solutionphase3

# solutionphase3 - % Anirban Chaudhuri % Aerospace structures...

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% Anirban Chaudhuri % Aerospace structures % Project Phase 1, 2 and 3 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) Cwbroot = 170; % Wing-box root chord or wing-box root section length (in) t = 1; % Wing-box root section thickness (in) Cwb_rw = 49; % Wing-box root section width (in) sig_yield = 50e3; % Yield strength of the material being used (psi) s 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); % 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

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% Elliptical Case w0_ell = (Wg*n/2)*(8/(pi*b)); % Max lift at root of wing-box for elliptic case w_ell = w0_ell*sqrt(1 - (4*y.^2/b^2)); % Elliptical distribution of lift % Average Case w_avg = (w_lin + w_ell)./2; % Average distribution of lift w0_avg = max(w_avg); % Max lift at root of wing-box for average case w % If you solved using the integration process for average case then no % points have been deducted from the project report but just stick to the % above procedure for next phase % w0_avg = 8*Wg*n /(b*(pi + 2)); % w_avg = ((w0_avg*(1 - (2/b)*y)) + (w0_avg*sqrt(1 - (4*y.^2/b^2))))./2; % % % Displaying the results % display('Aircraft Lift Curve Slope') % display(Cl_alpha) % display('Wing Mean geometric chord (ft)') % display(c_bar) % display(mu_g) % display(Kg) % display('Incremental Load Factor for Gust loads') % display(delta_n) % display('Load Factor for Gust loads') % display(n_wg) % display('Load Factor selected for the lift calculation (maximum between load factor with and without gust)') % display(n) % display('Maximum Lift for linear distribution') % display(w0_lin) % display('Maximum Lift for elliptic distribution') % display(w0_ell) % display('Maximum Lift for average distribution') % display(w0_avg)
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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.

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solutionphase3 - % Anirban Chaudhuri % Aerospace structures...

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