GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il) Reynolds number: 50,000 Max Cl/Cd: 39.84 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe143-il-50000-n5.txt Download as CSV file: xf-goe143-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 143 (MVA H.20) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4268 0.12248 0.11541 -0.0059 1.0000 0.0856
-9.250 -0.4292 0.12076 0.11377 -0.0092 1.0000 0.0865
-9.000 -0.4315 0.11881 0.11192 -0.0125 1.0000 0.0868
-8.750 -0.4103 0.11169 0.10474 -0.0094 1.0000 0.0893
-8.500 -0.4016 0.10815 0.10122 -0.0096 1.0000 0.0930
-8.250 -0.4000 0.10567 0.09880 -0.0117 1.0000 0.0975
-8.000 -0.4063 0.10432 0.09758 -0.0163 1.0000 0.0996
-7.750 -0.3975 0.09975 0.09306 -0.0161 1.0000 0.1017
-7.500 -0.3865 0.09594 0.08927 -0.0151 1.0000 0.1061
-7.250 -0.3812 0.09294 0.08633 -0.0178 1.0000 0.1102
-7.000 -0.3774 0.09076 0.08418 -0.0278 1.0000 0.1135
-6.250 -0.3476 0.07990 0.07339 -0.0338 1.0000 0.1284
-6.000 -0.3397 0.07624 0.06983 -0.0282 1.0000 0.1347
-5.750 -0.3277 0.07304 0.06657 -0.0344 1.0000 0.1439
-5.500 -0.3185 0.06975 0.06334 -0.0321 1.0000 0.1480
-5.000 -0.2940 0.06367 0.05724 -0.0346 1.0000 0.1649
-4.750 -0.2810 0.06119 0.05472 -0.0370 1.0000 0.1899
-4.500 -0.2375 0.05378 0.04669 -0.0462 1.0000 0.1113
-4.000 -0.1813 0.04501 0.03691 -0.0525 1.0000 0.0867
-3.750 -0.1625 0.04242 0.03425 -0.0527 1.0000 0.0880
-3.500 -0.1447 0.04058 0.03237 -0.0524 1.0000 0.0913
-3.250 -0.1213 0.03836 0.02986 -0.0532 1.0000 0.0921
-3.000 -0.0955 0.03602 0.02711 -0.0541 1.0000 0.0903
-2.750 -0.0696 0.03403 0.02470 -0.0547 1.0000 0.0893
-2.500 -0.0359 0.03215 0.02240 -0.0566 0.9964 0.0890
-2.250 0.0102 0.03028 0.02014 -0.0607 0.9867 0.0900
-2.000 0.0547 0.02891 0.01846 -0.0645 0.9762 0.0951
-1.750 0.0990 0.02760 0.01671 -0.0677 0.9650 0.0980
-1.500 0.1419 0.02641 0.01518 -0.0705 0.9531 0.0993
-1.250 0.1838 0.02529 0.01386 -0.0731 0.9407 0.1012
-1.000 0.2251 0.02428 0.01278 -0.0754 0.9280 0.1046
-0.750 0.2652 0.02360 0.01191 -0.0773 0.9138 0.1127
-0.500 0.3032 0.02279 0.01107 -0.0788 0.8986 0.1191
-0.250 0.3394 0.02215 0.01034 -0.0797 0.8820 0.1248
0.000 0.3746 0.02152 0.00969 -0.0805 0.8647 0.1321
0.250 0.4088 0.02095 0.00916 -0.0812 0.8469 0.1486
0.500 0.4406 0.02045 0.00874 -0.0813 0.8272 0.1717
0.750 0.4678 0.01871 0.00857 -0.0812 0.8076 0.5330
1.000 0.4963 0.01796 0.00815 -0.0795 0.7865 1.0000
1.250 0.5234 0.01812 0.00804 -0.0786 0.7631 1.0000
1.500 0.5508 0.01826 0.00795 -0.0778 0.7408 1.0000
1.750 0.5769 0.01845 0.00797 -0.0769 0.7167 1.0000
2.000 0.6035 0.01863 0.00796 -0.0759 0.6949 1.0000
2.500 0.6556 0.01912 0.00817 -0.0742 0.6512 1.0000
2.750 0.6815 0.01942 0.00835 -0.0735 0.6305 1.0000
3.250 0.7337 0.02010 0.00885 -0.0721 0.5926 1.0000
3.500 0.7601 0.02049 0.00914 -0.0715 0.5752 1.0000
3.750 0.7861 0.02091 0.00950 -0.0709 0.5578 1.0000
4.000 0.8116 0.02134 0.00993 -0.0703 0.5389 1.0000
4.250 0.8361 0.02173 0.01024 -0.0693 0.5170 1.0000
4.500 0.8597 0.02212 0.01055 -0.0683 0.4923 1.0000
4.750 0.8830 0.02251 0.01084 -0.0671 0.4681 1.0000
5.000 0.9063 0.02297 0.01130 -0.0662 0.4448 1.0000
5.250 0.9303 0.02346 0.01179 -0.0654 0.4257 1.0000
5.500 0.9540 0.02398 0.01235 -0.0647 0.4067 1.0000
5.750 0.9773 0.02453 0.01300 -0.0639 0.3867 1.0000
6.000 1.0004 0.02511 0.01364 -0.0631 0.3671 1.0000
6.250 1.0229 0.02571 0.01427 -0.0622 0.3473 1.0000
6.500 1.0449 0.02638 0.01510 -0.0613 0.3248 1.0000
6.750 1.0662 0.02709 0.01582 -0.0603 0.3038 1.0000
7.000 1.0875 0.02790 0.01672 -0.0594 0.2827 1.0000
7.250 1.1086 0.02879 0.01767 -0.0584 0.2648 1.0000
7.500 1.1300 0.02976 0.01872 -0.0575 0.2506 1.0000
7.750 1.1516 0.03079 0.01988 -0.0567 0.2395 1.0000
8.000 1.1735 0.03184 0.02101 -0.0559 0.2308 1.0000
8.250 1.1948 0.03296 0.02236 -0.0551 0.2216 1.0000
8.500 1.2130 0.03390 0.02342 -0.0540 0.2093 1.0000
8.750 1.2275 0.03476 0.02438 -0.0527 0.1931 1.0000
9.000 1.2414 0.03575 0.02554 -0.0514 0.1783 1.0000
9.250 1.2558 0.03686 0.02684 -0.0501 0.1669 1.0000
9.500 1.2671 0.03808 0.02823 -0.0487 0.1529 1.0000
9.750 1.2758 0.03949 0.02980 -0.0471 0.1376 1.0000
10.000 1.2822 0.04114 0.03163 -0.0455 0.1224 1.0000
10.250 1.2829 0.04315 0.03374 -0.0436 0.1051 1.0000
10.750 1.2809 0.04804 0.03897 -0.0403 0.0737 1.0000
11.000 1.2771 0.05111 0.04217 -0.0395 0.0626 1.0000
11.250 1.2705 0.05471 0.04583 -0.0393 0.0561 1.0000
11.500 1.2623 0.05879 0.05001 -0.0397 0.0524 1.0000
11.750 1.2534 0.06327 0.05459 -0.0406 0.0497 1.0000
12.000 1.2434 0.06817 0.05958 -0.0421 0.0478 1.0000
12.250 1.2325 0.07340 0.06489 -0.0438 0.0464 1.0000
12.500 1.2223 0.07869 0.07026 -0.0456 0.0452 1.0000
12.750 1.2133 0.08391 0.07565 -0.0473 0.0441 1.0000
13.000 1.2045 0.08914 0.08105 -0.0489 0.0433 1.0000
13.250 1.1960 0.09442 0.08649 -0.0506 0.0425 1.0000
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Polar data table (+)
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