wf_alpha = [-9:80];
wf_alpha2 = [-19:90];
wf_cl = [-0.270 -0.248 -0.208 -0.168 -0.128 ...
         -0.088 0.052 0.142 0.225 0.3 0.367 0.43 0.493 0.556 0.618 0.68 ...
          0.74 0.8 0.857 0.912 0.963 1.01 1.05 1.082 1.103 1.11 1.101 ...
          1.072 1.017 0.932 0.81 0.76 0.73 0.7 0.7 0.7 0.7 0.7 0.705 0.71 ...
          (720-8*(41:90))/1000];
wf_cd = [0.387 0.376 0.353 0.332 0.301 0.272 0.245 0.217 0.190 0.168 ...
        0.152 0.136 0.122 0.109 0.100 ... 
        0.091 0.084 0.077 0.075 0.073 0.075 0.08 0.084 0.091 0.1 0.109 ...
        0.122 0.136 0.152 0.168 0.19 0.217 0.245 0.272 0.301 0.331 0.353 ...
        0.376 0.387 0.399 0.415 0.43 0.443 0.457 0.468 0.48 0.493 0.507 ...
        0.518 0.53 (50+10*(51:110))/1000];
wf_cm = [-0.034 -0.034 -0.034 -0.034 -0.034 ...
        -0.054 -0.072 -0.101 -0.127 -0.148 -0.165 -0.18 -0.195 -0.21 ...
        -0.224 -0.239 -0.254 -0.269 -0.284 -0.299 -0.313 -0.328 -0.337 ...
        -0.344 -0.35 -0.353 -0.35 -0.345 -0.338 -0.334 -0.319 -0.308 ...
        -0.297 -0.286 -0.286 -0.286 -0.286 -0.286 -0.286 -0.286 ...
        -(140+4*(41:90))/1000]*-100;
wf_cls = [-0.500 -0.500 -0.500 -0.528 -0.590 -0.624 -0.634 ...
        -0.624 -0.602 -0.567 -0.523 -0.474 -0.419 -0.363 -0.304 ...
        -0.244 -0.183 -0.122 -0.061 0 0.061 0.122 0.183 0.244 ...
         0.304 0.363 0.419 0.474 0.523 0.567 0.602 0.625 0.634 ...
         0.642 0.590 0.528 0.510 0.5 0.5 0.5 0.490 0.460 ...
         0.440 0.420 0.4 0.380 0.360 0.340 0.320 0.3 (550-5*(51:110))/1000];
 wf_w2e = 9.7;
 wf_cp_e = 112; % % chord
 wf_weight = 750; % lbm
 wf_inertia = 280; % slugs-ft^2
 wf_sref = 510; % ft^2
 wf_c = 6.5; %ft
 wf_cg = 29; % % chord
 wf_incidence = 8; % deg
 wf_alphaa = 4.12; %deg
 wf_z1 = 15; % vertical coord center of lift
 wf_z2 = 23; % vertical coord center of drag
 wf_z3 = 13; % vertical coord center of thrust
 wf_q = 0; % rate of change of pitch angle (rad/sec)
 wf_gravity = 32.17; % gravity (ft/sec)
 wf_H = 16.9;
 wf_Q2 = 1.8;
 wf_Q4 = 2.0;
 wf_B3 = 0.06;
 %b7