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function[] = phase2linear() f % Anirban Chaudhuri % Aerospace structures % Project Phase 1 clear all; close all; clc; c % Change according to UFID F = 0; % UFID first digit L = 5; % UFID last digit L % Given Parameters Wg = 350000+1000*F; % Gross weight of airplane (lb) b = 1490+10*L; % Wing-box span (in) S = 3129; % Wing gross area (sq ft) Croot = 337.25; % Wing-root chord (in) Ctip = 90; % Wing-tip chord (in) Ar = 9.3; % Aspect ratio delta = pi/6; % Wing sweep angle (=30 deg) (rad) d rho = 0.00237; % Air density (lb-s^2/ft^4) Ve = 363.8; % Equivalent aircraft velocity (knots) Ude = 66; % Derived equivalent gust velocity (fps) g = 32.174; % Gravity (ft/s^2) M = 0.55; % Mach number Beta = sqrt(1-M^2); % Calculating load factor % Aircraft Lift Curve Slope Cl_alpha = 1.15*2*pi*Ar/(2 + (4 + Ar^2*Beta^2*(1 + (tan(delta)/Beta)^2))^0.5); % Wing Mean geometric chord (ft) c_bar = (2/3)*(Croot + Ctip - (Croot*Ctip/(Croot + Ctip)))*(1/12); c mu_g = 2*Wg/(rho*g*S*c_bar*Cl_alpha); Kg = 0.88*mu_g/(5.3 + mu_g);

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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 (linear case)'); xlabel('Span Location, in'); ylabel('Shear force, lb'); y figure(2) plot(y, M_lin, 'r') title('Bending moment (linear case)'); xlabel('Span Location, in'); ylabel('Moment, lb-in'); y...
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