XFOIL Version 6.96 Calculated polar for: GOE 16K AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.7470 0.07578 0.07252 -0.1670 0.9560 0.0246 -19.500 -0.7731 0.06890 0.06550 -0.1713 0.9557 0.0245 -19.250 -0.7902 0.06312 0.05960 -0.1752 0.9553 0.0246 -19.000 -0.8113 0.06001 0.05641 -0.1728 0.9499 0.0251 -18.750 -0.8385 0.05357 0.04983 -0.1762 0.9482 0.0250 -18.500 -0.8378 0.04998 0.04614 -0.1788 0.9472 0.0254 -18.250 -0.8530 0.04454 0.04057 -0.1825 0.9462 0.0261 -18.000 -0.8509 0.04129 0.03725 -0.1850 0.9455 0.0267 -17.750 -0.8490 0.03827 0.03413 -0.1870 0.9449 0.0269 -17.500 -0.8381 0.03626 0.03205 -0.1886 0.9444 0.0281 -17.250 -0.8285 0.03430 0.03001 -0.1899 0.9439 0.0284 -17.000 -0.8470 0.03252 0.02814 -0.1852 0.9375 0.0285 -16.750 -0.8365 0.03120 0.02673 -0.1850 0.9358 0.0290 -16.500 -0.8325 0.02939 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0.8298 0.3200 -2.250 0.3217 0.00937 0.00413 -0.1409 0.8289 0.3462 -2.000 0.3539 0.00931 0.00414 -0.1423 0.8278 0.3711 -1.750 0.3891 0.00926 0.00417 -0.1445 0.8267 0.3975 -1.500 0.3697 0.00937 0.00433 -0.1337 0.8237 0.4069 -1.250 0.3700 0.00938 0.00442 -0.1276 0.8207 0.4259 -1.000 0.3852 0.00934 0.00446 -0.1250 0.8189 0.4519 -0.750 0.4071 0.00914 0.00439 -0.1240 0.8167 0.4950 -0.500 0.4227 0.00878 0.00435 -0.1216 0.8151 0.5912 -0.250 0.5146 0.00872 0.00531 -0.1364 0.8156 0.8733 0.000 0.5581 0.00899 0.00558 -0.1400 0.8145 0.8895 0.250 0.5878 0.00925 0.00583 -0.1404 0.8130 0.9033 0.500 0.6260 0.00945 0.00600 -0.1429 0.8112 0.9091 0.750 0.6496 0.00967 0.00623 -0.1421 0.8098 0.9153 1.000 0.6710 0.01007 0.00665 -0.1406 0.8084 0.9183 1.250 0.6592 0.01044 0.00706 -0.1316 0.8055 0.9279 1.500 0.6948 0.01072 0.00734 -0.1336 0.8041 0.9292 1.750 0.7304 0.01090 0.00753 -0.1355 0.8020 0.9307 2.000 0.7721 0.01106 0.00768 -0.1387 0.8000 0.9327 2.250 0.8118 0.01106 0.00766 -0.1415 0.7972 0.9345 2.500 0.8536 0.01107 0.00765 -0.1450 0.7947 0.9364 2.750 0.8596 0.01149 0.00811 -0.1401 0.7912 0.9420 3.000 0.8786 0.01170 0.00835 -0.1381 0.7865 0.9440 3.250 0.9060 0.01174 0.00839 -0.1382 0.7825 0.9458 3.500 0.9380 0.01170 0.00831 -0.1393 0.7769 0.9477 3.750 0.9286 0.01220 0.00886 -0.1311 0.7704 0.9537 4.000 0.9585 0.01224 0.00888 -0.1317 0.7625 0.9552 4.250 0.9671 0.01261 0.00929 -0.1277 0.7560 0.9581 4.500 0.9712 0.01309 0.00980 -0.1227 0.7515 0.9639 4.750 0.9982 0.01316 0.00986 -0.1228 0.7430 0.9650 5.000 1.0198 0.01341 0.01015 -0.1219 0.7345 0.9668 5.250 1.0389 0.01373 0.01047 -0.1203 0.7232 0.9699 5.500 1.0536 0.01436 0.01108 -0.1179 0.7035 0.9758 5.750 1.0586 0.01514 0.01168 -0.1135 0.6624 0.9798 6.000 1.0408 0.01666 0.01298 -0.1045 0.6195 0.9855 6.250 1.0216 0.01838 0.01436 -0.0962 0.5490 0.9894 6.500 1.0269 0.01927 0.01517 -0.0924 0.5209 0.9922 6.750 0.9876 0.02176 0.01732 -0.0800 0.4549 0.9934 7.000 0.9737 0.02337 0.01873 -0.0725 0.4179 0.9939 7.250 0.9873 0.02358 0.01888 -0.0707 0.4011 0.9942 7.500 0.9992 0.02403 0.01925 -0.0686 0.3790 0.9947 7.750 1.0130 0.02449 0.01964 -0.0667 0.3593 0.9952 8.000 1.0227 0.02516 0.02019 -0.0643 0.3315 0.9957 8.250 1.0183 0.02652 0.02119 -0.0596 0.2670 0.9965 8.500 1.0299 0.02714 0.02171 -0.0574 0.2435 0.9970 8.750 1.0401 0.02784 0.02230 -0.0551 0.2202 0.9975 9.000 1.0447 0.02883 0.02309 -0.0519 0.1849 0.9980 9.250 1.0537 0.02960 0.02370 -0.0494 0.1600 0.9983 9.500 1.0698 0.03001 0.02415 -0.0480 0.1570 0.9985 9.750 1.0818 0.03063 0.02470 -0.0459 0.1434 0.9987 10.000 1.0929 0.03131 0.02532 -0.0438 0.1307 0.9988 10.250 1.1069 0.03184 0.02585 -0.0421 0.1255 0.9989 10.500 1.1176 0.03254 0.02648 -0.0399 0.1118 0.9990 10.750 1.1289 0.03322 0.02708 -0.0379 0.0996 0.9991 11.000 1.1419 0.03383 0.02768 -0.0361 0.0944 0.9992 11.250 1.1544 0.03447 0.02833 -0.0343 0.0895 0.9992 11.500 1.1655 0.03520 0.02902 -0.0323 0.0816 0.9993 11.750 1.1781 0.03585 0.02966 -0.0305 0.0773 0.9993 12.000 1.1901 0.03655 0.03034 -0.0288 0.0718 0.9993 12.250 1.2027 0.03723 0.03104 -0.0271 0.0691 0.9994 12.500 1.2127 0.03809 0.03187 -0.0251 0.0638 0.9994 12.750 1.2242 0.03885 0.03262 -0.0233 0.0587 0.9994 13.000 1.2354 0.03964 0.03342 -0.0215 0.0557 0.9994 13.250 1.2478 0.04034 0.03414 -0.0200 0.0533 0.9994 13.500 1.2572 0.04129 0.03507 -0.0181 0.0493 0.9994 13.750 1.2679 0.04215 0.03594 -0.0164 0.0455 0.9994 14.000 1.2785 0.04303 0.03684 -0.0146 0.0437 0.9995 14.250 1.2886 0.04394 0.03774 -0.0130 0.0399 0.9995 14.500 1.2965 0.04505 0.03886 -0.0111 0.0376 0.9995 14.750 1.3057 0.04608 0.03992 -0.0093 0.0353 0.9995 15.000 1.3145 0.04715 0.04099 -0.0076 0.0326 0.9995 15.250 1.3220 0.04831 0.04217 -0.0059 0.0306 0.9995 15.500 1.3304 0.04944 0.04333 -0.0043 0.0298 0.9995 15.750 1.3384 0.05062 0.04456 -0.0026 0.0289 0.9995 16.000 1.3429 0.05209 0.04604 -0.0007 0.0270 0.9995 16.250 1.3505 0.05336 0.04736 0.0008 0.0262 0.9995 16.500 1.3578 0.05465 0.04871 0.0023 0.0255 0.9995 16.750 1.3649 0.05601 0.05010 0.0037 0.0246 0.9995 17.000 1.3707 0.05747 0.05160 0.0052 0.0240 0.9995 17.250 1.3695 0.05961 0.05379 0.0071 0.0229 0.9995 17.500 1.3738 0.06127 0.05551 0.0085 0.0226 0.9995 17.750 1.3811 0.06269 0.05700 0.0097 0.0215 0.9995 18.000 1.3848 0.06445 0.05882 0.0109 0.0218 0.9995 18.250 1.3874 0.06635 0.06078 0.0122 0.0210 0.9995 18.500 1.3853 0.06874 0.06318 0.0135 0.0191 0.9994 18.750 1.3903 0.07049 0.06502 0.0145 0.0201 0.9994 19.000 1.3965 0.07212 0.06669 0.0153 0.0186 0.9994 19.250 1.3976 0.07429 0.06891 0.0162 0.0179 0.9994