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Unformatted text preview: % Incremental Load Factor for gust loads delta_n = Kg*Ude*Ve*Cl_alpha/(498*Wg/S); d n_wog = 2.5; % Load factor without gust loads (g-force) n_wg = 1 + delta_n; % Load factor with gust loads (g-force) n % Selecting the maximum load factor if(n_wg >= n_wog) n = n_wg; else n = n_wog; end e % Span length distribution for the plots y = 0:1:(b/2); % Varies from zero to Wing half-span (in) % Linear Case w0_lin = 2*Wg*n/b; % Max lift at root of wing-box for linear case w_lin = -w0_lin*(1 - (2/b)*y); % Lift distribution along the wing-box half span M_lin = 2*w0_lin.*y.^2/(2*b); % Plotting the linear, elliptic and average distributions over half-span figure(1) plot(y, w_lin, 'b') title('Shear force'); xlabel('Span Location, in'); ylabel('Shear force, lb'); legend('Shear force'); l figure(2) plot(y, M_lin, 'r') title('Bending moment'); xlabel('Span Location, in'); ylabel('Moment, lb'); legend('Shear force');...
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This note was uploaded on 08/27/2011 for the course AEROSPACE 3115C taught by Professor Bakcer during the Spring '10 term at University of Florida.
- Spring '10