GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 372 AIRFOIL (goe372-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.47 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe372-il-1000000.txt Download as CSV file: xf-goe372-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 372 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2822 0.09826 0.09673 -0.0297 1.0000 0.0102
-9.500 -0.2803 0.09488 0.09336 -0.0301 1.0000 0.0108
-7.000 -0.3249 0.07114 0.06968 -0.0436 0.9912 0.0110
-6.750 -0.2945 0.01264 0.00876 -0.1012 0.9729 0.0087
-6.500 -0.2609 0.01179 0.00777 -0.1028 0.9702 0.0099
-6.250 -0.2322 0.01117 0.00703 -0.1031 0.9635 0.0109
-6.000 -0.2005 0.01056 0.00629 -0.1040 0.9578 0.0119
-5.750 -0.1717 0.00962 0.00512 -0.1042 0.9492 0.0132
-5.500 -0.1411 0.00929 0.00477 -0.1048 0.9399 0.0159
-5.250 -0.1115 0.00926 0.00468 -0.1050 0.9283 0.0180
-5.000 -0.0844 0.00882 0.00414 -0.1049 0.9144 0.0212
-4.750 -0.0566 0.00892 0.00423 -0.1047 0.9005 0.0239
-4.500 -0.0293 0.00895 0.00418 -0.1045 0.8870 0.0260
-4.250 -0.0021 0.00906 0.00423 -0.1042 0.8741 0.0270
-4.000 0.0232 0.00839 0.00335 -0.1037 0.8616 0.0293
-3.750 0.0492 0.00803 0.00290 -0.1033 0.8501 0.0317
-3.500 0.0757 0.00784 0.00263 -0.1029 0.8395 0.0335
-3.250 0.1024 0.00770 0.00241 -0.1026 0.8299 0.0357
-3.000 0.1292 0.00758 0.00222 -0.1023 0.8205 0.0375
-2.750 0.1560 0.00746 0.00202 -0.1020 0.8117 0.0382
-2.500 0.1825 0.00723 0.00169 -0.1016 0.8033 0.0395
-2.250 0.2092 0.00702 0.00141 -0.1013 0.7952 0.0417
-2.000 0.2361 0.00689 0.00123 -0.1009 0.7875 0.0447
-1.750 0.2630 0.00678 0.00110 -0.1007 0.7794 0.0491
-1.500 0.2900 0.00667 0.00103 -0.1004 0.7718 0.0664
-1.250 0.3170 0.00667 0.00101 -0.1002 0.7639 0.0759
-1.000 0.3440 0.00660 0.00095 -0.0999 0.7552 0.0839
-0.750 0.3709 0.00659 0.00090 -0.0996 0.7456 0.0889
-0.500 0.3977 0.00656 0.00085 -0.0993 0.7358 0.0949
-0.250 0.4247 0.00652 0.00082 -0.0991 0.7260 0.1018
0.000 0.4515 0.00649 0.00079 -0.0988 0.7162 0.1119
0.250 0.4782 0.00646 0.00078 -0.0985 0.7056 0.1283
0.500 0.5046 0.00642 0.00078 -0.0982 0.6930 0.1570
0.750 0.5309 0.00636 0.00080 -0.0979 0.6789 0.1988
1.000 0.5563 0.00615 0.00086 -0.0975 0.6625 0.3207
1.250 0.6013 0.00478 0.00101 -0.1019 0.6389 1.0000
1.500 0.6260 0.00495 0.00104 -0.1012 0.6088 1.0000
1.750 0.6490 0.00524 0.00110 -0.1002 0.5627 1.0000
2.000 0.6725 0.00553 0.00120 -0.0992 0.5255 1.0000
2.250 0.6971 0.00576 0.00130 -0.0986 0.4998 1.0000
2.500 0.7218 0.00598 0.00141 -0.0979 0.4706 1.0000
2.750 0.7433 0.00648 0.00155 -0.0968 0.3923 1.0000
3.000 0.7541 0.00812 0.00216 -0.0940 0.1776 1.0000
3.250 0.7698 0.00940 0.00277 -0.0919 0.0207 1.0000
3.500 0.7951 0.00963 0.00301 -0.0913 0.0163 1.0000
3.750 0.8200 0.00990 0.00337 -0.0907 0.0138 1.0000
4.000 0.8447 0.01018 0.00367 -0.0900 0.0131 1.0000
4.250 0.8690 0.01051 0.00405 -0.0893 0.0123 1.0000
4.500 0.8928 0.01091 0.00449 -0.0884 0.0113 1.0000
4.750 0.9157 0.01140 0.00503 -0.0874 0.0102 1.0000
5.000 0.9375 0.01201 0.00571 -0.0862 0.0098 1.0000
5.250 0.9580 0.01275 0.00650 -0.0847 0.0093 1.0000
5.500 0.9749 0.01385 0.00767 -0.0827 0.0087 1.0000
5.750 0.9900 0.01526 0.00913 -0.0804 0.0085 1.0000
6.000 1.0069 0.01690 0.01080 -0.0785 0.0083 1.0000
6.250 1.0318 0.01688 0.01085 -0.0778 0.0078 1.0000
6.500 1.0546 0.01740 0.01145 -0.0768 0.0072 1.0000
6.750 1.0755 0.01863 0.01274 -0.0754 0.0068 1.0000
7.000 1.1045 0.02563 0.01976 -0.0754 0.0083 1.0000
7.250 1.1264 0.02775 0.02204 -0.0743 0.0083 1.0000
7.500 1.1464 0.02997 0.02443 -0.0729 0.0082 1.0000
7.750 1.1647 0.03220 0.02686 -0.0713 0.0082 1.0000
8.000 1.1812 0.03445 0.02932 -0.0695 0.0082 1.0000
8.250 1.1956 0.03666 0.03176 -0.0675 0.0082 1.0000
8.500 1.2080 0.03865 0.03400 -0.0652 0.0082 1.0000
8.750 1.2201 0.03976 0.03533 -0.0628 0.0080 1.0000
9.000 1.2411 0.03867 0.03436 -0.0611 0.0072 1.0000
9.250 1.2524 0.04054 0.03644 -0.0587 0.0067 1.0000
9.500 1.2599 0.04278 0.03890 -0.0562 0.0063 1.0000
9.750 1.2646 0.04509 0.04139 -0.0535 0.0061 1.0000
10.000 1.2659 0.04753 0.04401 -0.0507 0.0059 1.0000
10.250 1.2646 0.04987 0.04650 -0.0477 0.0057 1.0000
10.500 1.2562 0.05221 0.04900 -0.0438 0.0056 1.0000
10.750 1.2445 0.05432 0.05123 -0.0398 0.0055 1.0000
11.000 1.2306 0.05686 0.05391 -0.0364 0.0055 1.0000
11.250 1.2161 0.05974 0.05692 -0.0340 0.0054 1.0000
11.500 1.2001 0.06313 0.06045 -0.0325 0.0054 1.0000
11.750 1.1858 0.06666 0.06409 -0.0319 0.0054 1.0000
12.000 1.1659 0.07140 0.06899 -0.0322 0.0054 1.0000
12.250 1.1463 0.07670 0.07443 -0.0335 0.0054 1.0000
12.500 1.1268 0.08255 0.08042 -0.0359 0.0054 1.0000
12.750 1.1034 0.09006 0.08808 -0.0398 0.0054 1.0000
13.000 1.0822 0.09798 0.09613 -0.0447 0.0055 1.0000
13.250 1.0579 0.10794 0.10623 -0.0513 0.0055 1.0000
13.500 1.0275 0.12257 0.12101 -0.0613 0.0057 1.0000
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Polar data table (+)
Polar graphs
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