Simplified Solution of the Compressible Subsonic Lifting Surface Problem

A new technique for determining the spanwise and chordwise distribution of load, on thin finite wings in compressible subsonic flow, is presented. The method is based on the application of planar lifting surface theory. Classical theoretical results are used to define functions for the pressure coef...

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Bibliographic Details
Main Author: Purvis,J W
Format: Report
Language:English
Subjects:
AERODYNAMIC LOADING
Aircraft
COMPRESSIBLE FLOW
DAMAGE
Damaged wings
Fluid Mechanics
LIFTING SURFACES
LOAD DISTRIBUTION
Planar lifting surface theory
SUBSONIC FLOW
THIN WINGS
WINGS
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Summary:A new technique for determining the spanwise and chordwise distribution of load, on thin finite wings in compressible subsonic flow, is presented. The method is based on the application of planar lifting surface theory. Classical theoretical results are used to define functions for the pressure coefficient distribution, and a new technique is presented for evaluating the kernel function integral. Analytical results are compared with experimental data and with solutions from a standard numerical integration method of applying lifting surface theory. Excellent correlation with experimental results is obtained for Mach numbers up to 0.80 to 0.85 for thin wings. Advantages of the new technique as opposed to other methods are also presented.