GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 553 AIRFOIL (goe553-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.49 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe553-il-1000000.txt Download as CSV file: xf-goe553-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 553 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2210 0.09843 0.09686 -0.0450 0.9987 0.0257
-11.000 -0.2227 0.09215 0.09058 -0.0483 0.9909 0.0258
-10.750 -0.3124 0.09877 0.09709 -0.0418 1.0000 0.0257
-10.500 -0.1992 0.08254 0.08095 -0.0555 0.9688 0.0263
-10.250 -0.1636 0.07785 0.07620 -0.0634 0.9529 0.0267
-10.000 -0.1238 0.07155 0.06978 -0.0743 0.9217 0.0275
-9.750 -0.3924 0.05333 0.05165 -0.0765 0.9751 0.0263
-9.500 -0.4313 0.02676 0.02361 -0.1131 0.9261 0.0252
-9.250 -0.4129 0.02493 0.02133 -0.1134 0.8936 0.0257
-9.000 -0.4054 0.02152 0.01739 -0.1125 0.8602 0.0261
-8.750 -0.3869 0.02034 0.01598 -0.1115 0.8245 0.0264
-8.500 -0.3663 0.01977 0.01520 -0.1105 0.7856 0.0267
-8.250 -0.3445 0.01929 0.01453 -0.1096 0.7502 0.0270
-8.000 -0.3218 0.01873 0.01379 -0.1089 0.7225 0.0273
-7.750 -0.2985 0.01809 0.01297 -0.1084 0.7021 0.0276
-7.500 -0.2745 0.01735 0.01207 -0.1079 0.6871 0.0279
-7.250 -0.2499 0.01661 0.01116 -0.1075 0.6752 0.0283
-7.000 -0.2248 0.01603 0.01042 -0.1070 0.6646 0.0288
-6.750 -0.1989 0.01543 0.00969 -0.1067 0.6563 0.0292
-6.500 -0.1731 0.01483 0.00895 -0.1063 0.6482 0.0295
-6.250 -0.1465 0.01436 0.00837 -0.1061 0.6412 0.0297
-6.000 -0.1196 0.01402 0.00793 -0.1058 0.6344 0.0299
-5.750 -0.0945 0.01305 0.00683 -0.1054 0.6279 0.0304
-5.500 -0.0682 0.01233 0.00610 -0.1051 0.6229 0.0308
-5.250 -0.0413 0.01193 0.00567 -0.1049 0.6174 0.0312
-5.000 -0.0143 0.01168 0.00538 -0.1046 0.6119 0.0318
-4.750 0.0132 0.01140 0.00508 -0.1044 0.6072 0.0323
-4.500 0.0407 0.01110 0.00475 -0.1042 0.6023 0.0328
-4.250 0.0680 0.01081 0.00443 -0.1040 0.5973 0.0332
-4.000 0.0951 0.01059 0.00414 -0.1037 0.5923 0.0337
-3.750 0.1231 0.01033 0.00387 -0.1036 0.5883 0.0341
-3.500 0.1510 0.01012 0.00364 -0.1034 0.5833 0.0345
-3.250 0.1786 0.00995 0.00343 -0.1032 0.5781 0.0349
-3.000 0.2056 0.00955 0.00299 -0.1030 0.5733 0.0358
-2.750 0.2337 0.00935 0.00279 -0.1029 0.5688 0.0367
-2.500 0.2618 0.00922 0.00264 -0.1028 0.5637 0.0378
-2.250 0.2896 0.00912 0.00251 -0.1026 0.5582 0.0388
-2.000 0.3180 0.00900 0.00237 -0.1026 0.5532 0.0397
-1.750 0.3462 0.00887 0.00222 -0.1025 0.5472 0.0407
-1.500 0.3739 0.00875 0.00206 -0.1023 0.5409 0.0428
-1.250 0.4023 0.00865 0.00196 -0.1022 0.5347 0.0450
-1.000 0.4304 0.00858 0.00186 -0.1021 0.5271 0.0480
-0.750 0.4584 0.00849 0.00177 -0.1019 0.5196 0.0562
-0.500 0.4856 0.00816 0.00169 -0.1019 0.5112 0.1394
-0.250 0.5118 0.00762 0.00163 -0.1018 0.5034 0.3194
0.000 0.5384 0.00730 0.00166 -0.1017 0.4946 0.4552
0.250 0.5659 0.00727 0.00171 -0.1015 0.4861 0.5018
0.500 0.5935 0.00729 0.00175 -0.1013 0.4768 0.5309
0.750 0.6212 0.00733 0.00180 -0.1011 0.4681 0.5568
1.250 0.6762 0.00745 0.00191 -0.1007 0.4491 0.5917
1.500 0.7033 0.00753 0.00199 -0.1004 0.4397 0.6134
1.750 0.7306 0.00758 0.00207 -0.1002 0.4309 0.6355
2.000 0.7577 0.00767 0.00215 -0.0999 0.4220 0.6510
2.250 0.7851 0.00775 0.00222 -0.0998 0.4138 0.6635
2.500 0.8121 0.00784 0.00231 -0.0995 0.4059 0.6773
2.750 0.8393 0.00791 0.00239 -0.0993 0.3983 0.6925
3.000 0.8658 0.00801 0.00250 -0.0989 0.3911 0.7134
3.250 0.8926 0.00803 0.00260 -0.0986 0.3850 0.7407
3.500 0.9184 0.00808 0.00271 -0.0982 0.3784 0.7763
3.750 0.9423 0.00800 0.00282 -0.0972 0.3726 0.8446
4.000 0.9789 0.00792 0.00293 -0.0990 0.3654 1.0000
4.250 1.0053 0.00810 0.00306 -0.0988 0.3589 1.0000
4.500 1.0327 0.00821 0.00316 -0.0986 0.3538 1.0000
4.750 1.0593 0.00837 0.00328 -0.0984 0.3479 1.0000
5.000 1.0856 0.00855 0.00343 -0.0981 0.3422 1.0000
5.250 1.1126 0.00867 0.00355 -0.0979 0.3377 1.0000
5.500 1.1389 0.00883 0.00369 -0.0976 0.3326 1.0000
5.750 1.1646 0.00904 0.00386 -0.0972 0.3270 1.0000
6.000 1.1914 0.00916 0.00399 -0.0971 0.3227 1.0000
6.250 1.2171 0.00935 0.00415 -0.0967 0.3154 1.0000
6.500 1.2426 0.00955 0.00433 -0.0963 0.3089 1.0000
6.750 1.2684 0.00972 0.00449 -0.0960 0.3022 1.0000
7.000 1.2931 0.00996 0.00470 -0.0955 0.2946 1.0000
7.250 1.3187 0.01013 0.00487 -0.0951 0.2878 1.0000
7.500 1.3427 0.01040 0.00510 -0.0945 0.2791 1.0000
7.750 1.3674 0.01062 0.00530 -0.0940 0.2703 1.0000
8.000 1.3908 0.01090 0.00555 -0.0934 0.2592 1.0000
8.250 1.4130 0.01126 0.00584 -0.0925 0.2443 1.0000
8.500 1.4339 0.01168 0.00617 -0.0915 0.2272 1.0000
8.750 1.4529 0.01219 0.00657 -0.0902 0.2086 1.0000
9.000 1.4713 0.01271 0.00701 -0.0887 0.1936 1.0000
9.250 1.4907 0.01314 0.00740 -0.0874 0.1846 1.0000
9.500 1.5091 0.01360 0.00783 -0.0860 0.1771 1.0000
9.750 1.5288 0.01395 0.00819 -0.0848 0.1727 1.0000
10.000 1.5447 0.01440 0.00863 -0.0829 0.1670 1.0000
10.250 1.5602 0.01479 0.00903 -0.0809 0.1620 1.0000
10.500 1.5759 0.01518 0.00943 -0.0790 0.1577 1.0000
10.750 1.5884 0.01570 0.00994 -0.0767 0.1525 1.0000
11.000 1.6034 0.01613 0.01040 -0.0748 0.1484 1.0000
11.250 1.6192 0.01654 0.01083 -0.0731 0.1442 1.0000
11.500 1.6306 0.01716 0.01145 -0.0709 0.1383 1.0000
11.750 1.6441 0.01770 0.01202 -0.0690 0.1323 1.0000
12.000 1.6521 0.01855 0.01281 -0.0666 0.1201 1.0000
12.250 1.6401 0.02051 0.01454 -0.0621 0.0878 1.0000
12.500 1.6337 0.02239 0.01636 -0.0588 0.0750 1.0000
12.750 1.6338 0.02404 0.01803 -0.0565 0.0687 1.0000
13.000 1.6370 0.02563 0.01965 -0.0548 0.0649 1.0000
13.250 1.6375 0.02754 0.02159 -0.0531 0.0607 1.0000
13.500 1.6430 0.02919 0.02329 -0.0520 0.0583 1.0000
13.750 1.6454 0.03120 0.02535 -0.0510 0.0559 1.0000
14.000 1.6462 0.03346 0.02765 -0.0501 0.0534 1.0000
14.250 1.6497 0.03556 0.02982 -0.0495 0.0516 1.0000
14.500 1.6527 0.03777 0.03209 -0.0490 0.0498 1.0000
14.750 1.6524 0.04034 0.03471 -0.0486 0.0478 1.0000
15.000 1.6500 0.04321 0.03763 -0.0482 0.0460 1.0000
15.250 1.6508 0.04580 0.04029 -0.0480 0.0445 1.0000
15.500 1.6512 0.04846 0.04303 -0.0478 0.0430 1.0000
15.750 1.6486 0.05153 0.04616 -0.0478 0.0414 1.0000
16.000 1.6438 0.05495 0.04962 -0.0479 0.0398 1.0000
16.250 1.6405 0.05827 0.05301 -0.0481 0.0382 1.0000
16.500 1.6383 0.06155 0.05636 -0.0484 0.0366 1.0000
16.750 1.6333 0.06528 0.06016 -0.0490 0.0351 1.0000
17.000 1.6251 0.06951 0.06444 -0.0497 0.0334 1.0000
17.250 1.6219 0.07318 0.06819 -0.0504 0.0320 1.0000
17.500 1.6160 0.07730 0.07238 -0.0514 0.0304 1.0000
17.750 1.6068 0.08197 0.07711 -0.0526 0.0289 1.0000
18.000 1.6004 0.08634 0.08156 -0.0538 0.0275 1.0000
18.250 1.5931 0.09091 0.08620 -0.0551 0.0260 1.0000
18.500 1.5834 0.09596 0.09131 -0.0568 0.0248 1.0000
18.750 1.5740 0.10101 0.09644 -0.0586 0.0237 1.0000
19.000 1.5661 0.10590 0.10142 -0.0604 0.0226 1.0000
19.250 1.5571 0.11105 0.10664 -0.0624 0.0217 1.0000
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Polar data table (+)
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