method presented for the calculation of the linearised values of generalised airforce coefficients on a harmonically oscillating flat plate wing in subsonic flow is a further development of the lifting surface theory of Multhopp type, and has been justified mathematically. The method of spanwise integration is refined, and the number of upwash points taken may be greater than the number of basic functions used in the approximation for the loading. The refined method of spanwise integration leads to improved accuracy in the evaluated values of upwash, especially near the perimeter of the planform. By taking more upwash points than the number of basic loading functions more accurate values should be obtained for the generalised airforce coefficients for a given number of basic functions. The procedure has been programmed in ICL 1900 FORTRAN. The program has been used to obtain results for tapered swept and rectangular wings. For the particular examples of tapered swept and rectangular wings the convergence of the results is studied. Author

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE