XFOIL Version 6.96 Calculated polar for: FX 75-VG-166/22 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 ------ -------- --------- --------- -------- -------- -------- -12.750 -0.1716 0.08906 0.08580 -0.1005 0.7617 0.0296 -12.500 -0.4913 0.05007 0.04575 -0.1260 0.7650 0.0173 -12.250 -0.5042 0.04711 0.04268 -0.1246 0.7643 0.0171 -12.000 -0.5291 0.04346 0.03878 -0.1216 0.7635 0.0171 -11.750 -0.5343 0.04130 0.03652 -0.1195 0.7626 0.0166 -11.500 -0.5515 0.03840 0.03334 -0.1157 0.7616 0.0169 -11.250 -0.5654 0.03542 0.03006 -0.1116 0.7606 0.0169 -11.000 -0.5659 0.03323 0.02765 -0.1087 0.7596 0.0165 -10.750 -0.5677 0.03151 0.02565 -0.1052 0.7588 0.0171 -10.500 -0.5608 0.02963 0.02353 -0.1028 0.7580 0.0172 -10.250 -0.5486 0.02814 0.02183 -0.1010 0.7573 0.0172 -10.000 -0.5404 0.02732 0.02079 -0.0983 0.7566 0.0176 -9.750 -0.5147 0.02547 0.01875 -0.0986 0.7559 0.0181 -9.500 -0.4928 0.02457 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0.8476 5.000 0.7873 0.01384 0.00955 -0.0456 0.6629 0.8487 5.250 0.8117 0.01365 0.00943 -0.0452 0.6580 0.8502 5.500 0.8425 0.01326 0.00906 -0.0460 0.6543 0.8513 5.750 0.8705 0.01296 0.00878 -0.0462 0.6493 0.8521 6.000 0.8941 0.01279 0.00869 -0.0457 0.6418 0.8530 6.250 0.9212 0.01252 0.00844 -0.0458 0.6335 0.8538 6.500 0.9469 0.01226 0.00818 -0.0456 0.6207 0.8546 6.750 0.9674 0.01209 0.00797 -0.0443 0.5994 0.8555 7.000 0.9819 0.01196 0.00778 -0.0417 0.5747 0.8567 7.250 0.9915 0.01203 0.00775 -0.0383 0.5447 0.8578 7.500 0.9923 0.01230 0.00790 -0.0332 0.5127 0.8592 8.000 0.9612 0.01344 0.00874 -0.0177 0.4482 0.8623 8.250 0.9481 0.01441 0.00961 -0.0115 0.4225 0.8637 8.500 0.9322 0.01598 0.01106 -0.0061 0.3941 0.8652 8.750 0.9168 0.01751 0.01241 -0.0006 0.3600 0.8669 9.000 0.9096 0.01881 0.01356 0.0035 0.3314 0.8678 9.250 0.9040 0.02013 0.01471 0.0073 0.2993 0.8686 9.500 0.8990 0.02150 0.01589 0.0108 0.2628 0.8691 9.750 0.8985 0.02277 0.01699 0.0135 0.2313 0.8696 10.000 0.8997 0.02404 0.01807 0.0160 0.1993 0.8699 10.250 0.9049 0.02517 0.01908 0.0178 0.1756 0.8702 10.500 0.9125 0.02623 0.02003 0.0193 0.1540 0.8704 10.750 0.9221 0.02725 0.02097 0.0204 0.1350 0.8707 11.000 0.9314 0.02841 0.02202 0.0214 0.1143 0.8710 11.250 0.9420 0.02954 0.02306 0.0222 0.0951 0.8713 11.500 0.9505 0.03086 0.02424 0.0231 0.0727 0.8715 11.750 0.9579 0.03232 0.02558 0.0240 0.0546 0.8717 12.000 0.9670 0.03372 0.02692 0.0247 0.0437 0.8719 12.250 0.9767 0.03514 0.02832 0.0253 0.0373 0.8721 12.500 0.9893 0.03641 0.02962 0.0255 0.0343 0.8723 12.750 0.9989 0.03794 0.03116 0.0259 0.0310 0.8724 13.000 1.0115 0.03926 0.03254 0.0261 0.0290 0.8726 13.250 1.0218 0.04083 0.03412 0.0262 0.0269 0.8730 13.500 1.0307 0.04252 0.03588 0.0264 0.0253 0.8732 13.750 1.0416 0.04412 0.03755 0.0265 0.0242 0.8735 14.000 1.0525 0.04572 0.03921 0.0264 0.0231 0.8736 14.250 1.0603 0.04764 0.04118 0.0265 0.0225 0.8736 14.500 1.0607 0.05021 0.04378 0.0269 0.0213 0.8736 14.750 1.0711 0.05198 0.04564 0.0267 0.0206 0.8736 15.000 1.0807 0.05383 0.04758 0.0265 0.0198 0.8737 15.250 1.0884 0.05585 0.04967 0.0264 0.0197 0.8737 15.500 1.0958 0.05800 0.05188 0.0261 0.0188 0.8737 15.750 1.1041 0.06006 0.05399 0.0257 0.0183 0.8737 16.000 1.1072 0.06258 0.05655 0.0256 0.0176 0.8737 16.250 1.1126 0.06481 0.05884 0.0255 0.0174 0.8739 16.500 1.1186 0.06723 0.06138 0.0251 0.0167 0.8741 16.750 1.1258 0.06938 0.06361 0.0249 0.0167 0.8744 17.000 1.1324 0.07181 0.06616 0.0243 0.0163 0.8748 17.250 1.1375 0.07439 0.06884 0.0237 0.0158 0.8750 17.500 1.1434 0.07683 0.07138 0.0231 0.0157 0.8751 17.750 1.1473 0.07955 0.07419 0.0225 0.0153 0.8750 18.000 1.1513 0.08238 0.07712 0.0216 0.0151 0.8750 18.250 1.1547 0.08524 0.08006 0.0208 0.0148 0.8749 18.500 1.1576 0.08817 0.08308 0.0200 0.0147 0.8749 18.750 1.1603 0.09118 0.08614 0.0189 0.0144 0.8749 19.000 1.1619 0.09421 0.08928 0.0181 0.0143 0.8748 19.250 1.1631 0.09708 0.09221 0.0177 0.0139 0.8748