GOE 483 AIRFOIL (goe483-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 483 AIRFOIL (goe483-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.39 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe483-il-1000000.txt Download as CSV file: xf-goe483-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 483 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2256 0.08653 0.08509 -0.0272 1.0000 0.0076
-8.250 -0.2229 0.08344 0.08202 -0.0276 1.0000 0.0076
-8.000 -0.2211 0.08044 0.07904 -0.0278 1.0000 0.0076
-7.750 -0.2108 0.07644 0.07505 -0.0305 0.9901 0.0076
-7.500 -0.1952 0.07165 0.07025 -0.0350 0.9816 0.0076
-7.250 -0.1832 0.06504 0.06363 -0.0399 0.9695 0.0081
-7.000 -0.1638 0.06121 0.05977 -0.0441 0.9519 0.0084
-6.750 -0.1559 0.05806 0.05655 -0.0459 0.9223 0.0085
-6.500 -0.1498 0.05564 0.05405 -0.0467 0.8983 0.0092
-6.250 -0.1424 0.05273 0.05107 -0.0483 0.8798 0.0098
-6.000 -0.1330 0.04948 0.04776 -0.0506 0.8651 0.0104
-5.750 -0.1190 0.04603 0.04425 -0.0542 0.8529 0.0114
-5.500 -0.1017 0.04284 0.04099 -0.0578 0.8428 0.0117
-5.250 -0.0837 0.03920 0.03730 -0.0611 0.8335 0.0118
-4.000 0.0668 0.01366 0.00985 -0.1004 0.8218 0.0088
-3.750 0.0938 0.01232 0.00820 -0.1003 0.8140 0.0094
-3.500 0.1209 0.01146 0.00712 -0.1002 0.8054 0.0104
-3.250 0.1481 0.01050 0.00589 -0.1000 0.7971 0.0111
-3.000 0.1753 0.00979 0.00496 -0.0997 0.7889 0.0116
-2.750 0.2026 0.00885 0.00379 -0.0995 0.7810 0.0124
-2.500 0.2297 0.00819 0.00298 -0.0992 0.7733 0.0144
-2.250 0.2573 0.00793 0.00265 -0.0990 0.7650 0.0164
-2.000 0.2848 0.00774 0.00238 -0.0987 0.7567 0.0178
-1.750 0.3119 0.00725 0.00177 -0.0984 0.7478 0.0222
-1.500 0.3395 0.00719 0.00170 -0.0982 0.7383 0.0264
-1.250 0.3667 0.00693 0.00137 -0.0979 0.7284 0.0332
-1.000 0.3939 0.00686 0.00123 -0.0976 0.7173 0.0380
-0.750 0.4211 0.00673 0.00106 -0.0974 0.7049 0.0458
-0.250 0.4752 0.00656 0.00092 -0.0969 0.6745 0.0936
0.000 0.5022 0.00658 0.00088 -0.0966 0.6550 0.1059
0.250 0.5289 0.00662 0.00086 -0.0963 0.6317 0.1176
0.500 0.5554 0.00669 0.00084 -0.0960 0.6051 0.1285
1.000 0.6084 0.00686 0.00091 -0.0954 0.5593 0.1636
1.250 0.6352 0.00696 0.00097 -0.0952 0.5426 0.1873
1.500 0.6620 0.00705 0.00104 -0.0950 0.5281 0.2053
1.750 0.6888 0.00714 0.00111 -0.0947 0.5142 0.2194
2.000 0.7157 0.00723 0.00118 -0.0945 0.5015 0.2303
2.250 0.7427 0.00731 0.00124 -0.0944 0.4902 0.2404
2.500 0.7696 0.00739 0.00131 -0.0942 0.4795 0.2510
2.750 0.7965 0.00747 0.00139 -0.0940 0.4688 0.2629
3.000 0.8235 0.00752 0.00147 -0.0938 0.4583 0.2801
3.250 0.8503 0.00756 0.00158 -0.0937 0.4469 0.3155
3.500 0.8776 0.00642 0.00177 -0.0940 0.4350 1.0000
3.750 0.9040 0.00658 0.00187 -0.0937 0.4184 1.0000
4.000 0.9300 0.00679 0.00199 -0.0934 0.3974 1.0000
4.250 0.9555 0.00706 0.00213 -0.0930 0.3705 1.0000
4.500 0.9808 0.00735 0.00232 -0.0926 0.3430 1.0000
4.750 1.0059 0.00768 0.00251 -0.0922 0.3141 1.0000
5.000 1.0306 0.00804 0.00274 -0.0918 0.2821 1.0000
5.250 1.0535 0.00864 0.00306 -0.0911 0.2283 1.0000
5.500 1.0659 0.01067 0.00413 -0.0892 0.0625 1.0000
5.750 1.0868 0.01161 0.00489 -0.0881 0.0151 1.0000
6.000 1.1113 0.01203 0.00538 -0.0875 0.0129 1.0000
6.250 1.1356 0.01243 0.00584 -0.0869 0.0118 1.0000
6.500 1.1594 0.01290 0.00636 -0.0862 0.0105 1.0000
6.750 1.1817 0.01356 0.00708 -0.0853 0.0089 1.0000
7.000 1.1976 0.01507 0.00882 -0.0834 0.0079 1.0000
7.250 1.2207 0.01552 0.00931 -0.0826 0.0077 1.0000
7.500 1.2421 0.01616 0.01001 -0.0817 0.0074 1.0000
7.750 1.2624 0.01691 0.01083 -0.0805 0.0069 1.0000
8.000 1.2817 0.01773 0.01172 -0.0792 0.0063 1.0000
8.250 1.2984 0.01880 0.01287 -0.0776 0.0060 1.0000
8.500 1.3137 0.02001 0.01418 -0.0757 0.0058 1.0000
8.750 1.3309 0.02092 0.01515 -0.0743 0.0054 1.0000
9.000 1.3464 0.02195 0.01622 -0.0727 0.0051 1.0000
9.250 1.3554 0.02396 0.01831 -0.0702 0.0048 1.0000
9.500 1.3670 0.02616 0.02061 -0.0681 0.0048 1.0000
9.750 1.3810 0.02923 0.02383 -0.0665 0.0047 1.0000
10.000 1.3933 0.03141 0.02622 -0.0646 0.0045 1.0000
10.250 1.4053 0.03244 0.02739 -0.0626 0.0043 1.0000
10.500 1.4140 0.03394 0.02905 -0.0601 0.0042 1.0000
10.750 1.4196 0.03609 0.03138 -0.0574 0.0041 1.0000
11.000 1.4216 0.03832 0.03382 -0.0543 0.0039 1.0000
11.250 1.4181 0.04136 0.03711 -0.0511 0.0038 1.0000
11.500 1.4095 0.04484 0.04084 -0.0480 0.0038 1.0000
11.750 1.3957 0.04889 0.04514 -0.0452 0.0039 1.0000
12.000 1.3785 0.05332 0.04981 -0.0432 0.0040 1.0000
12.250 1.3606 0.05790 0.05458 -0.0422 0.0042 1.0000
12.500 1.3577 0.06305 0.05977 -0.0418 0.0048 1.0000
12.750 1.3480 0.06633 0.06319 -0.0417 0.0048 1.0000
13.000 1.3325 0.07102 0.06805 -0.0424 0.0048 1.0000
13.250 1.3140 0.07665 0.07385 -0.0441 0.0048 1.0000
13.500 1.2997 0.08190 0.07924 -0.0462 0.0049 1.0000
13.750 1.2828 0.08812 0.08562 -0.0493 0.0049 1.0000
14.000 1.2658 0.09491 0.09255 -0.0530 0.0049 1.0000
14.250 1.2486 0.10233 0.10012 -0.0574 0.0049 1.0000
14.500 1.2317 0.11033 0.10826 -0.0624 0.0050 1.0000
14.750 1.2141 0.11914 0.11721 -0.0680 0.0050 1.0000
15.000 1.1950 0.12913 0.12734 -0.0746 0.0051 1.0000
15.250 1.1655 0.14356 0.14195 -0.0845 0.0052 1.0000
15.500 1.1307 0.16275 0.16132 -0.0965 0.0056 1.0000
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Polar data table (+)
Polar graphs
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