navion_1 - %Calculate the Static Stability Params for the...

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%Calculate the Static Stability Params for the %Navion General Aviation A/C % 16.333 % Adapted from Nelson, page 57 %clear all W=2750 %lb V=176 % ft/sec X_cg=0.295 %cbar h=0.295 S=184 % ft^2 b=33.4 % ft cbar = 5.7 % ft S_t=43 %ft^2 l_t=16 %ft h_t=l_t/cbar+h % Wing C_m_ac_w=-0.116 C_l_alp_w=0.097 %/deg alp_0_L=-5 % deg X_ac=0.25 %cbar h_nbar=0.25 i_w=1 %deg %Tail C_l_alp_t=0.088 %/deg C_m_ac_t=0 %i_t=-1% deg eta=1; b_t=2.2/5.5*b; V_H=l_t*S_t/cbar/S AR=b^2/S AR_t=b_t^2/S_t d2r=180/pi; % convert wing section lifts to 3D wing C_L_alp_w=C_l_alp_w*d2r/(1+C_l_alp_w*d2r/(pi*AR)) C_L_alp_t=C_l_alp_t*d2r/(1+C_l_alp_t*d2r/(pi*AR_t)) % Wing contribution % from 2-4 % C_m_cg_w=C_L_w(h-h_nbar)+C_m_ac_w; % % with C_L_w=C_L_0_w + C_L_alp_w alp_w % where C_L_0_w = lift coeff at zero angle of attack C_L_0_w = C_L_alp_w * abs(alp_0_L/d2r) % C_m_cg_0_w=C_L_0_w*(h-h_nbar)+C_m_ac_w C_m_cg_alp_w=C_L_alp_w*(h-h_nbar) % for downwash % eps = eps_0 + eps_alp alp_w eps_0=2*C_L_0_w/pi/AR eps_alp=2*C_L_alp_w/pi/AR % Tail from 2-8
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This note was uploaded on 11/07/2011 for the course AERO 16.333 taught by Professor Alexandremegretski during the Fall '04 term at MIT.

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navion_1 - %Calculate the Static Stability Params for the...

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