GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 255 (MVA CA.6) AIRFOIL (goe255-il) Reynolds number: 100,000 Max Cl/Cd: 41.38 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe255-il-100000.txt Download as CSV file: xf-goe255-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 255 (MVA CA.6) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4408 0.10763 0.10349 -0.0542 1.0000 0.0696
-11.500 -0.6198 0.07171 0.06702 -0.0832 0.9910 0.0590
-11.250 -0.6374 0.06546 0.06052 -0.0899 0.9825 0.0586
-11.000 -0.6519 0.06052 0.05526 -0.0931 0.9718 0.0584
-10.750 -0.6584 0.05591 0.05025 -0.0951 0.9616 0.0585
-10.500 -0.6533 0.05148 0.04528 -0.0976 0.9544 0.0588
-10.250 -0.6473 0.04803 0.04148 -0.0977 0.9453 0.0595
-10.000 -0.6152 0.04542 0.03887 -0.1008 0.9413 0.0623
-9.750 -0.6031 0.04371 0.03697 -0.0999 0.9317 0.0645
-9.500 -0.5749 0.04095 0.03373 -0.1022 0.9268 0.0676
-9.250 -0.5611 0.03890 0.03136 -0.1011 0.9177 0.0697
-9.000 -0.5267 0.03686 0.02939 -0.1032 0.9130 0.0743
-8.750 -0.5038 0.03545 0.02762 -0.1033 0.9056 0.0801
-8.500 -0.4758 0.03371 0.02606 -0.1042 0.8994 0.0881
-8.250 -0.4373 0.03177 0.02408 -0.1070 0.8960 0.1028
-8.000 -0.4242 0.03084 0.02312 -0.1051 0.8861 0.1184
-7.750 -0.3865 0.02958 0.02190 -0.1078 0.8819 0.1481
-7.500 -0.3664 0.02908 0.02150 -0.1071 0.8731 0.1687
-7.250 -0.3311 0.02830 0.02062 -0.1089 0.8678 0.1962
-7.000 -0.2912 0.02745 0.01976 -0.1114 0.8646 0.2270
-6.750 -0.2748 0.02725 0.01973 -0.1097 0.8540 0.2471
-6.500 -0.2363 0.02664 0.01911 -0.1115 0.8503 0.2752
-6.250 -0.2156 0.02680 0.01935 -0.1103 0.8409 0.2932
-6.000 -0.1796 0.02676 0.01931 -0.1113 0.8360 0.3142
-5.750 -0.1399 0.02655 0.01893 -0.1129 0.8329 0.3364
-5.500 -0.1230 0.02704 0.01945 -0.1110 0.8221 0.3495
-5.250 -0.0863 0.02683 0.01908 -0.1122 0.8182 0.3691
-5.000 -0.0667 0.02720 0.01946 -0.1108 0.8089 0.3825
-4.750 -0.0344 0.02705 0.01922 -0.1113 0.8036 0.4011
-4.500 0.0019 0.02678 0.01883 -0.1123 0.8002 0.4218
-4.250 0.0155 0.02731 0.01939 -0.1101 0.7896 0.4358
-4.000 0.0484 0.02705 0.01904 -0.1107 0.7855 0.4545
-3.750 0.0686 0.02733 0.01935 -0.1096 0.7785 0.4675
-3.500 0.0912 0.02748 0.01948 -0.1088 0.7719 0.4811
-3.250 0.1234 0.02727 0.01918 -0.1094 0.7684 0.4964
-3.000 0.1397 0.02782 0.01966 -0.1081 0.7615 0.5089
-2.750 0.1592 0.02823 0.02007 -0.1071 0.7554 0.5202
-2.500 0.1907 0.02809 0.01988 -0.1076 0.7522 0.5324
-2.250 0.2252 0.02786 0.01954 -0.1086 0.7497 0.5452
-2.000 0.2206 0.02950 0.02125 -0.1049 0.7395 0.5521
-1.750 0.2489 0.02961 0.02129 -0.1052 0.7363 0.5629
-1.500 0.2848 0.02934 0.02092 -0.1064 0.7340 0.5749
-1.250 0.2745 0.03147 0.02314 -0.1022 0.7247 0.5801
-1.000 0.3006 0.03166 0.02329 -0.1022 0.7205 0.5907
-0.750 0.3394 0.03111 0.02270 -0.1035 0.7180 0.6016
-0.500 0.3317 0.03321 0.02482 -0.0998 0.7089 0.6087
-0.250 0.3561 0.03343 0.02508 -0.0995 0.7043 0.6197
0.000 0.3937 0.03295 0.02459 -0.1005 0.7018 0.6342
0.250 0.4352 0.03231 0.02391 -0.1020 0.7000 0.6486
0.500 0.3840 0.03701 0.02876 -0.0942 0.6876 0.6515
0.750 0.4331 0.03591 0.02763 -0.0965 0.6856 0.6656
1.000 0.4804 0.03492 0.02662 -0.0987 0.6839 0.6803
1.750 0.5021 0.03866 0.03062 -0.0925 0.6635 0.7242
2.000 0.5855 0.03497 0.02702 -0.0974 0.6660 0.7668
2.250 0.5368 0.03967 0.03198 -0.0899 0.6525 0.7955
2.500 0.5195 0.04231 0.03507 -0.0854 0.6423 0.9612
2.750 0.5606 0.04213 0.03465 -0.0881 0.6380 1.0000
3.000 0.6107 0.04104 0.03339 -0.0904 0.6360 1.0000
3.250 0.6642 0.03952 0.03174 -0.0927 0.6347 1.0000
3.500 0.6414 0.04313 0.03535 -0.0887 0.6210 1.0000
3.750 0.6931 0.04149 0.03362 -0.0904 0.6194 1.0000
4.000 0.7502 0.03944 0.03148 -0.0926 0.6186 1.0000
4.250 0.7335 0.04243 0.03449 -0.0887 0.6043 1.0000
4.500 0.7686 0.04178 0.03381 -0.0889 0.5999 1.0000
4.750 0.8362 0.03894 0.03090 -0.0921 0.6012 1.0000
5.000 0.8308 0.04085 0.03284 -0.0887 0.5885 1.0000
5.250 0.8886 0.03866 0.03062 -0.0910 0.5877 1.0000
5.500 0.9522 0.03647 0.02839 -0.0946 0.5867 1.0000
5.750 0.9007 0.04090 0.03290 -0.0861 0.5653 1.0000
6.000 0.9790 0.03733 0.02929 -0.0904 0.5678 1.0000
6.250 1.0007 0.03725 0.02923 -0.0892 0.5586 1.0000
6.500 1.0706 0.03475 0.02672 -0.0937 0.5567 1.0000
6.750 1.1441 0.03248 0.02439 -0.0992 0.5544 1.0000
7.000 1.1400 0.03363 0.02561 -0.0947 0.5412 1.0000
7.250 1.1448 0.03442 0.02644 -0.0914 0.5296 1.0000
7.500 1.2147 0.03230 0.02426 -0.0964 0.5244 1.0000
7.750 1.2176 0.03310 0.02510 -0.0928 0.5123 1.0000
8.000 1.2887 0.03114 0.02300 -0.0983 0.5062 1.0000
8.250 1.2795 0.03244 0.02442 -0.0931 0.4938 1.0000
8.500 1.2992 0.03263 0.02462 -0.0918 0.4846 1.0000
8.750 1.3258 0.03258 0.02457 -0.0915 0.4759 1.0000
9.000 1.3228 0.03386 0.02594 -0.0874 0.4669 1.0000
9.250 1.3537 0.03375 0.02583 -0.0878 0.4597 1.0000
9.500 1.3476 0.03530 0.02749 -0.0836 0.4513 1.0000
9.750 1.3745 0.03526 0.02746 -0.0835 0.4442 1.0000
10.000 1.3718 0.03676 0.02906 -0.0801 0.4364 1.0000
10.250 1.3921 0.03700 0.02935 -0.0792 0.4291 1.0000
10.500 1.3957 0.03821 0.03065 -0.0767 0.4215 1.0000
10.750 1.4219 0.03783 0.03026 -0.0762 0.4131 1.0000
11.000 1.4132 0.03978 0.03233 -0.0728 0.4046 1.0000
11.250 1.4472 0.03855 0.03100 -0.0727 0.3939 1.0000
11.500 1.4546 0.03928 0.03176 -0.0707 0.3834 1.0000
11.750 1.4551 0.04075 0.03328 -0.0683 0.3737 1.0000
12.000 1.4782 0.04065 0.03310 -0.0676 0.3628 1.0000
12.250 1.5036 0.04050 0.03278 -0.0671 0.3503 1.0000
12.500 1.4935 0.04287 0.03529 -0.0642 0.3407 1.0000
12.750 1.5040 0.04393 0.03633 -0.0628 0.3300 1.0000
13.000 1.5254 0.04428 0.03655 -0.0622 0.3183 1.0000
13.250 1.5124 0.04703 0.03947 -0.0596 0.3095 1.0000
13.500 1.5184 0.04845 0.04089 -0.0581 0.2993 1.0000
13.750 1.5177 0.05039 0.04288 -0.0565 0.2900 1.0000
14.000 1.5128 0.05283 0.04545 -0.0548 0.2821 1.0000
14.250 1.5113 0.05496 0.04765 -0.0535 0.2738 1.0000
14.500 1.5035 0.05780 0.05065 -0.0521 0.2663 1.0000
14.750 1.4959 0.06066 0.05361 -0.0509 0.2582 1.0000
15.000 1.4835 0.06419 0.05728 -0.0500 0.2504 1.0000
15.250 1.4744 0.06748 0.06067 -0.0493 0.2421 1.0000
15.500 1.4609 0.07162 0.06498 -0.0489 0.2347 1.0000
15.750 1.4533 0.07514 0.06858 -0.0487 0.2268 1.0000
16.000 1.4390 0.07978 0.07340 -0.0488 0.2194 1.0000
16.250 1.4330 0.08333 0.07700 -0.0490 0.2114 1.0000
16.500 1.4150 0.08884 0.08269 -0.0496 0.2037 1.0000
16.750 1.4118 0.09222 0.08608 -0.0500 0.1960 1.0000
17.000 1.3950 0.09781 0.09186 -0.0509 0.1891 1.0000
17.250 1.3913 0.10141 0.09545 -0.0515 0.1813 1.0000
17.500 1.3755 0.10701 0.10118 -0.0528 0.1738 1.0000
17.750 1.3677 0.11140 0.10558 -0.0538 0.1658 1.0000
18.000 1.3561 0.11652 0.11080 -0.0552 0.1586 1.0000
18.250 1.3449 0.12166 0.11601 -0.0568 0.1510 1.0000
18.500 1.3353 0.12657 0.12090 -0.0585 0.1418 1.0000
18.750 1.3181 0.13315 0.12768 -0.0610 0.1347 1.0000
19.000 1.3043 0.13919 0.13378 -0.0636 0.1248 1.0000
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Polar data table (+)
Polar graphs
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