XFOIL Version 6.96 Calculated polar for: WORTMANN FX 75-193 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.000 -0.1954 0.11991 0.11253 -0.1148 0.9335 0.0461 -12.750 -0.1964 0.11454 0.10717 -0.1180 0.9320 0.0460 -12.250 -0.2418 0.09740 0.09004 -0.1264 0.9280 0.0429 -12.000 -0.2648 0.09303 0.08568 -0.1266 0.9247 0.0426 -11.750 -0.2865 0.08846 0.08108 -0.1276 0.9215 0.0422 -11.500 -0.3111 0.08353 0.07607 -0.1291 0.9183 0.0417 -11.250 -0.3358 0.07892 0.07132 -0.1304 0.9154 0.0413 -11.000 -0.3589 0.07493 0.06716 -0.1310 0.9130 0.0410 -10.750 -0.3900 0.07309 0.06523 -0.1270 0.9087 0.0404 -10.500 -0.4216 0.07179 0.06386 -0.1222 0.9036 0.0403 -10.250 -0.4458 0.06988 0.06181 -0.1190 0.8995 0.0404 -10.000 -0.4643 0.06772 0.05944 -0.1166 0.8959 0.0403 -9.750 -0.4791 0.06575 0.05723 -0.1142 0.8928 0.0406 -9.500 -0.5175 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0.000 -0.1552 0.05254 0.04199 -0.0070 0.7387 0.8192 0.250 -0.1265 0.05259 0.04187 -0.0080 0.7359 0.8221 0.500 -0.1246 0.05256 0.04178 -0.0056 0.7289 0.8257 0.750 -0.1020 0.05260 0.04167 -0.0059 0.7246 0.8293 1.000 -0.0726 0.05274 0.04165 -0.0074 0.7217 0.8325 1.250 -0.0682 0.05289 0.04176 -0.0053 0.7150 0.8351 1.500 -0.0452 0.05302 0.04180 -0.0057 0.7106 0.8373 1.750 -0.0147 0.05317 0.04182 -0.0069 0.7075 0.8397 2.000 -0.0091 0.05345 0.04206 -0.0052 0.7003 0.8430 2.250 0.0142 0.05371 0.04224 -0.0057 0.6958 0.8459 2.500 0.0453 0.05396 0.04240 -0.0073 0.6926 0.8483 2.750 0.0545 0.05441 0.04280 -0.0063 0.6854 0.8506 3.000 0.0767 0.05467 0.04302 -0.0065 0.6804 0.8529 3.250 0.1067 0.05492 0.04321 -0.0076 0.6771 0.8553 3.500 0.1162 0.05545 0.04373 -0.0065 0.6699 0.8578 3.750 0.1392 0.05586 0.04411 -0.0071 0.6647 0.8599 4.000 0.1699 0.05622 0.04443 -0.0085 0.6613 0.8619 4.500 0.2044 0.05744 0.04564 -0.0087 0.6486 0.8665 4.750 0.2353 0.05774 0.04594 -0.0099 0.6451 0.8685 5.000 0.2445 0.05858 0.04680 -0.0091 0.6373 0.8704 5.250 0.2680 0.05909 0.04733 -0.0097 0.6319 0.8720 5.500 0.3001 0.05937 0.04762 -0.0111 0.6282 0.8738 6.000 0.3329 0.06094 0.04927 -0.0111 0.6142 0.8782 6.250 0.3660 0.06121 0.04958 -0.0126 0.6107 0.8804 6.500 0.3710 0.06257 0.05100 -0.0119 0.6011 0.8823 6.750 0.3984 0.06311 0.05159 -0.0130 0.5959 0.8840 7.000 0.4319 0.06331 0.05186 -0.0144 0.5926 0.8857 7.250 0.4327 0.06493 0.05359 -0.0133 0.5820 0.8876 7.500 0.4607 0.06535 0.05408 -0.0142 0.5771 0.8898 7.750 0.4777 0.06633 0.05514 -0.0144 0.5699 0.8920 8.000 0.4943 0.06735 0.05626 -0.0147 0.5619 0.8942 8.250 0.5266 0.06759 0.05662 -0.0159 0.5578 0.8963 8.500 0.5322 0.06933 0.05845 -0.0156 0.5472 0.8980 8.750 0.5596 0.06985 0.05909 -0.0166 0.5416 0.9002 9.000 0.5935 0.06988 0.05926 -0.0178 0.5382 0.9026 9.250 0.5911 0.07224 0.06174 -0.0171 0.5258 0.9048 9.500 0.6223 0.07244 0.06211 -0.0181 0.5214 0.9075 9.750 0.6259 0.07455 0.06435 -0.0179 0.5102 0.9097 10.000 0.6547 0.07488 0.06483 -0.0188 0.5043 0.9122 10.500 0.6885 0.07723 0.06752 -0.0196 0.4869 0.9173 10.750 0.7241 0.07686 0.06736 -0.0205 0.4831 0.9211 11.000 0.7198 0.07986 0.07050 -0.0203 0.4695 0.9242 11.250 0.7544 0.07957 0.07045 -0.0212 0.4652 0.9289 11.750 0.7890 0.08193 0.07322 -0.0222 0.4469 0.9391 12.000 0.7894 0.08467 0.07612 -0.0225 0.4328 0.9451 12.250 0.8253 0.08338 0.07508 -0.0229 0.4278 0.9685 12.750 0.8368 0.08761 0.07965 -0.0231 0.4014 1.0000 13.000 0.8736 0.08586 0.07817 -0.0231 0.3921 1.0000 13.500 0.9067 0.08639 0.07910 -0.0227 0.3602 1.0000 14.000 0.9572 0.08386 0.07698 -0.0215 0.3214 1.0000 14.250 0.9757 0.08379 0.07704 -0.0211 0.2954 1.0000 14.500 0.9879 0.08467 0.07793 -0.0209 0.2590 1.0000 14.750 0.9979 0.08588 0.07887 -0.0206 0.2117 1.0000 15.000 0.9975 0.08883 0.08143 -0.0207 0.1683 1.0000 15.500 0.9860 0.09706 0.08905 -0.0221 0.1169 1.0000 15.750 0.9820 0.10117 0.09297 -0.0232 0.1015 1.0000 16.000 0.9813 0.10491 0.09658 -0.0243 0.0894 1.0000 16.250 0.9824 0.10849 0.10011 -0.0255 0.0791 1.0000 16.500 0.9859 0.11171 0.10330 -0.0267 0.0713 1.0000 16.750 0.9907 0.11476 0.10635 -0.0278 0.0646 1.0000 17.000 0.9981 0.11741 0.10904 -0.0289 0.0596 1.0000 17.250 1.0064 0.11990 0.11153 -0.0299 0.0553 1.0000 17.500 1.0165 0.12222 0.11398 -0.0308 0.0517 1.0000