XFOIL Version 6.96 Calculated polar for: GOE 632 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.4029 0.05880 0.05496 -0.0797 0.9541 0.0343 -9.250 -0.4213 0.05082 0.04662 -0.0824 0.9323 0.0342 -9.000 -0.4290 0.04460 0.03997 -0.0831 0.9140 0.0346 -8.750 -0.4024 0.04368 0.03900 -0.0846 0.9010 0.0351 -8.500 -0.3871 0.04121 0.03630 -0.0850 0.8866 0.0355 -8.250 -0.3777 0.03822 0.03300 -0.0841 0.8722 0.0359 -8.000 -0.3725 0.03494 0.02929 -0.0820 0.8583 0.0360 -7.750 -0.3646 0.03243 0.02641 -0.0795 0.8452 0.0363 -7.500 -0.3546 0.03025 0.02387 -0.0770 0.8334 0.0366 -7.250 -0.3416 0.02832 0.02157 -0.0748 0.8230 0.0370 -7.000 -0.3270 0.02663 0.01955 -0.0727 0.8125 0.0374 -6.750 -0.3100 0.02527 0.01788 -0.0708 0.8027 0.0381 -6.500 -0.2912 0.02395 0.01622 -0.0692 0.7934 0.0389 -6.250 -0.2715 0.02275 0.01471 -0.0677 0.7839 0.0396 -6.000 -0.2489 0.02168 0.01334 -0.0666 0.7754 0.0400 -5.750 -0.2262 0.02075 0.01223 -0.0656 0.7658 0.0404 -5.500 -0.2017 0.01995 0.01132 -0.0650 0.7576 0.0409 -5.250 -0.1782 0.01934 0.01065 -0.0642 0.7479 0.0415 -5.000 -0.1535 0.01878 0.00999 -0.0635 0.7395 0.0421 -4.750 -0.1291 0.01825 0.00938 -0.0628 0.7303 0.0429 -4.500 -0.1039 0.01772 0.00874 -0.0622 0.7221 0.0437 -4.250 -0.0793 0.01730 0.00824 -0.0615 0.7134 0.0452 -4.000 -0.0541 0.01686 0.00768 -0.0609 0.7058 0.0465 -3.750 -0.0298 0.01640 0.00720 -0.0601 0.6977 0.0476 -3.500 -0.0053 0.01605 0.00681 -0.0594 0.6908 0.0488 -3.250 0.0185 0.01574 0.00648 -0.0585 0.6830 0.0501 -3.000 0.0427 0.01544 0.00612 -0.0577 0.6763 0.0520 -2.750 0.0664 0.01517 0.00579 -0.0568 0.6693 0.0541 -2.500 0.0898 0.01491 0.00553 -0.0558 0.6624 0.0565 -2.250 0.1139 0.01474 0.00531 -0.0550 0.6562 0.0604 -2.000 0.1373 0.01454 0.00511 -0.0540 0.6493 0.0655 -1.750 0.1612 0.01438 0.00490 -0.0531 0.6432 0.0719 -1.500 0.1843 0.01418 0.00469 -0.0522 0.6369 0.0787 -1.250 0.2078 0.01404 0.00452 -0.0512 0.6303 0.0867 -1.000 0.2316 0.01389 0.00436 -0.0503 0.6247 0.0979 -0.750 0.2541 0.01369 0.00427 -0.0493 0.6183 0.1183 -0.500 0.2742 0.01326 0.00419 -0.0478 0.6122 0.2071 -0.250 0.3406 0.01134 0.00443 -0.0564 0.6059 0.7978 0.000 0.2994 0.01137 0.00416 -0.0418 0.6009 0.7088 0.500 0.4888 0.01297 0.00589 -0.0676 0.5848 0.9408 0.750 0.5238 0.01315 0.00599 -0.0689 0.5776 0.9474 1.000 0.5607 0.01335 0.00609 -0.0707 0.5711 0.9552 1.250 0.5996 0.01350 0.00620 -0.0730 0.5636 0.9618 1.500 0.6358 0.01362 0.00623 -0.0747 0.5566 0.9676 1.750 0.6717 0.01371 0.00629 -0.0765 0.5473 0.9733 2.000 0.7075 0.01375 0.00624 -0.0782 0.5381 0.9775 2.250 0.7346 0.01380 0.00626 -0.0782 0.5266 0.9808 2.500 0.7622 0.01386 0.00628 -0.0783 0.5170 0.9836 2.750 0.7944 0.01387 0.00623 -0.0794 0.5075 0.9861 3.000 0.8252 0.01391 0.00625 -0.0803 0.4980 0.9889 3.250 0.8558 0.01399 0.00627 -0.0811 0.4891 0.9922 3.500 0.8865 0.01403 0.00628 -0.0819 0.4787 0.9948 3.750 0.9148 0.01409 0.00631 -0.0823 0.4684 0.9968 4.250 0.9662 0.01431 0.00646 -0.0819 0.4477 0.9998 4.500 0.9863 0.01448 0.00660 -0.0806 0.4398 1.0000 4.750 1.0051 0.01465 0.00677 -0.0790 0.4312 1.0000 5.000 1.0233 0.01485 0.00694 -0.0772 0.4236 1.0000 5.250 1.0417 0.01504 0.00715 -0.0755 0.4155 1.0000 5.500 1.0590 0.01526 0.00735 -0.0737 0.4082 1.0000 5.750 1.0761 0.01547 0.00757 -0.0718 0.3989 1.0000 6.000 1.0923 0.01572 0.00781 -0.0697 0.3905 1.0000 6.250 1.1091 0.01594 0.00805 -0.0677 0.3829 1.0000 6.500 1.1243 0.01620 0.00831 -0.0655 0.3760 1.0000 6.750 1.1398 0.01644 0.00858 -0.0632 0.3671 1.0000 7.000 1.1529 0.01673 0.00888 -0.0606 0.3577 1.0000 7.250 1.1653 0.01702 0.00918 -0.0579 0.3472 1.0000 7.500 1.1772 0.01732 0.00949 -0.0550 0.3376 1.0000 7.750 1.1860 0.01767 0.00983 -0.0516 0.3267 1.0000 8.000 1.1957 0.01799 0.01018 -0.0484 0.3161 1.0000 8.250 1.2019 0.01835 0.01055 -0.0446 0.3047 1.0000 8.500 1.2027 0.01871 0.01090 -0.0397 0.2931 1.0000 8.750 1.2020 0.01913 0.01131 -0.0347 0.2791 1.0000 9.000 1.2009 0.01966 0.01180 -0.0298 0.2612 1.0000 9.250 1.1967 0.02039 0.01244 -0.0247 0.2385 1.0000 9.500 1.1881 0.02142 0.01333 -0.0193 0.2113 1.0000 9.750 1.1815 0.02258 0.01439 -0.0146 0.1926 1.0000 10.250 1.1756 0.02507 0.01679 -0.0072 0.1697 1.0000 10.500 1.1746 0.02641 0.01812 -0.0041 0.1617 1.0000 10.750 1.1772 0.02764 0.01939 -0.0017 0.1548 1.0000 11.000 1.1762 0.02920 0.02094 0.0009 0.1482 1.0000 11.250 1.1812 0.03044 0.02225 0.0028 0.1413 1.0000 11.500 1.1815 0.03209 0.02391 0.0049 0.1341 1.0000 11.750 1.1858 0.03353 0.02539 0.0065 0.1275 1.0000 12.000 1.1880 0.03518 0.02706 0.0081 0.1217 1.0000 12.250 1.1909 0.03685 0.02876 0.0095 0.1166 1.0000 12.500 1.1947 0.03850 0.03046 0.0108 0.1124 1.0000 12.750 1.1964 0.04039 0.03238 0.0120 0.1085 1.0000 13.000 1.1990 0.04225 0.03429 0.0131 0.1057 1.0000 13.250 1.2026 0.04408 0.03618 0.0140 0.1026 1.0000 13.500 1.2050 0.04606 0.03821 0.0149 0.1000 1.0000 13.750 1.2055 0.04830 0.04047 0.0156 0.0969 1.0000 14.000 1.2066 0.05052 0.04273 0.0163 0.0948 1.0000 14.250 1.2112 0.05244 0.04475 0.0169 0.0928 1.0000 14.500 1.2146 0.05452 0.04691 0.0174 0.0909 1.0000 14.750 1.2164 0.05681 0.04927 0.0178 0.0883 1.0000 15.000 1.2171 0.05926 0.05176 0.0182 0.0862 1.0000 15.250 1.2174 0.06179 0.05433 0.0184 0.0844 1.0000 15.500 1.2203 0.06411 0.05675 0.0186 0.0819 1.0000 15.750 1.2251 0.06624 0.05899 0.0187 0.0799 1.0000 16.000 1.2275 0.06867 0.06153 0.0188 0.0776 1.0000 16.250 1.2252 0.07176 0.06467 0.0185 0.0737 1.0000 16.500 1.2256 0.07455 0.06752 0.0184 0.0715 1.0000 16.750 1.2313 0.07678 0.06992 0.0182 0.0666 1.0000 17.000 1.2321 0.07966 0.07288 0.0178 0.0607 1.0000 17.250 1.2334 0.08248 0.07577 0.0173 0.0478 1.0000 17.500 1.2181 0.08761 0.08071 0.0162 0.0328 1.0000 17.750 1.2075 0.09212 0.08520 0.0152 0.0280 1.0000