Turbojet Project

Turbojet Project - #X8.596####### ##"Turbojet...

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Unformatted text preview: #X8.596####### ##"Turbojet Project" # "State 1" v_1 = 150 T_1 = 300 p_1 = 1 A_1 = 0.7 rho_1 = 1/Volume(air,T=T_1,P=p_1) h_1 = enthalpy(air,T=T_1) s_1 = entropy(air,T=T_1,P=p_1) M_1 = v_1/c_1 c_1 = SoundSpeed(air,T=T_1) m_dot = rho_1*A_1*v_1 m "State 2" M_2 = 0.5 R = 8.314 k_2 = Cp(air,T=T_2)/Cv(air,T=T_2) {k = 1.4} c_2 = (k_2*R*(1000/28.97)*T_2)^(1/2) M_2 = v_2/c_2 0 = m_dot*(h_1+(v_1^2/2000)) - m_dot*(h_2 + (v_2^2/2000)) s_1 = s_2 h_2 = enthalpy(air,T=T_2) p_2 = Pressure(air,T=T_2,S=s_2) rho_2 = 1/volume(air,T=T_2,S=s_2) m_dot = rho_2*A_2*v_2 m "State 3" A_3 = A_2/12 p_3 = 40 eta_c = .7 "Reversible" s_2 = s_3r T_3r = Temperature(air,P=p_3,S=s_3r) h_3r = enthalpy(air,T=T_3r) rho_3r = 1/Volume(air,T=T_3r,P=p_3) m_dot = rho_3r*A_3*v_3r 0 = W_dot_reversible + m_dot*(h_2 + (v_2^2/2000)) - m_dot*(h_3r + (v_3r^2/2000)) "Real" eta_c = W_dot_reversible/W_dot_realc 0 = W_dot_realc + m_dot*(h_2 + (v_2^2/2000)) - m_dot*(h_3 + (v_3^2/2000)) 0 = m_dot*(s_2 - s_3) + sigma_dot_3 s_3 = entropy(air,T=T_3,P=p_3) M_3 = v_3/c_3 c_3 = SoundSpeed(air,T=T_3) h_3 = enthalpy(air,T=T_3) rho_3 = 1/Volume(air,P=p_3,T=T_3) m_dot = rho_3*A_3*v_3 m "State 4" M_4 = .6 M_4 = v_4/c_4 c_4 = (k_4*R*(1000/28.97)*T_4)^(1/2) k_4 = Cp(air,T=T_4)/Cv(air,T=T_4) {k_4 = 1.4} s_3 = s_4 h_4 = enthalpy(air,T=T_4) p_4 = Pressure(air,T=T_4,S=s_4) rho_4 = 1/Volume(air,T=T_4,S=s_4) m_dot = rho_4*A_4*v_4 0 = m_dot*(h_3 + (v_3^2/2000)) - m_dot*(h_4 + (v_4^2/2000)) "State 5" A_5 = A_4 T_5 = 2000 T_b = 2000 h_5 = enthalpy(air,T=T_5) M_5 = v_5/c_5 c_5 = SoundSpeed(air,T=T_5) "p_4 = p_5" rho_5 = 1/Volume(air,T=T_5,P=p_5) s_5 = entropy(air,T=T_5,P=p_5) m_dot = rho_5*v_5*A_5 0 = Q_dot_in + m_dot*(h_4 + (v_4^2/2000)) - m_dot*(h_5 + (v_5^2/2000)) 0 = Q_dot_in/T_b + m_dot*(s_4-s_5) "State 6" A_6 = 5*A_5 W_dot_tout = W_dot_realc s_5 = s_6 M_6 = v_6/c_6 c_6 = SoundSpeed(air,T=T_6) 0 = -W_dot_tout + m_dot*(h_5 + (v_5^2/2000)) - m_dot*(h_6 + (v_6^2/2000)) h_6 = enthalpy(air,S=s_6,P=p_6) T_6 = Temperature(air,S=s_6,P=p_6) m_dot = rho_6*A_6*v_6 rho_6 = 1/Volume(air,S=s_6,P=p_6) r "State 7" M_7 = 3.0 M_7 = v_7/c_7 c_7 = (k_7*R*(1000/28.97)*T_7)^(1/2) k_7 = Cp(air,T=T_7)/Cv(air,T=T_7) {k_7 = 1.4} s_6 = s_7 h_7 = enthalpy(air,T=T_7) p_7 = Pressure(air,T=T_7,S=s_7) rho_7 = 1/Volume(air,T=T_7,S=s_7) m_dot = rho_7*A_7*v_7 0 = m_dot*(h_6 + (v_6^2/2000)) - m_dot*(h_7 + (v_7^2/2000)) "State 8" m_dot = rho_8*A_8*v_8 A_8 = A_7 0 = m_dot*(h_7 + (v_7^2/2000)) - m_dot*(h_8 + (v_8^2/2000)) 0 = m_dot*(s_7 - s_8) + sigma_dot_8 p_7 - p_8 = (rho_8*v_8^2 - rho_7*v_7^2)/10^5 h_8 = enthalpy(air,T=T_8) M_8 = v_8/c_8 c_8 = (k_8*R*(1000/28.97)*T_8)^(1/2) k_8 = Cp(air,T=T_8)/Cv(air,T=T_8) rho_8 = 1/Volume(air,P=p_8,T=T_8) s_8 = entropy(air,T=T_8,P=p_8) s "Thrust w/ shock wave" Thrust_shock = (p_8*A_8 - p_1*A_1)*10^5 + m_dot*(v_8 - v_1) T "Thrust w/o shock wave" Thrust_noshock = (p_7*A_7 - p_1*A_1)*10^5 + m_dot*(v_7 - v_1) { "G-Forces" m = 10000 Thrust_shock = m*a_shock g_forceshock = a_shock/9.81 g Thrust_noshock = m*a_noshock g_forcenoshock = a_noshock/9.81}g_forcenoshock = a_noshock/9....
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This note was uploaded on 08/18/2011 for the course ME 332 taught by Professor Feve during the Spring '08 term at Iowa State.

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Turbojet Project - #X8.596####### ##"Turbojet...

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