GOE 476 AIRFOIL (goe476-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 476 AIRFOIL (goe476-il) Reynolds number: 200,000 Max Cl/Cd: 74.37 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe476-il-200000-n5.txt Download as CSV file: xf-goe476-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 476 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1914 0.06840 0.06413 -0.1010 0.9152 0.0520
-9.000 -0.3374 0.03259 0.02696 -0.1254 0.8567 0.0552
-8.750 -0.3342 0.02944 0.02329 -0.1241 0.8440 0.0561
-8.500 -0.3250 0.02712 0.02049 -0.1226 0.8321 0.0570
-8.250 -0.3123 0.02538 0.01830 -0.1209 0.8209 0.0578
-8.000 -0.2914 0.02437 0.01709 -0.1201 0.8109 0.0584
-7.750 -0.2701 0.02376 0.01644 -0.1191 0.8004 0.0591
-7.500 -0.2470 0.02318 0.01574 -0.1185 0.7913 0.0598
-7.250 -0.2263 0.02255 0.01498 -0.1173 0.7816 0.0607
-7.000 -0.2041 0.02184 0.01407 -0.1164 0.7729 0.0617
-6.750 -0.1832 0.02111 0.01315 -0.1152 0.7638 0.0627
-6.500 -0.1608 0.02040 0.01220 -0.1143 0.7553 0.0636
-6.250 -0.1382 0.01977 0.01135 -0.1132 0.7472 0.0645
-6.000 -0.1149 0.01923 0.01077 -0.1124 0.7388 0.0655
-5.750 -0.0908 0.01885 0.01033 -0.1117 0.7310 0.0665
-5.500 -0.0672 0.01848 0.00990 -0.1108 0.7223 0.0677
-5.250 -0.0426 0.01809 0.00937 -0.1100 0.7148 0.0691
-5.000 -0.0189 0.01768 0.00886 -0.1091 0.7066 0.0704
-4.750 0.0058 0.01730 0.00832 -0.1084 0.6996 0.0717
-4.500 0.0303 0.01691 0.00789 -0.1076 0.6933 0.0729
-4.250 0.0547 0.01662 0.00759 -0.1069 0.6869 0.0744
-4.000 0.0799 0.01637 0.00729 -0.1062 0.6811 0.0762
-3.750 0.1053 0.01612 0.00695 -0.1056 0.6760 0.0783
-3.500 0.1302 0.01587 0.00663 -0.1049 0.6700 0.0802
-3.250 0.1548 0.01560 0.00637 -0.1041 0.6644 0.0821
-3.000 0.1806 0.01541 0.00614 -0.1036 0.6596 0.0845
-2.750 0.2056 0.01524 0.00594 -0.1029 0.6546 0.0875
-2.500 0.2306 0.01505 0.00576 -0.1022 0.6495 0.0906
-2.250 0.2560 0.01491 0.00562 -0.1015 0.6446 0.0944
-1.750 0.3067 0.01467 0.00538 -0.1003 0.6350 0.1036
-1.500 0.3319 0.01459 0.00529 -0.0995 0.6297 0.1102
-1.250 0.3576 0.01453 0.00525 -0.0990 0.6251 0.1177
-0.750 0.4089 0.01448 0.00518 -0.0978 0.6163 0.1351
-0.500 0.4338 0.01443 0.00519 -0.0971 0.6115 0.1439
-0.250 0.4595 0.01442 0.00515 -0.0965 0.6069 0.1528
0.000 0.4856 0.01441 0.00512 -0.0960 0.6028 0.1614
0.250 0.5100 0.01439 0.00513 -0.0952 0.5978 0.1694
0.500 0.5341 0.01435 0.00516 -0.0944 0.5925 0.1782
0.750 0.5591 0.01435 0.00514 -0.0937 0.5878 0.1872
1.000 0.5848 0.01434 0.00514 -0.0931 0.5838 0.1975
1.250 0.6085 0.01432 0.00520 -0.0922 0.5790 0.2085
1.750 0.6560 0.01427 0.00529 -0.0904 0.5689 0.2431
2.000 0.6804 0.01421 0.00530 -0.0896 0.5644 0.2743
2.250 0.7008 0.01405 0.00541 -0.0881 0.5581 0.3322
2.750 0.8817 0.01316 0.00598 -0.1143 0.5415 1.0000
3.000 0.9030 0.01329 0.00608 -0.1130 0.5360 1.0000
3.250 0.9247 0.01343 0.00616 -0.1116 0.5312 1.0000
3.500 0.9457 0.01357 0.00627 -0.1102 0.5258 1.0000
3.750 0.9658 0.01371 0.00641 -0.1086 0.5192 1.0000
4.000 0.9864 0.01386 0.00650 -0.1070 0.5135 1.0000
4.250 1.0069 0.01402 0.00664 -0.1055 0.5082 1.0000
4.500 1.0268 0.01418 0.00681 -0.1039 0.5023 1.0000
4.750 1.0464 0.01435 0.00694 -0.1022 0.4963 1.0000
5.000 1.0657 0.01452 0.00710 -0.1005 0.4902 1.0000
5.250 1.0842 0.01470 0.00728 -0.0986 0.4837 1.0000
5.500 1.1030 0.01489 0.00743 -0.0968 0.4778 1.0000
5.750 1.1205 0.01509 0.00764 -0.0947 0.4707 1.0000
6.000 1.1374 0.01530 0.00782 -0.0925 0.4633 1.0000
6.250 1.1542 0.01552 0.00802 -0.0904 0.4566 1.0000
6.500 1.1700 0.01575 0.00827 -0.0881 0.4491 1.0000
7.000 1.1983 0.01627 0.00876 -0.0828 0.4330 1.0000
7.250 1.2084 0.01655 0.00899 -0.0794 0.4242 1.0000
7.500 1.2186 0.01682 0.00929 -0.0761 0.4148 1.0000
7.750 1.2280 0.01716 0.00958 -0.0727 0.4053 1.0000
8.000 1.2380 0.01750 0.00995 -0.0696 0.3944 1.0000
8.250 1.2478 0.01791 0.01035 -0.0665 0.3835 1.0000
8.500 1.2560 0.01838 0.01079 -0.0633 0.3715 1.0000
8.750 1.2649 0.01889 0.01131 -0.0603 0.3571 1.0000
9.000 1.2715 0.01952 0.01191 -0.0571 0.3403 1.0000
9.250 1.2750 0.02033 0.01264 -0.0537 0.3189 1.0000
9.500 1.2743 0.02141 0.01361 -0.0499 0.2941 1.0000
9.750 1.2715 0.02274 0.01482 -0.0463 0.2736 1.0000
10.250 1.2724 0.02552 0.01746 -0.0405 0.2463 1.0000
10.500 1.2752 0.02693 0.01885 -0.0382 0.2372 1.0000
10.750 1.2787 0.02838 0.02029 -0.0361 0.2289 1.0000
11.000 1.2828 0.02985 0.02176 -0.0342 0.2222 1.0000
11.250 1.2886 0.03127 0.02319 -0.0326 0.2150 1.0000
11.500 1.2918 0.03292 0.02483 -0.0309 0.2089 1.0000
11.750 1.2996 0.03428 0.02624 -0.0296 0.2036 1.0000
12.000 1.3063 0.03577 0.02775 -0.0283 0.1977 1.0000
12.250 1.3103 0.03750 0.02949 -0.0269 0.1924 1.0000
12.500 1.3183 0.03896 0.03101 -0.0259 0.1872 1.0000
12.750 1.3256 0.04051 0.03261 -0.0249 0.1817 1.0000
13.000 1.3303 0.04231 0.03442 -0.0238 0.1769 1.0000
13.250 1.3376 0.04393 0.03611 -0.0230 0.1721 1.0000
13.500 1.3445 0.04561 0.03785 -0.0222 0.1665 1.0000
13.750 1.3475 0.04769 0.03994 -0.0214 0.1611 1.0000
14.000 1.3546 0.04943 0.04176 -0.0207 0.1553 1.0000
14.250 1.3581 0.05155 0.04391 -0.0200 0.1491 1.0000
14.500 1.3620 0.05367 0.04608 -0.0195 0.1433 1.0000
14.750 1.3651 0.05590 0.04834 -0.0189 0.1369 1.0000
15.000 1.3665 0.05835 0.05082 -0.0185 0.1307 1.0000
15.250 1.3684 0.06079 0.05329 -0.0181 0.1243 1.0000
15.500 1.3689 0.06342 0.05595 -0.0177 0.1186 1.0000
15.750 1.3691 0.06612 0.05869 -0.0175 0.1122 1.0000
16.000 1.3686 0.06894 0.06154 -0.0173 0.1069 1.0000
16.250 1.3683 0.07179 0.06443 -0.0172 0.1012 1.0000
16.500 1.3664 0.07486 0.06753 -0.0172 0.0965 1.0000
16.750 1.3662 0.07778 0.07051 -0.0172 0.0915 1.0000
17.000 1.3627 0.08113 0.07387 -0.0174 0.0877 1.0000
17.250 1.3635 0.08398 0.07679 -0.0175 0.0841 1.0000
17.500 1.3613 0.08724 0.08010 -0.0178 0.0810 1.0000
18.000 1.3584 0.09367 0.08664 -0.0185 0.0766 1.0000
18.250 1.3578 0.09678 0.08982 -0.0189 0.0747 1.0000
18.500 1.3566 0.10000 0.09310 -0.0195 0.0732 1.0000
18.750 1.3548 0.10331 0.09646 -0.0201 0.0718 1.0000
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