XFOIL Version 6.96 Calculated polar for: WORTMANN FX 76-100 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.500 -0.9311 0.10389 0.10113 -0.0041 1.0000 0.0155 -15.250 -0.9741 0.09082 0.08789 -0.0120 1.0000 0.0152 -15.000 -1.0060 0.08044 0.07735 -0.0186 1.0000 0.0150 -14.750 -1.0316 0.07132 0.06805 -0.0250 1.0000 0.0152 -14.500 -1.0540 0.06350 0.06004 -0.0302 1.0000 0.0149 -14.250 -1.0677 0.05742 0.05378 -0.0346 1.0000 0.0152 -14.000 -1.0826 0.05179 0.04797 -0.0378 1.0000 0.0149 -13.750 -1.0970 0.04676 0.04272 -0.0403 1.0000 0.0151 -13.500 -1.1049 0.04312 0.03888 -0.0413 1.0000 0.0153 -13.250 -1.1091 0.04032 0.03590 -0.0414 1.0000 0.0154 -13.000 -1.1077 0.03855 0.03396 -0.0408 1.0000 0.0157 -12.750 -1.1131 0.03593 0.03114 -0.0392 1.0000 0.0157 -12.500 -1.1258 0.03259 0.02759 -0.0365 1.0000 0.0162 -12.250 -1.1246 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-0.0019 0.5510 0.9604 2.250 0.2830 0.00731 0.00242 -0.0039 0.4922 0.9645 2.500 0.3151 0.00765 0.00257 -0.0047 0.4438 0.9712 2.750 0.3548 0.00804 0.00272 -0.0073 0.3885 0.9747 3.000 0.3884 0.00835 0.00286 -0.0085 0.3471 0.9802 3.250 0.4254 0.00863 0.00300 -0.0106 0.3111 0.9831 3.500 0.4619 0.00891 0.00314 -0.0126 0.2779 0.9869 3.750 0.5006 0.00916 0.00329 -0.0150 0.2511 0.9908 4.000 0.5394 0.00941 0.00344 -0.0174 0.2250 0.9946 4.250 0.5763 0.00963 0.00357 -0.0195 0.2013 0.9977 4.500 0.6106 0.00984 0.00370 -0.0211 0.1765 1.0000 4.750 0.6308 0.01007 0.00384 -0.0197 0.1549 1.0000 5.000 0.6507 0.01035 0.00401 -0.0182 0.1292 1.0000 5.250 0.6699 0.01071 0.00424 -0.0166 0.1021 1.0000 5.500 0.6889 0.01110 0.00453 -0.0150 0.0818 1.0000 5.750 0.7079 0.01150 0.00488 -0.0133 0.0688 1.0000 6.000 0.7265 0.01194 0.00528 -0.0115 0.0597 1.0000 6.250 0.7461 0.01228 0.00562 -0.0099 0.0538 1.0000 6.500 0.7643 0.01278 0.00613 -0.0081 0.0489 1.0000 6.750 0.7842 0.01312 0.00651 -0.0065 0.0457 1.0000 7.000 0.8027 0.01361 0.00700 -0.0047 0.0422 1.0000 7.250 0.8204 0.01421 0.00764 -0.0028 0.0394 1.0000 7.500 0.8408 0.01455 0.00802 -0.0014 0.0371 1.0000 7.750 0.8604 0.01499 0.00849 0.0002 0.0349 1.0000 8.000 0.8746 0.01600 0.00950 0.0025 0.0322 1.0000 8.250 0.8957 0.01633 0.00992 0.0038 0.0309 1.0000 8.500 0.9155 0.01682 0.01046 0.0053 0.0294 1.0000 8.750 0.9349 0.01734 0.01102 0.0068 0.0278 1.0000 9.000 0.9519 0.01811 0.01181 0.0085 0.0264 1.0000 9.250 0.9662 0.01928 0.01306 0.0107 0.0252 1.0000 9.500 0.9866 0.01970 0.01358 0.0120 0.0240 1.0000 9.750 1.0053 0.02032 0.01427 0.0134 0.0228 1.0000 10.000 1.0230 0.02099 0.01499 0.0149 0.0219 1.0000 10.250 1.0388 0.02186 0.01589 0.0167 0.0209 1.0000 10.500 1.0472 0.02379 0.01793 0.0193 0.0200 1.0000 10.750 1.0641 0.02446 0.01874 0.0209 0.0195 1.0000 11.000 1.0782 0.02546 0.01989 0.0228 0.0189 1.0000 11.250 1.0915 0.02646 0.02100 0.0246 0.0183 1.0000 11.500 1.1027 0.02762 0.02228 0.0267 0.0178 1.0000 11.750 1.1135 0.02863 0.02337 0.0287 0.0172 1.0000 12.000 1.1215 0.02951 0.02431 0.0312 0.0168 1.0000 12.250 1.1251 0.03087 0.02575 0.0339 0.0164 1.0000 12.500 1.1251 0.03270 0.02769 0.0365 0.0160 1.0000 12.750 1.1160 0.03556 0.03078 0.0390 0.0156 1.0000 13.000 1.1172 0.03731 0.03270 0.0403 0.0154 1.0000 13.250 1.1120 0.04003 0.03562 0.0411 0.0153 1.0000 13.500 1.1079 0.04285 0.03862 0.0411 0.0151 1.0000 13.750 1.0972 0.04690 0.04287 0.0400 0.0150 1.0000 14.000 1.0880 0.05120 0.04735 0.0378 0.0149 1.0000 14.250 1.0744 0.05668 0.05303 0.0344 0.0148 1.0000 14.500 1.0556 0.06353 0.06008 0.0299 0.0149 1.0000 14.750 1.0345 0.07131 0.06805 0.0245 0.0149 1.0000 15.000 1.0046 0.08113 0.07807 0.0178 0.0150 1.0000 15.250 0.9736 0.09145 0.08854 0.0112 0.0151 1.0000 15.500 0.9361 0.10368 0.10094 0.0036 0.0152 1.0000