GOE 683 AIRFOIL (goe683-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
Details | Polar file |
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Airfoil: GOE 683 AIRFOIL (goe683-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.05 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe683-il-1000000-n5.txt Download as CSV file: xf-goe683-il-1000000-n5.csv |
XFOIL Version 6.96 Calculated polar for: GOE 683 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1608 0.06610 0.06207 -0.0748 1.0000 0.0328 -19.500 -1.1823 0.06028 0.05612 -0.0776 1.0000 0.0330 -19.250 -1.1993 0.05515 0.05087 -0.0798 1.0000 0.0331 -19.000 -1.2083 0.05113 0.04675 -0.0815 1.0000 0.0337 -18.750 -1.2192 0.04701 0.04252 -0.0830 1.0000 0.0337 -18.500 -1.2232 0.04383 0.03925 -0.0839 1.0000 0.0340 -18.250 -1.2305 0.04048 0.03579 -0.0846 1.0000 0.0340 -18.000 -1.2272 0.03837 0.03360 -0.0847 1.0000 0.0345 -17.750 -1.2310 0.03572 0.03089 -0.0846 1.0000 0.0349 -17.500 -1.2312 0.03358 0.02868 -0.0841 1.0000 0.0352 -17.250 -1.2300 0.03171 0.02675 -0.0833 1.0000 0.0356 -17.000 -1.2274 0.03009 0.02508 -0.0822 1.0000 0.0358 -16.750 -1.2233 0.02869 0.02364 -0.0808 1.0000 0.0363 -16.500 -1.2181 0.02747 0.02236 -0.0792 1.0000 0.0368 -16.250 -1.2123 0.02637 0.02121 -0.0775 1.0000 0.0372 -16.000 -1.2057 0.02539 0.02019 -0.0755 1.0000 0.0375 -15.750 -1.1987 0.02449 0.01924 -0.0735 1.0000 0.0379 -15.500 -1.1894 0.02375 0.01845 -0.0715 1.0000 0.0384 -15.250 -1.1617 0.02292 0.01757 -0.0729 0.9987 0.0389 -15.000 -1.1379 0.02195 0.01658 -0.0738 0.9958 0.0396 -14.750 -1.1350 0.02113 0.01573 -0.0701 0.9722 0.0400 -14.500 -1.0861 0.02027 0.01483 -0.0755 0.9425 0.0408 -14.250 -1.0255 0.01950 0.01396 -0.0832 0.9133 0.0420 -14.000 -0.9751 0.01894 0.01325 -0.0887 0.8801 0.0430 -13.750 -0.9322 0.01846 0.01263 -0.0927 0.8583 0.0437 -13.250 -0.8742 0.01747 0.01147 -0.0951 0.8235 0.0453 -13.000 -0.8505 0.01706 0.01100 -0.0950 0.8098 0.0462 -12.750 -0.8275 0.01671 0.01056 -0.0947 0.7965 0.0470 -12.500 -0.8062 0.01637 0.01015 -0.0940 0.7836 0.0477 -12.250 -0.7852 0.01608 0.00978 -0.0932 0.7707 0.0485 -12.000 -0.7651 0.01580 0.00941 -0.0921 0.7553 0.0490 -11.750 -0.7464 0.01547 0.00902 -0.0908 0.7405 0.0498 -11.500 -0.7273 0.01519 0.00868 -0.0894 0.7261 0.0508 -11.250 -0.7082 0.01493 0.00836 -0.0880 0.7137 0.0516 -11.000 -0.6889 0.01471 0.00808 -0.0866 0.7004 0.0527 -10.750 -0.6693 0.01448 0.00780 -0.0852 0.6884 0.0535 -10.500 -0.6496 0.01429 0.00753 -0.0837 0.6781 0.0543 -10.250 -0.6301 0.01407 0.00726 -0.0823 0.6677 0.0549 -10.000 -0.6115 0.01384 0.00698 -0.0806 0.6584 0.0559 -9.750 -0.5921 0.01362 0.00674 -0.0791 0.6498 0.0569 -9.500 -0.5724 0.01344 0.00651 -0.0776 0.6415 0.0580 -9.250 -0.5520 0.01326 0.00630 -0.0761 0.6337 0.0589 -9.000 -0.5313 0.01310 0.00610 -0.0748 0.6267 0.0601 -8.500 -0.4906 0.01276 0.00568 -0.0718 0.6148 0.0618 -8.250 -0.4706 0.01257 0.00547 -0.0703 0.6079 0.0629 -8.000 -0.4506 0.01242 0.00528 -0.0687 0.6007 0.0640 -7.750 -0.4294 0.01226 0.00510 -0.0674 0.5956 0.0652 -7.500 -0.4077 0.01212 0.00494 -0.0661 0.5901 0.0664 -7.250 -0.3863 0.01200 0.00478 -0.0648 0.5841 0.0674 -7.000 -0.3648 0.01188 0.00463 -0.0634 0.5784 0.0682 -6.750 -0.3436 0.01171 0.00444 -0.0620 0.5725 0.0696 -6.500 -0.3226 0.01156 0.00427 -0.0606 0.5655 0.0714 -6.250 -0.3014 0.01144 0.00412 -0.0592 0.5599 0.0725 -6.000 -0.2793 0.01131 0.00398 -0.0580 0.5548 0.0742 -5.750 -0.2572 0.01120 0.00385 -0.0567 0.5486 0.0754 -5.500 -0.2361 0.01109 0.00371 -0.0553 0.5419 0.0774 -5.250 -0.2140 0.01096 0.00357 -0.0540 0.5358 0.0796 -5.000 -0.1921 0.01084 0.00343 -0.0527 0.5280 0.0822 -4.750 -0.1706 0.01073 0.00331 -0.0513 0.5215 0.0865 -4.500 -0.1491 0.01053 0.00316 -0.0500 0.5155 0.0968 -4.250 -0.1295 0.01025 0.00302 -0.0484 0.5084 0.1302 -4.000 -0.1076 0.01016 0.00295 -0.0471 0.5011 0.1420 -3.750 -0.0848 0.01009 0.00287 -0.0460 0.4942 0.1493 -3.500 -0.0627 0.01005 0.00281 -0.0447 0.4860 0.1547 -3.250 -0.0398 0.00998 0.00275 -0.0436 0.4796 0.1605 -3.000 -0.0170 0.00994 0.00270 -0.0424 0.4730 0.1658 -2.750 0.0052 0.00992 0.00265 -0.0412 0.4664 0.1707 -2.500 0.0283 0.00986 0.00261 -0.0401 0.4610 0.1766 -2.250 0.0510 0.00983 0.00257 -0.0389 0.4545 0.1825 -2.000 0.0727 0.00980 0.00254 -0.0376 0.4477 0.1903 -1.750 0.0958 0.00975 0.00251 -0.0365 0.4433 0.1996 -1.500 0.1184 0.00969 0.00249 -0.0354 0.4383 0.2106 -1.250 0.1405 0.00967 0.00247 -0.0341 0.4328 0.2206 -1.000 0.1627 0.00964 0.00246 -0.0328 0.4279 0.2327 -0.750 0.1854 0.00958 0.00245 -0.0317 0.4235 0.2489 -0.500 0.2080 0.00954 0.00245 -0.0306 0.4194 0.2612 -0.250 0.2301 0.00953 0.00246 -0.0293 0.4151 0.2747 0.000 0.2518 0.00952 0.00247 -0.0280 0.4104 0.2900 0.250 0.2748 0.00948 0.00248 -0.0269 0.4069 0.3043 0.500 0.2970 0.00943 0.00249 -0.0257 0.4025 0.3248 0.750 0.3181 0.00937 0.00251 -0.0243 0.3977 0.3534 1.000 0.3374 0.00927 0.00255 -0.0226 0.3927 0.3996 1.250 0.3581 0.00915 0.00257 -0.0211 0.3886 0.4433 1.500 0.3771 0.00902 0.00260 -0.0192 0.3850 0.4938 1.750 0.3964 0.00897 0.00264 -0.0174 0.3813 0.5226 2.000 0.4133 0.00892 0.00269 -0.0151 0.3772 0.5593 2.250 0.4285 0.00886 0.00274 -0.0124 0.3740 0.5985 2.500 0.4424 0.00875 0.00278 -0.0094 0.3709 0.6407 2.750 0.4532 0.00865 0.00282 -0.0057 0.3674 0.6833 3.000 0.4573 0.00850 0.00286 -0.0006 0.3639 0.7357 3.500 0.6248 0.00904 0.00390 -0.0246 0.3518 0.9021 3.750 0.6461 0.00920 0.00404 -0.0232 0.3477 0.9115 4.000 0.6650 0.00942 0.00424 -0.0212 0.3439 0.9213 4.250 0.6850 0.00966 0.00447 -0.0195 0.3398 0.9282 4.500 0.7157 0.00993 0.00473 -0.0200 0.3362 0.9329 4.750 0.7198 0.01001 0.00482 -0.0149 0.3329 0.9406 5.000 0.7544 0.01027 0.00505 -0.0164 0.3283 0.9420 5.250 0.7883 0.01056 0.00531 -0.0178 0.3236 0.9437 5.500 0.8229 0.01082 0.00557 -0.0193 0.3201 0.9461 5.750 0.8472 0.01103 0.00577 -0.0186 0.3166 0.9498 6.000 0.8577 0.01124 0.00597 -0.0150 0.3122 0.9553 6.250 0.8914 0.01152 0.00622 -0.0164 0.3064 0.9564 6.500 0.9219 0.01170 0.00640 -0.0172 0.3023 0.9575 6.750 0.9450 0.01186 0.00655 -0.0164 0.2968 0.9588 7.000 0.9649 0.01205 0.00671 -0.0151 0.2922 0.9605 7.250 0.9817 0.01222 0.00688 -0.0130 0.2885 0.9629 7.500 0.9751 0.01236 0.00704 -0.0061 0.2863 0.9679 7.750 1.0004 0.01252 0.00720 -0.0059 0.2821 0.9684 8.000 1.0244 0.01274 0.00741 -0.0056 0.2766 0.9691 8.250 1.0481 0.01298 0.00764 -0.0053 0.2722 0.9699 8.500 1.0707 0.01321 0.00786 -0.0047 0.2665 0.9708 8.750 1.0901 0.01352 0.00815 -0.0036 0.2601 0.9718 9.000 1.1087 0.01382 0.00845 -0.0024 0.2546 0.9731 9.250 1.1250 0.01416 0.00877 -0.0008 0.2479 0.9746 9.500 1.1359 0.01459 0.00919 0.0017 0.2423 0.9767 9.750 1.1332 0.01511 0.00971 0.0071 0.2373 0.9805 10.000 1.1526 0.01559 0.01017 0.0076 0.2290 0.9810 10.250 1.1716 0.01609 0.01066 0.0081 0.2220 0.9815 10.500 1.1891 0.01669 0.01124 0.0087 0.2139 0.9822 10.750 1.2057 0.01735 0.01189 0.0094 0.2066 0.9829 11.000 1.2203 0.01811 0.01262 0.0103 0.1983 0.9837 11.250 1.2286 0.01924 0.01370 0.0117 0.1837 0.9847 11.500 1.2285 0.02100 0.01535 0.0135 0.1602 0.9863 11.750 1.2210 0.02314 0.01738 0.0161 0.1390 0.9878 12.000 1.2208 0.02487 0.01907 0.0180 0.1289 0.9889 12.250 1.2272 0.02618 0.02040 0.0193 0.1251 0.9899 12.500 1.2310 0.02767 0.02190 0.0209 0.1214 0.9908 12.750 1.2340 0.02914 0.02340 0.0226 0.1187 0.9918 13.000 1.2427 0.03051 0.02481 0.0234 0.1168 0.9925 13.250 1.2523 0.03198 0.02631 0.0236 0.1145 0.9928 13.500 1.2624 0.03341 0.02779 0.0238 0.1137 0.9931 13.750 1.2659 0.03543 0.02982 0.0243 0.1103 0.9935 14.000 1.2705 0.03736 0.03179 0.0246 0.1079 0.9939 14.250 1.2768 0.03916 0.03363 0.0249 0.1061 0.9942 14.500 1.2846 0.04085 0.03537 0.0251 0.1049 0.9946 14.750 1.2918 0.04260 0.03718 0.0253 0.1040 0.9949 15.000 1.2978 0.04448 0.03911 0.0255 0.1033 0.9953 15.250 1.2999 0.04673 0.04140 0.0258 0.1010 0.9956 15.500 1.3036 0.04885 0.04356 0.0260 0.0998 0.9959 15.750 1.3047 0.05128 0.04604 0.0261 0.0985 0.9962 16.000 1.3056 0.05385 0.04866 0.0261 0.0972 0.9966 16.250 1.3072 0.05640 0.05126 0.0259 0.0954 0.9969 16.500 1.3113 0.05864 0.05356 0.0258 0.0943 0.9972 16.750 1.3148 0.06090 0.05588 0.0258 0.0936 0.9974 17.000 1.3164 0.06341 0.05845 0.0257 0.0920 0.9977 17.250 1.3163 0.06612 0.06120 0.0255 0.0898 0.9979 17.500 1.3108 0.06946 0.06455 0.0253 0.0859 0.9981 17.750 1.3100 0.07234 0.06748 0.0250 0.0833 0.9983 18.000 1.3058 0.07561 0.07077 0.0246 0.0782 0.9984 18.250 1.3004 0.07909 0.07427 0.0242 0.0745 0.9986 18.500 1.2888 0.08333 0.07852 0.0235 0.0684 0.9988 18.750 1.2831 0.08692 0.08212 0.0229 0.0648 0.9989 |
Polar data table (+)
Polar graphs
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