GOE 493 AIRFOIL (goe493-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 493 AIRFOIL (goe493-il) Reynolds number: 200,000 Max Cl/Cd: 72.89 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe493-il-200000-n5.txt Download as CSV file: xf-goe493-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 493 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.5729 0.11031 0.10615 -0.0628 1.0000 0.0187
-15.500 -0.6252 0.09596 0.09158 -0.0701 1.0000 0.0185
-15.250 -0.6546 0.08709 0.08256 -0.0745 1.0000 0.0183
-15.000 -0.6757 0.08020 0.07554 -0.0779 1.0000 0.0183
-14.750 -0.6947 0.07417 0.06940 -0.0807 1.0000 0.0183
-14.500 -0.7119 0.06875 0.06387 -0.0831 1.0000 0.0185
-14.250 -0.7283 0.06384 0.05886 -0.0850 1.0000 0.0186
-14.000 -0.7437 0.05942 0.05435 -0.0864 1.0000 0.0186
-13.750 -0.7590 0.05541 0.05024 -0.0873 1.0000 0.0188
-13.500 -0.7743 0.05187 0.04662 -0.0875 1.0000 0.0189
-13.250 -0.7912 0.04872 0.04338 -0.0870 1.0000 0.0191
-13.000 -0.8096 0.04594 0.04053 -0.0856 1.0000 0.0192
-12.750 -0.8038 0.04226 0.03666 -0.0897 0.9963 0.0197
-12.500 -0.7942 0.03906 0.03327 -0.0936 0.9911 0.0203
-12.250 -0.7827 0.03629 0.03027 -0.0969 0.9859 0.0208
-12.000 -0.7748 0.03378 0.02768 -0.0993 0.9794 0.0213
-11.750 -0.7621 0.03178 0.02556 -0.1013 0.9739 0.0219
-11.500 -0.7536 0.03032 0.02399 -0.1010 0.9664 0.0226
-11.250 -0.7358 0.02890 0.02241 -0.1018 0.9618 0.0237
-11.000 -0.7203 0.02769 0.02104 -0.1015 0.9557 0.0250
-10.750 -0.7026 0.02637 0.01962 -0.1018 0.9505 0.0262
-10.500 -0.6778 0.02519 0.01835 -0.1030 0.9475 0.0280
-10.250 -0.6602 0.02425 0.01728 -0.1023 0.9419 0.0299
-10.000 -0.6399 0.02324 0.01617 -0.1022 0.9367 0.0319
-9.750 -0.6134 0.02230 0.01514 -0.1031 0.9336 0.0350
-9.500 -0.5852 0.02133 0.01411 -0.1043 0.9312 0.0392
-9.250 -0.5701 0.02075 0.01344 -0.1025 0.9237 0.0431
-9.000 -0.5453 0.01997 0.01263 -0.1028 0.9196 0.0489
-8.750 -0.5164 0.01926 0.01189 -0.1037 0.9167 0.0566
-8.500 -0.4927 0.01873 0.01133 -0.1034 0.9120 0.0646
-8.250 -0.4707 0.01831 0.01087 -0.1027 0.9062 0.0729
-8.000 -0.4421 0.01786 0.01035 -0.1032 0.9025 0.0826
-7.750 -0.4115 0.01739 0.00986 -0.1042 0.8996 0.0922
-7.500 -0.3916 0.01709 0.00952 -0.1029 0.8932 0.1000
-7.250 -0.3651 0.01678 0.00913 -0.1029 0.8884 0.1094
-7.000 -0.3362 0.01634 0.00868 -0.1034 0.8848 0.1180
-6.750 -0.3111 0.01605 0.00831 -0.1030 0.8798 0.1256
-6.500 -0.2887 0.01572 0.00799 -0.1022 0.8738 0.1336
-6.250 -0.2603 0.01538 0.00758 -0.1025 0.8697 0.1426
-6.000 -0.2331 0.01506 0.00723 -0.1026 0.8654 0.1524
-5.750 -0.2118 0.01479 0.00698 -0.1014 0.8586 0.1619
-5.500 -0.1843 0.01448 0.00664 -0.1015 0.8541 0.1736
-5.250 -0.1567 0.01419 0.00632 -0.1016 0.8497 0.1869
-5.000 -0.1352 0.01396 0.00611 -0.1005 0.8430 0.2002
-4.750 -0.1081 0.01366 0.00582 -0.1004 0.8381 0.2177
-4.500 -0.0818 0.01337 0.00556 -0.1003 0.8333 0.2371
-4.250 -0.0593 0.01315 0.00540 -0.0993 0.8265 0.2576
-4.000 -0.0319 0.01289 0.00517 -0.0993 0.8217 0.2837
-3.750 -0.0073 0.01267 0.00502 -0.0988 0.8158 0.3117
-3.500 0.0168 0.01248 0.00490 -0.0981 0.8094 0.3386
-3.250 0.0453 0.01229 0.00473 -0.0982 0.8048 0.3664
-3.000 0.0686 0.01217 0.00467 -0.0973 0.7979 0.3925
-2.750 0.0947 0.01204 0.00457 -0.0970 0.7918 0.4173
-2.500 0.1229 0.01193 0.00446 -0.0970 0.7867 0.4399
-2.250 0.1465 0.01188 0.00443 -0.0961 0.7794 0.4601
-2.000 0.1746 0.01178 0.00433 -0.0961 0.7739 0.4800
-1.750 0.1994 0.01173 0.00431 -0.0955 0.7670 0.4994
-1.500 0.2256 0.01167 0.00427 -0.0951 0.7604 0.5187
-1.250 0.2532 0.01160 0.00421 -0.0950 0.7549 0.5384
-1.000 0.2773 0.01158 0.00422 -0.0942 0.7472 0.5551
-0.750 0.3056 0.01152 0.00415 -0.0941 0.7414 0.5714
-0.500 0.3297 0.01150 0.00417 -0.0934 0.7339 0.5870
-0.250 0.3565 0.01146 0.00415 -0.0931 0.7275 0.6030
0.000 0.3820 0.01143 0.00416 -0.0925 0.7206 0.6203
0.250 0.4073 0.01140 0.00416 -0.0919 0.7127 0.6383
0.500 0.4325 0.01137 0.00417 -0.0913 0.7046 0.6569
0.750 0.4577 0.01134 0.00417 -0.0906 0.6955 0.6757
1.000 0.4815 0.01133 0.00421 -0.0897 0.6858 0.6954
1.250 0.5072 0.01131 0.00420 -0.0891 0.6768 0.7160
1.500 0.5301 0.01132 0.00428 -0.0880 0.6670 0.7381
1.750 0.5552 0.01133 0.00432 -0.0873 0.6593 0.7620
2.000 0.5791 0.01135 0.00441 -0.0864 0.6513 0.7862
2.250 0.6054 0.01137 0.00448 -0.0860 0.6446 0.8124
2.500 0.6314 0.01140 0.00461 -0.0855 0.6368 0.8406
2.750 0.6638 0.01145 0.00470 -0.0863 0.6297 0.8720
3.000 0.7013 0.01154 0.00488 -0.0884 0.6209 0.9067
3.250 0.7477 0.01167 0.00502 -0.0924 0.6132 0.9407
3.500 0.7909 0.01180 0.00520 -0.0959 0.6047 0.9763
3.750 0.8292 0.01199 0.00535 -0.0983 0.5971 1.0000
4.000 0.8481 0.01213 0.00551 -0.0966 0.5888 1.0000
4.250 0.8693 0.01229 0.00563 -0.0954 0.5812 1.0000
4.500 0.8887 0.01245 0.00581 -0.0938 0.5723 1.0000
4.750 0.9097 0.01263 0.00597 -0.0925 0.5640 1.0000
5.000 0.9288 0.01281 0.00615 -0.0908 0.5536 1.0000
5.250 0.9464 0.01300 0.00633 -0.0888 0.5403 1.0000
5.500 0.9629 0.01321 0.00651 -0.0866 0.5249 1.0000
5.750 0.9780 0.01344 0.00669 -0.0842 0.5077 1.0000
6.000 0.9925 0.01370 0.00690 -0.0816 0.4902 1.0000
6.250 1.0059 0.01397 0.00712 -0.0788 0.4726 1.0000
6.500 1.0171 0.01427 0.00738 -0.0757 0.4544 1.0000
6.750 1.0279 0.01461 0.00767 -0.0725 0.4337 1.0000
7.000 1.0362 0.01505 0.00800 -0.0690 0.4098 1.0000
7.250 1.0422 0.01560 0.00842 -0.0653 0.3812 1.0000
7.500 1.0494 0.01621 0.00891 -0.0619 0.3571 1.0000
7.750 1.0567 0.01689 0.00948 -0.0586 0.3335 1.0000
8.000 1.0644 0.01761 0.01011 -0.0556 0.3117 1.0000
8.250 1.0741 0.01831 0.01076 -0.0530 0.2904 1.0000
8.500 1.0818 0.01913 0.01149 -0.0502 0.2653 1.0000
8.750 1.0862 0.02016 0.01237 -0.0471 0.2264 1.0000
9.000 1.0797 0.02183 0.01368 -0.0429 0.1710 1.0000
9.250 1.0792 0.02336 0.01502 -0.0397 0.1388 1.0000
9.500 1.0819 0.02478 0.01632 -0.0370 0.1096 1.0000
9.750 1.0831 0.02636 0.01774 -0.0344 0.0847 1.0000
10.000 1.0868 0.02783 0.01914 -0.0321 0.0712 1.0000
10.250 1.0934 0.02917 0.02049 -0.0302 0.0622 1.0000
10.500 1.1003 0.03053 0.02187 -0.0285 0.0569 1.0000
10.750 1.1072 0.03193 0.02332 -0.0269 0.0529 1.0000
11.000 1.1124 0.03350 0.02491 -0.0252 0.0500 1.0000
11.250 1.1198 0.03495 0.02644 -0.0238 0.0477 1.0000
11.500 1.1263 0.03652 0.02808 -0.0225 0.0456 1.0000
11.750 1.1317 0.03822 0.02984 -0.0212 0.0440 1.0000
12.000 1.1347 0.04018 0.03185 -0.0199 0.0425 1.0000
12.250 1.1386 0.04214 0.03386 -0.0188 0.0413 1.0000
12.500 1.1444 0.04397 0.03581 -0.0179 0.0401 1.0000
12.750 1.1501 0.04587 0.03779 -0.0170 0.0387 1.0000
13.000 1.1543 0.04793 0.03994 -0.0162 0.0377 1.0000
13.250 1.1583 0.05008 0.04215 -0.0155 0.0366 1.0000
13.500 1.1606 0.05245 0.04456 -0.0149 0.0356 1.0000
13.750 1.1610 0.05503 0.04716 -0.0142 0.0345 1.0000
14.000 1.1673 0.05708 0.04933 -0.0138 0.0337 1.0000
14.250 1.1727 0.05924 0.05161 -0.0134 0.0328 1.0000
14.500 1.1777 0.06149 0.05395 -0.0130 0.0319 1.0000
14.750 1.1824 0.06381 0.05635 -0.0128 0.0308 1.0000
15.000 1.1863 0.06622 0.05882 -0.0127 0.0299 1.0000
15.250 1.1896 0.06872 0.06137 -0.0125 0.0291 1.0000
15.500 1.1930 0.07115 0.06379 -0.0122 0.0283 1.0000
15.750 1.1983 0.07355 0.06634 -0.0122 0.0276 1.0000
16.000 1.2027 0.07609 0.06903 -0.0123 0.0268 1.0000
16.250 1.2065 0.07870 0.07177 -0.0124 0.0260 1.0000
16.500 1.2096 0.08145 0.07462 -0.0127 0.0251 1.0000
16.750 1.2119 0.08434 0.07758 -0.0132 0.0243 1.0000
17.000 1.2149 0.08711 0.08041 -0.0136 0.0238 1.0000
17.250 1.2177 0.08987 0.08320 -0.0139 0.0232 1.0000
17.500 1.2192 0.09298 0.08645 -0.0145 0.0226 1.0000
17.750 1.2190 0.09642 0.09008 -0.0153 0.0220 1.0000
18.000 1.2183 0.09998 0.09381 -0.0163 0.0214 1.0000
18.250 1.2166 0.10376 0.09774 -0.0176 0.0207 1.0000
18.500 1.2152 0.10751 0.10163 -0.0189 0.0202 1.0000
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