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+model Trim_Cessna
+
+
+import Modelica.SIunits.*;
+import Modelica.Math.Matrices.*;
+
+parameter Real m = 1043.26;//
+parameter Real s = 16.1651;//reference area
+parameter Real cbar = 1.493 ;//average chord
+parameter Real b = 10.911 ;//span
+parameter Real W[3]  = m*{0,0, 9.81};//gravitational force
+
+
+
+parameter Real CD0    = 0.036;//
+parameter Real K_drag  = 0.0830304;//for cessna
+parameter Real CD_beta = 0.17;//for cessna
+parameter Real CD_alpha= 0.2108;
+parameter Real CD_q = 0;
+parameter Real CD_delta_e= 0.3045;
+
+//side force
+parameter Real Cy_beta  = -0.31;//for cessna
+parameter Real Cy_p  = -0.037;//for cessna
+parameter Real Cy_r   = 0.21;//for cessna
+parameter Real Cy_delta_r = 0.187; //for cessna
+parameter Real Cy_delta_a= 0;     //for cessna
+
+// lift
+parameter Real CL0 = 0.25;   //for cessna
+parameter Real CL_alpha = 4.47;//for cessna
+parameter Real CL_q = 3.9;//for cessna
+parameter Real CL_delta_e = 0.3476;//for cessna
+
+// rolling moment
+parameter Real Cl_beta = -0.089;//for cessna
+parameter Real Cl_p = -0.47;//for cessna
+parameter Real Cl_r = 0.096;//for cessna
+parameter Real Cl_delta_a= -0.09;//for cessna
+parameter Real Cl_delta_r = 0.0147;//for cessna
+
+// pitching moment
+parameter Real Cm0   = -0.02;//for cessna
+parameter Real Cm_alpha = -1.8;//for cessna
+parameter Real Cm_q  = -12.4;//for cessna
+parameter Real Cm_delta_e= -1.28;//for cessna
+
+// yawing moment
+parameter Real Cn_beta = 0.065;//for cessna
+parameter Real Cn_p  = -0.03;//for cessna
+parameter Real Cn_r = -0.99;//for cessna
+parameter Real Cn_delta_a = -0.0053;//for cessna
+parameter Real Cn_delta_r = -0.0657;//for cessna
+
+parameter Real rho = 1.225;
+parameter Real[3,3] J = {{1285.31, 0.0, 0.0}, {0.0, 1824.93, 0.0}, {0.0, 0.0, 2666.893}};
+Real L;
+Real D;
+
+Real Q;
+  
+
+Real V;
+
+parameter Real[3] omega = {0,0.0,0};
+
+Real CL;
+Real CD;
+parameter Real alpha = 0.1;
+Real de;//To be pasted in delta[2] in the TestFm file
+Real thrust;//To be pasted in thrust[1] in the TestFm file
+Real theta = alpha;
+
+
+equation
+
+
+Q=0.5*rho*V^2;
+
+0  = Cm0+Cm_alpha*alpha+((Cm_q*omega[2]*cbar)/(2*V))+Cm_delta_e*de;
+CL = CL0+CL_alpha*alpha+((CL_q*omega[2]*cbar)/(2*V))+CL_delta_e*de;
+//CD = CD0+CD_alpha*alpha+((CD_q*omega[2]*cbar)/(2*V))+CD_delta_e*abs(de);// + CDbeta * beta + CDdeltae * 
+CD = CD0 + K_drag*CL^2;
+
+//Elevator;
+// forces and moments
+
+L = CL*s*Q;
+D = CD*s*Q;
+
+
+
+0 = -D*cos(alpha)+L*sin(alpha)+thrust - m*9.81*sin(theta);
+0 = -D*sin(alpha)-L*cos(alpha)+m*9.81*cos(theta);
+
+end Trim_Cessna;
+\ No newline at end of file