GOE 464 AIRFOIL (goe464-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 464 AIRFOIL (goe464-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.26 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe464-il-1000000-n5.txt Download as CSV file: xf-goe464-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 464 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0111 0.10991 0.10752 -0.0804 0.8474 0.0065
-11.000 -0.0015 0.10749 0.10507 -0.0814 0.8412 0.0064
-10.750 0.0056 0.10431 0.10187 -0.0824 0.8348 0.0065
-10.250 0.0221 0.09903 0.09652 -0.0842 0.8199 0.0066
-10.000 0.0330 0.09730 0.09478 -0.0850 0.8125 0.0069
-9.750 0.0391 0.09411 0.09156 -0.0859 0.8058 0.0066
-9.500 0.0498 0.09232 0.08976 -0.0866 0.8002 0.0068
-9.250 0.0623 0.09093 0.08836 -0.0872 0.7941 0.0071
-9.000 0.0669 0.08769 0.08510 -0.0880 0.7865 0.0069
-8.750 0.0800 0.08649 0.08389 -0.0885 0.7803 0.0072
-8.500 0.0889 0.08445 0.08183 -0.0890 0.7713 0.0073
-8.250 0.0979 0.08249 0.07985 -0.0894 0.7627 0.0075
-8.000 0.1045 0.08032 0.07766 -0.0896 0.7518 0.0075
-7.750 0.1096 0.07817 0.07550 -0.0895 0.7380 0.0074
-7.500 0.1135 0.07643 0.07367 -0.0889 0.7101 0.0077
-7.250 0.1197 0.07442 0.07150 -0.0891 0.6700 0.0078
-7.000 0.1284 0.07206 0.06904 -0.0901 0.6466 0.0082
-6.750 0.1393 0.06953 0.06644 -0.0917 0.6321 0.0083
-6.500 0.1513 0.06625 0.06312 -0.0943 0.6215 0.0087
-6.250 0.1661 0.06307 0.05990 -0.0973 0.6135 0.0090
-6.000 0.1846 0.06148 0.05829 -0.0989 0.6054 0.0092
-5.500 0.2245 0.05754 0.05429 -0.1033 0.5927 0.0100
-5.250 0.2500 0.05180 0.04850 -0.1107 0.5876 0.0115
-4.750 0.2994 0.04827 0.04488 -0.1156 0.5749 0.0121
-4.250 0.3839 0.03527 0.03159 -0.1364 0.5647 0.0178
-4.000 0.4450 0.02442 0.02018 -0.1535 0.5603 0.0211
-3.750 0.4758 0.02282 0.01846 -0.1554 0.5533 0.0217
-3.500 0.5041 0.02197 0.01752 -0.1561 0.5452 0.0223
-3.250 0.5333 0.02089 0.01634 -0.1571 0.5378 0.0230
-3.000 0.5623 0.01976 0.01508 -0.1580 0.5296 0.0237
-2.750 0.5910 0.01879 0.01398 -0.1587 0.5220 0.0243
-2.500 0.6193 0.01788 0.01293 -0.1592 0.5121 0.0249
-2.250 0.6472 0.01710 0.01202 -0.1595 0.5018 0.0252
-2.000 0.6742 0.01687 0.01169 -0.1593 0.4896 0.0256
-1.750 0.7010 0.01665 0.01139 -0.1591 0.4767 0.0262
-1.500 0.7280 0.01638 0.01105 -0.1589 0.4658 0.0268
-1.250 0.7548 0.01612 0.01069 -0.1587 0.4554 0.0275
-1.000 0.7816 0.01589 0.01039 -0.1585 0.4450 0.0280
-0.750 0.8082 0.01572 0.01015 -0.1582 0.4356 0.0285
-0.500 0.8344 0.01565 0.01000 -0.1578 0.4251 0.0290
-0.250 0.8610 0.01556 0.00987 -0.1574 0.4163 0.0294
0.250 0.9136 0.01548 0.00970 -0.1567 0.4011 0.0304
0.500 0.9400 0.01533 0.00951 -0.1563 0.3940 0.0315
0.750 0.9668 0.01502 0.00913 -0.1561 0.3879 0.0330
1.000 0.9938 0.01464 0.00868 -0.1559 0.3818 0.0345
1.250 1.0207 0.01409 0.00803 -0.1557 0.3747 0.0397
1.500 1.0458 0.01456 0.00859 -0.1551 0.3674 0.0577
1.750 1.0725 0.01404 0.00793 -0.1548 0.3595 0.0625
2.000 1.0988 0.01368 0.00745 -0.1544 0.3520 0.0649
2.250 1.1243 0.01378 0.00751 -0.1539 0.3437 0.0659
2.500 1.1497 0.01380 0.00748 -0.1534 0.3359 0.0675
2.750 1.1767 0.01298 0.00647 -0.1531 0.3302 0.0703
3.000 1.2019 0.01308 0.00653 -0.1526 0.3233 0.0707
3.250 1.2272 0.01328 0.00673 -0.1521 0.3176 0.0711
3.500 1.2525 0.01338 0.00682 -0.1516 0.3118 0.0717
3.750 1.2775 0.01340 0.00680 -0.1510 0.3060 0.0722
4.000 1.3027 0.01347 0.00686 -0.1505 0.3019 0.0732
4.250 1.3283 0.01337 0.00673 -0.1500 0.2980 0.0744
4.500 1.3537 0.01317 0.00646 -0.1494 0.2934 0.0750
4.750 1.3788 0.01275 0.00590 -0.1488 0.2885 0.0769
5.000 1.4036 0.01279 0.00593 -0.1482 0.2841 0.0771
5.250 1.4282 0.01285 0.00598 -0.1476 0.2783 0.0774
5.500 1.4520 0.01300 0.00610 -0.1469 0.2718 0.0778
5.750 1.4763 0.01307 0.00616 -0.1462 0.2673 0.0782
6.000 1.5004 0.01316 0.00624 -0.1456 0.2619 0.0787
6.250 1.5236 0.01329 0.00634 -0.1447 0.2556 0.0793
6.500 1.5473 0.01336 0.00640 -0.1440 0.2505 0.0799
6.750 1.5703 0.01346 0.00646 -0.1432 0.2436 0.0808
7.000 1.5924 0.01358 0.00653 -0.1422 0.2355 0.0820
7.250 1.6133 0.01380 0.00668 -0.1410 0.2243 0.0831
7.500 1.6340 0.01410 0.00695 -0.1398 0.2127 0.0835
7.750 1.6542 0.01443 0.00725 -0.1386 0.2032 0.0839
8.000 1.6734 0.01479 0.00758 -0.1372 0.1933 0.0843
8.250 1.6929 0.01512 0.00789 -0.1358 0.1849 0.0849
8.500 1.7102 0.01553 0.00827 -0.1341 0.1751 0.0854
8.750 1.7259 0.01593 0.00863 -0.1321 0.1660 0.0859
9.000 1.7404 0.01630 0.00899 -0.1299 0.1590 0.0865
9.250 1.7537 0.01675 0.00941 -0.1275 0.1510 0.0870
9.500 1.7671 0.01722 0.00987 -0.1251 0.1431 0.0876
9.750 1.7802 0.01771 0.01034 -0.1228 0.1364 0.0882
10.000 1.7934 0.01822 0.01084 -0.1206 0.1306 0.0889
10.250 1.8066 0.01873 0.01136 -0.1185 0.1250 0.0896
10.500 1.8166 0.01943 0.01204 -0.1160 0.1176 0.0900
10.750 1.8299 0.01998 0.01263 -0.1140 0.1136 0.0904
11.000 1.8390 0.02079 0.01342 -0.1116 0.1068 0.0910
11.250 1.8493 0.02157 0.01421 -0.1095 0.1012 0.0916
11.500 1.8561 0.02260 0.01523 -0.1070 0.0934 0.0921
11.750 1.8584 0.02397 0.01655 -0.1043 0.0816 0.0926
12.000 1.8545 0.02587 0.01835 -0.1011 0.0667 0.0930
12.500 1.8565 0.02927 0.02174 -0.0964 0.0517 0.0939
12.750 1.8567 0.03115 0.02364 -0.0943 0.0453 0.0943
13.000 1.8497 0.03377 0.02623 -0.0919 0.0354 0.0945
13.250 1.8296 0.03779 0.03021 -0.0892 0.0182 0.0945
13.500 1.8251 0.04059 0.03308 -0.0877 0.0141 0.0948
13.750 1.8241 0.04318 0.03575 -0.0867 0.0123 0.0951
14.000 1.8236 0.04586 0.03852 -0.0859 0.0109 0.0954
14.250 1.8235 0.04865 0.04139 -0.0853 0.0100 0.0958
14.500 1.8216 0.05175 0.04458 -0.0849 0.0091 0.0967
14.750 1.8194 0.05502 0.04794 -0.0848 0.0084 0.0968
15.000 1.8181 0.05827 0.05129 -0.0847 0.0079 0.0974
15.250 1.8153 0.06178 0.05489 -0.0848 0.0075 0.0980
15.500 1.8113 0.06555 0.05875 -0.0851 0.0071 0.0986
15.750 1.8058 0.06963 0.06293 -0.0856 0.0067 0.0990
16.000 1.7992 0.07398 0.06737 -0.0862 0.0063 0.0993
16.250 1.7934 0.07829 0.07179 -0.0870 0.0061 0.0997
16.500 1.7874 0.08274 0.07635 -0.0880 0.0059 0.1004
16.750 1.7809 0.08739 0.08111 -0.0891 0.0057 0.1007
17.000 1.7735 0.09226 0.08608 -0.0904 0.0055 0.1012
17.250 1.7655 0.09730 0.09123 -0.0918 0.0054 0.1018
17.500 1.7571 0.10251 0.09655 -0.0935 0.0052 0.1019
17.750 1.7483 0.10784 0.10198 -0.0953 0.0050 0.1023
18.000 1.7393 0.11325 0.10750 -0.0972 0.0048 0.1027
18.250 1.7302 0.11871 0.11306 -0.0993 0.0047 0.1030
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