Method for calculating rigid and induced airload distribution for low aspect ratio wings with supersonic leading and trailing edges and inwardly raked tips is applied to static aeroelastic analysis of set of missile fins for which experimental data is available for both rigid and flexible cases; comparisons are given between theoretical and experimental values for several aerodynamic coefficients; good agreement is shown; general construction of matrices used in aeroelastic analysis is also presented.
Aerodynamic matrix procedure for low aspect ratio wings
J Aircraft
Journal of Aircraft ; 1 , n 4
1964
7 pages
Article (Journal)
English
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Aerodynamic matrix procedure for low aspect ratio wings
AIAA | 1964
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