GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Reynolds number: 500,000 Max Cl/Cd: 102.94 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe115-il-500000-n5.txt Download as CSV file: xf-goe115-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 115 (MVA MK.2) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4194 0.08650 0.08434 -0.0390 1.0000 0.0065
-9.500 -0.4323 0.08002 0.07791 -0.0416 1.0000 0.0064
-9.250 -0.5887 0.02888 0.02574 -0.0856 0.9735 0.0057
-9.000 -0.5632 0.02563 0.02211 -0.0890 0.9641 0.0060
-8.750 -0.5346 0.02365 0.01986 -0.0913 0.9531 0.0062
-8.500 -0.5048 0.02195 0.01791 -0.0933 0.9414 0.0066
-8.250 -0.4759 0.02022 0.01588 -0.0949 0.9279 0.0073
-8.000 -0.4506 0.01819 0.01346 -0.0955 0.9117 0.0079
-7.750 -0.4271 0.01658 0.01153 -0.0955 0.8953 0.0084
-7.500 -0.4020 0.01590 0.01069 -0.0953 0.8797 0.0090
-7.250 -0.3766 0.01550 0.01015 -0.0951 0.8654 0.0096
-6.750 -0.3270 0.01441 0.00870 -0.0943 0.8398 0.0115
-6.500 -0.3022 0.01385 0.00799 -0.0939 0.8278 0.0126
-6.250 -0.2754 0.01387 0.00793 -0.0937 0.8160 0.0137
-6.000 -0.2493 0.01366 0.00760 -0.0934 0.8042 0.0150
-5.750 -0.2238 0.01326 0.00704 -0.0930 0.7922 0.0167
-5.500 -0.1970 0.01322 0.00685 -0.0928 0.7801 0.0181
-5.250 -0.1723 0.01261 0.00616 -0.0924 0.7682 0.0196
-5.000 -0.1464 0.01232 0.00578 -0.0921 0.7562 0.0210
-4.750 -0.1203 0.01207 0.00543 -0.0919 0.7440 0.0230
-4.500 -0.0941 0.01182 0.00506 -0.0915 0.7315 0.0247
-4.250 -0.0679 0.01159 0.00472 -0.0912 0.7187 0.0257
-4.000 -0.0413 0.01150 0.00451 -0.0910 0.7058 0.0265
-3.500 0.0098 0.01066 0.00344 -0.0903 0.6809 0.0281
-3.250 0.0358 0.01034 0.00301 -0.0900 0.6701 0.0295
-3.000 0.0623 0.01012 0.00269 -0.0897 0.6607 0.0302
-2.750 0.0891 0.00993 0.00241 -0.0895 0.6518 0.0311
-2.500 0.1160 0.00977 0.00217 -0.0894 0.6442 0.0321
-2.250 0.1430 0.00966 0.00196 -0.0892 0.6368 0.0332
-2.000 0.1702 0.00958 0.00180 -0.0891 0.6304 0.0341
-1.750 0.1975 0.00951 0.00167 -0.0889 0.6240 0.0347
-1.500 0.2247 0.00947 0.00156 -0.0888 0.6183 0.0353
-1.250 0.2521 0.00943 0.00147 -0.0887 0.6125 0.0359
-1.000 0.2793 0.00940 0.00140 -0.0886 0.6072 0.0376
-0.750 0.3067 0.00936 0.00135 -0.0885 0.6027 0.0414
-0.500 0.3341 0.00931 0.00132 -0.0884 0.5978 0.0451
-0.250 0.3601 0.00896 0.00123 -0.0882 0.5928 0.1555
0.000 0.3864 0.00872 0.00126 -0.0881 0.5876 0.2386
0.250 0.4136 0.00871 0.00131 -0.0880 0.5821 0.2614
0.500 0.4408 0.00875 0.00136 -0.0879 0.5773 0.2782
0.750 0.4682 0.00875 0.00140 -0.0878 0.5727 0.2870
1.000 0.4957 0.00878 0.00145 -0.0877 0.5679 0.2948
1.250 0.5229 0.00881 0.00150 -0.0876 0.5637 0.3024
1.500 0.5502 0.00884 0.00156 -0.0875 0.5600 0.3094
1.750 0.5776 0.00885 0.00163 -0.0875 0.5555 0.3174
2.000 0.6047 0.00887 0.00171 -0.0873 0.5511 0.3298
2.500 0.6588 0.00888 0.00190 -0.0871 0.5424 0.3599
2.750 0.6858 0.00890 0.00199 -0.0870 0.5374 0.3715
3.000 0.7126 0.00893 0.00211 -0.0868 0.5331 0.3876
3.250 0.7391 0.00891 0.00221 -0.0866 0.5236 0.4163
3.500 0.7644 0.00879 0.00235 -0.0862 0.5142 0.4998
4.000 0.8307 0.00807 0.00267 -0.0888 0.4655 1.0000
4.250 0.8520 0.00850 0.00284 -0.0877 0.4012 1.0000
4.500 0.8674 0.00952 0.00336 -0.0857 0.3043 1.0000
4.750 0.8790 0.01098 0.00412 -0.0833 0.1662 1.0000
5.000 0.8900 0.01247 0.00503 -0.0808 0.0433 1.0000
5.250 0.9122 0.01293 0.00543 -0.0799 0.0267 1.0000
5.500 0.9346 0.01336 0.00584 -0.0790 0.0185 1.0000
5.750 0.9567 0.01380 0.00629 -0.0781 0.0148 1.0000
6.000 0.9771 0.01439 0.00698 -0.0768 0.0122 1.0000
6.250 0.9992 0.01480 0.00743 -0.0758 0.0110 1.0000
6.500 1.0201 0.01528 0.00796 -0.0747 0.0099 1.0000
6.750 1.0400 0.01583 0.00856 -0.0735 0.0091 1.0000
7.000 1.0573 0.01655 0.00933 -0.0718 0.0083 1.0000
7.250 1.0706 0.01753 0.01041 -0.0695 0.0077 1.0000
7.500 1.0871 0.01822 0.01120 -0.0677 0.0074 1.0000
7.750 1.1020 0.01898 0.01204 -0.0657 0.0071 1.0000
8.000 1.1175 0.01963 0.01275 -0.0639 0.0065 1.0000
8.250 1.1297 0.02034 0.01351 -0.0615 0.0061 1.0000
8.500 1.1416 0.02107 0.01428 -0.0591 0.0058 1.0000
8.750 1.1512 0.02197 0.01525 -0.0565 0.0056 1.0000
9.000 1.1595 0.02302 0.01636 -0.0539 0.0054 1.0000
9.250 1.1641 0.02448 0.01790 -0.0510 0.0051 1.0000
9.500 1.1716 0.02589 0.01941 -0.0486 0.0050 1.0000
9.750 1.1809 0.02727 0.02094 -0.0466 0.0049 1.0000
10.000 1.1917 0.02859 0.02240 -0.0448 0.0047 1.0000
10.250 1.2015 0.03025 0.02420 -0.0429 0.0046 1.0000
10.500 1.2118 0.03203 0.02613 -0.0412 0.0045 1.0000
10.750 1.2220 0.03394 0.02823 -0.0396 0.0043 1.0000
11.000 1.2311 0.03616 0.03065 -0.0379 0.0042 1.0000
11.250 1.2383 0.03822 0.03290 -0.0363 0.0040 1.0000
11.500 1.2443 0.03981 0.03461 -0.0350 0.0038 1.0000
11.750 1.2485 0.04178 0.03672 -0.0337 0.0037 1.0000
12.000 1.2467 0.04548 0.04073 -0.0319 0.0037 1.0000
12.250 1.2517 0.04647 0.04173 -0.0314 0.0035 1.0000
12.500 1.2522 0.04879 0.04416 -0.0306 0.0034 1.0000
12.750 1.2474 0.05225 0.04787 -0.0298 0.0034 1.0000
13.000 1.2488 0.05424 0.04989 -0.0298 0.0033 1.0000
13.250 1.2390 0.05848 0.05437 -0.0295 0.0033 1.0000
13.500 1.2286 0.06280 0.05888 -0.0297 0.0033 1.0000
13.750 1.2140 0.06799 0.06430 -0.0304 0.0032 1.0000
14.000 1.1907 0.07479 0.07136 -0.0320 0.0032 1.0000
14.250 1.1766 0.08044 0.07719 -0.0338 0.0032 1.0000
14.500 1.1587 0.08711 0.08406 -0.0363 0.0032 1.0000
14.750 1.1368 0.09505 0.09220 -0.0398 0.0032 1.0000
15.000 1.1176 0.10310 0.10044 -0.0438 0.0033 1.0000
15.250 1.0958 0.11234 0.10985 -0.0490 0.0032 1.0000
15.500 1.0635 0.12564 0.12336 -0.0566 0.0033 1.0000
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Polar data table (+)
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