UNSTEADY AERODYNAMIC FORCES FOR GENERAL WING/CONTROL-SURFACE CONFIGURATIONS IN SUBSONIC FLOW PART I-THEORETICAL DEVELOPMENT,
Abstract
A kernel-function procedure is presented for the prediction of subsonic oscillatory pressure distributions on finite-aspect-ratio wings with partial-span control surfaces. The basic wing pressure-series functions used in previous kernel-function applications are augmented in this report to include the logarithmic singularity at the control-surface leading edge, and to account for gap effects at the control-surface side edges. The procedure employs either a conventional planar kernel function or, on an optional basis, a non-planar kernel function which considers the effect of an initially deflected control surface. The solution for the unknown coefficients of the pressure-series functions is performed in a least-squares sense based on downwash values at locations chosen by the program user. The final results obtained are in the form of pressure distributions and generalized forces. Finally, a limited correlation of program calculations with available experimental data is presented. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1967
- Accession Number
- AD0831747
Entities
People
- J. B. Smedfjeld
- J. H. Berman
- P. Shyprykevich
Organizations
- Grumman