Sref = 0.28; Cref = 0.20; Bref = 1.4; Xref = 0.055158; Yref = 0.0; Zref = 0.015347; Mass = 0.950; Ixx = 0.03004; Ixy = 0.; Ixz =-0.00137; Iyx = 0.; Iyy = 0.01916; Iyz = 0.; Izx =-0.00137; Izy = 0.; Izz = 0.04573; Tmax = 5; % N max static thrust Vmax = 15; % m.s-1 max propeller speed alpha=[-180. -90. -5. 0. 5. 10. 15. 90. 180.]; CZtot=[ 0. 10. 0.10258 -0.38256 -0.86495 -1.33935 -1.87647 -10. 0.]; CXtot=[ 0.03 0. -0.06047 -0.05454 0.00301 0.07523 -0.10960 0. 0.03]; Cmtot=[ 0. 2. 0.09734 0.03674 -0.04723 -0.13748 -0.11085 -2. 0.]; CZq= [ 0. 0. -9.116817 -8.745563 -8.333030 -7.894211 -7.541241 0. 0.]; CXq= [ 0. 0. -0.507980 -0.147635 0.201468 0.570160 1.026440 0. 0.]; Cmq= -12.3; CZd1= -0.0067; Cmd1= -0.018; CYb= [0. 0. -0.204297 -0.201261 -0.208921 -0.263082 -0.644075 0. 0.]; CYp= [0. 0. -0.217328 -0.145848 -0.074906 -0.009213 0.015563 0. 0.]; CYr= [0. 0. 0.049136 0.076784 0.103757 0.129586 0.152006 0. 0.]; CYd2= -0.0016; Clb= [0. 0. -0.098934 -0.137640 -0.176627 -0.217863 -0.281340 0. 0.]; Clp= -0.50; Clr= [0. 0. 0.064176 0.123690 0.182594 0.241567 0.304727 0. 0.]; Cld2= -0.000045; Cnb= [0. 0. 0.011072 0.000613 -0.009400 -0.018783 -0.019168 0. 0.]; Cnp= [0. 0. 0.027829 -0.031472 -0.087978 -0.137944 -0.158838 0. 0.]; Cnr= [0. 0. -0.041685 -0.040010 -0.043374 -0.056065 -0.120576 0. 0.]; Cnd2= [0. 0. 0.000628 0.000668 0.000698 0.000717 0.000725 0. 0.];