GOE 534 AIRFOIL (goe534-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 534 AIRFOIL (goe534-il) Reynolds number: 200,000 Max Cl/Cd: 67.37 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe534-il-200000-n5.txt Download as CSV file: xf-goe534-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 534 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6935 0.04695 0.04234 -0.0696 1.0000 0.0403
-11.250 -0.7185 0.03877 0.03393 -0.0780 1.0000 0.0404
-11.000 -0.7136 0.03437 0.02936 -0.0826 1.0000 0.0408
-10.750 -0.7033 0.03182 0.02668 -0.0841 1.0000 0.0412
-10.500 -0.6782 0.02964 0.02435 -0.0871 0.9963 0.0418
-10.250 -0.6418 0.02759 0.02211 -0.0914 0.9870 0.0427
-10.000 -0.6075 0.02579 0.02009 -0.0947 0.9772 0.0437
-9.750 -0.5737 0.02432 0.01847 -0.0973 0.9676 0.0448
-9.500 -0.5413 0.02341 0.01752 -0.0989 0.9558 0.0459
-9.250 -0.5075 0.02247 0.01648 -0.1007 0.9439 0.0472
-9.000 -0.4729 0.02146 0.01532 -0.1026 0.9315 0.0488
-8.750 -0.4361 0.02071 0.01450 -0.1045 0.9185 0.0503
-8.500 -0.4002 0.02011 0.01382 -0.1062 0.9030 0.0521
-8.250 -0.3652 0.01937 0.01293 -0.1076 0.8861 0.0546
-8.000 -0.3308 0.01904 0.01252 -0.1087 0.8685 0.0570
-7.750 -0.2992 0.01856 0.01185 -0.1092 0.8508 0.0607
-7.500 -0.2691 0.01831 0.01146 -0.1093 0.8339 0.0642
-7.250 -0.2406 0.01801 0.01097 -0.1091 0.8184 0.0678
-7.000 -0.2130 0.01779 0.01057 -0.1087 0.8032 0.0713
-6.750 -0.1861 0.01750 0.01011 -0.1082 0.7889 0.0744
-6.500 -0.1593 0.01729 0.00980 -0.1077 0.7758 0.0771
-6.250 -0.1324 0.01707 0.00938 -0.1071 0.7628 0.0802
-6.000 -0.1061 0.01678 0.00899 -0.1066 0.7499 0.0826
-5.750 -0.0796 0.01657 0.00871 -0.1060 0.7375 0.0852
-5.500 -0.0530 0.01634 0.00837 -0.1054 0.7246 0.0878
-5.250 -0.0261 0.01616 0.00800 -0.1048 0.7122 0.0901
-5.000 -0.0001 0.01583 0.00765 -0.1041 0.6991 0.0924
-4.750 0.0265 0.01561 0.00740 -0.1035 0.6852 0.0949
-4.500 0.0532 0.01543 0.00712 -0.1029 0.6717 0.0977
-4.250 0.0800 0.01530 0.00683 -0.1022 0.6571 0.1001
-4.000 0.1061 0.01498 0.00652 -0.1016 0.6412 0.1025
-3.750 0.1326 0.01479 0.00627 -0.1009 0.6252 0.1047
-3.500 0.1591 0.01462 0.00603 -0.1003 0.6091 0.1068
-3.250 0.1856 0.01448 0.00578 -0.0995 0.5929 0.1084
-3.000 0.2120 0.01436 0.00554 -0.0988 0.5776 0.1100
-2.750 0.2385 0.01427 0.00534 -0.0981 0.5629 0.1114
-2.500 0.2649 0.01412 0.00514 -0.0975 0.5492 0.1132
-2.250 0.2913 0.01404 0.00499 -0.0969 0.5366 0.1150
-2.000 0.3178 0.01400 0.00486 -0.0962 0.5240 0.1172
-1.750 0.3447 0.01395 0.00475 -0.0956 0.5121 0.1197
-1.500 0.3713 0.01396 0.00465 -0.0950 0.5015 0.1228
-1.250 0.3983 0.01389 0.00458 -0.0945 0.4913 0.1274
-1.000 0.4250 0.01389 0.00452 -0.0939 0.4825 0.1346
-0.750 0.4522 0.01380 0.00449 -0.0935 0.4736 0.1488
-0.500 0.4787 0.01373 0.00449 -0.0929 0.4649 0.1782
-0.250 0.5056 0.01367 0.00453 -0.0925 0.4567 0.2168
0.000 0.5324 0.01367 0.00459 -0.0920 0.4485 0.2481
0.250 0.5591 0.01374 0.00466 -0.0914 0.4410 0.2730
0.500 0.5861 0.01378 0.00474 -0.0909 0.4325 0.2938
0.750 0.6125 0.01389 0.00482 -0.0903 0.4245 0.3124
1.000 0.6394 0.01396 0.00493 -0.0898 0.4165 0.3326
1.250 0.6658 0.01406 0.00504 -0.0892 0.4087 0.3539
1.500 0.6922 0.01417 0.00517 -0.0886 0.4012 0.3713
1.750 0.7185 0.01428 0.00530 -0.0880 0.3927 0.3880
2.000 0.7443 0.01442 0.00542 -0.0873 0.3848 0.4037
2.250 0.7708 0.01453 0.00555 -0.0867 0.3762 0.4173
2.500 0.7963 0.01469 0.00568 -0.0860 0.3685 0.4326
2.750 0.8224 0.01481 0.00585 -0.0854 0.3603 0.4485
3.000 0.8477 0.01497 0.00600 -0.0847 0.3517 0.4650
3.250 0.8733 0.01511 0.00617 -0.0840 0.3433 0.4819
3.500 0.8984 0.01528 0.00635 -0.0833 0.3349 0.4995
3.750 0.9236 0.01543 0.00653 -0.0826 0.3271 0.5163
4.000 0.9484 0.01560 0.00672 -0.0819 0.3185 0.5338
4.250 0.9726 0.01577 0.00691 -0.0810 0.3108 0.5532
4.500 0.9977 0.01592 0.00713 -0.0803 0.3025 0.5796
4.750 1.0220 0.01607 0.00736 -0.0796 0.2953 0.6229
5.250 1.0867 0.01619 0.00789 -0.0814 0.2793 1.0000
5.500 1.1110 0.01649 0.00817 -0.0806 0.2725 1.0000
5.750 1.1340 0.01685 0.00846 -0.0797 0.2659 1.0000
6.000 1.1568 0.01722 0.00878 -0.0787 0.2602 1.0000
6.250 1.1800 0.01756 0.00912 -0.0778 0.2542 1.0000
6.500 1.2018 0.01796 0.00947 -0.0768 0.2487 1.0000
6.750 1.2236 0.01837 0.00984 -0.0757 0.2439 1.0000
7.000 1.2459 0.01874 0.01023 -0.0747 0.2389 1.0000
7.250 1.2670 0.01916 0.01062 -0.0736 0.2340 1.0000
7.500 1.2865 0.01965 0.01106 -0.0722 0.2296 1.0000
7.750 1.3078 0.02005 0.01150 -0.0711 0.2255 1.0000
8.000 1.3280 0.02047 0.01195 -0.0699 0.2211 1.0000
8.250 1.3467 0.02096 0.01241 -0.0685 0.2168 1.0000
8.500 1.3635 0.02153 0.01294 -0.0669 0.2130 1.0000
8.750 1.3822 0.02196 0.01344 -0.0655 0.2092 1.0000
9.000 1.3987 0.02244 0.01397 -0.0637 0.2053 1.0000
9.250 1.4131 0.02299 0.01452 -0.0617 0.2015 1.0000
9.500 1.4256 0.02364 0.01515 -0.0596 0.1981 1.0000
9.750 1.4401 0.02423 0.01579 -0.0578 0.1946 1.0000
10.000 1.4546 0.02483 0.01646 -0.0560 0.1908 1.0000
10.250 1.4670 0.02553 0.01719 -0.0542 0.1870 1.0000
10.500 1.4773 0.02637 0.01803 -0.0522 0.1836 1.0000
10.750 1.4886 0.02721 0.01892 -0.0505 0.1802 1.0000
11.000 1.5008 0.02804 0.01983 -0.0490 0.1764 1.0000
11.250 1.5107 0.02903 0.02087 -0.0475 0.1726 1.0000
11.500 1.5184 0.03019 0.02205 -0.0459 0.1694 1.0000
11.750 1.5267 0.03141 0.02332 -0.0446 0.1663 1.0000
12.000 1.5366 0.03260 0.02460 -0.0434 0.1628 1.0000
12.250 1.5442 0.03398 0.02605 -0.0423 0.1595 1.0000
12.500 1.5495 0.03559 0.02770 -0.0413 0.1564 1.0000
12.750 1.5538 0.03736 0.02950 -0.0404 0.1537 1.0000
13.000 1.5610 0.03898 0.03123 -0.0397 0.1506 1.0000
13.250 1.5660 0.04083 0.03318 -0.0390 0.1476 1.0000
13.500 1.5690 0.04292 0.03533 -0.0385 0.1448 1.0000
13.750 1.5695 0.04529 0.03773 -0.0381 0.1423 1.0000
14.000 1.5718 0.04760 0.04012 -0.0378 0.1399 1.0000
14.250 1.5740 0.04998 0.04262 -0.0376 0.1372 1.0000
14.500 1.5738 0.05268 0.04541 -0.0376 0.1344 1.0000
14.750 1.5720 0.05563 0.04842 -0.0378 0.1319 1.0000
15.000 1.5684 0.05885 0.05168 -0.0382 0.1297 1.0000
15.250 1.5673 0.06192 0.05486 -0.0386 0.1274 1.0000
15.500 1.5655 0.06520 0.05826 -0.0391 0.1250 1.0000
15.750 1.5620 0.06874 0.06190 -0.0399 0.1227 1.0000
16.000 1.5576 0.07243 0.06566 -0.0408 0.1206 1.0000
16.250 1.5528 0.07623 0.06950 -0.0417 0.1186 1.0000
16.500 1.5491 0.07997 0.07332 -0.0427 0.1168 1.0000
16.750 1.5440 0.08403 0.07753 -0.0439 0.1147 1.0000
17.000 1.5379 0.08829 0.08191 -0.0453 0.1127 1.0000
17.250 1.5320 0.09257 0.08627 -0.0468 0.1107 1.0000
17.500 1.5266 0.09676 0.09052 -0.0482 0.1089 1.0000
17.750 1.5239 0.10049 0.09425 -0.0495 0.1072 1.0000
18.000 1.5166 0.10516 0.09906 -0.0513 0.1055 1.0000
18.250 1.5073 0.11028 0.10433 -0.0535 0.1035 1.0000
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Polar data table (+)
Polar graphs
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