GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Reynolds number: 500,000 Max Cl/Cd: 104.54 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe117-il-500000-n5.txt Download as CSV file: xf-goe117-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 117 (MVA MK.4) 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3673 0.09060 0.08845 -0.0407 1.0000 0.0064
-9.250 -0.3674 0.08526 0.08314 -0.0440 0.9982 0.0064
-8.750 -0.4372 0.02455 0.02123 -0.1090 0.9269 0.0061
-8.500 -0.4124 0.02130 0.01744 -0.1114 0.9127 0.0063
-8.250 -0.3911 0.01876 0.01446 -0.1121 0.8997 0.0067
-8.000 -0.3671 0.01755 0.01297 -0.1122 0.8898 0.0071
-7.750 -0.3425 0.01664 0.01184 -0.1122 0.8808 0.0075
-7.500 -0.3179 0.01589 0.01089 -0.1120 0.8715 0.0082
-7.250 -0.2934 0.01511 0.00990 -0.1117 0.8628 0.0089
-6.750 -0.2449 0.01342 0.00780 -0.1109 0.8459 0.0106
-6.500 -0.2190 0.01304 0.00732 -0.1107 0.8383 0.0116
-6.250 -0.1930 0.01267 0.00684 -0.1104 0.8300 0.0129
-6.000 -0.1668 0.01239 0.00642 -0.1101 0.8221 0.0142
-5.750 -0.1406 0.01213 0.00611 -0.1099 0.8131 0.0165
-5.500 -0.1141 0.01195 0.00586 -0.1097 0.8035 0.0188
-5.250 -0.0877 0.01177 0.00556 -0.1094 0.7932 0.0212
-5.000 -0.0608 0.01179 0.00547 -0.1092 0.7817 0.0226
-4.750 -0.0357 0.01124 0.00478 -0.1087 0.7692 0.0247
-4.500 -0.0099 0.01094 0.00439 -0.1084 0.7550 0.0269
-4.250 0.0159 0.01074 0.00407 -0.1080 0.7379 0.0287
-4.000 0.0414 0.01053 0.00373 -0.1076 0.7164 0.0301
-3.750 0.0665 0.01038 0.00340 -0.1070 0.6913 0.0314
-3.250 0.1168 0.01013 0.00281 -0.1059 0.6488 0.0328
-3.000 0.1426 0.01001 0.00256 -0.1055 0.6343 0.0333
-2.750 0.1687 0.00989 0.00231 -0.1052 0.6232 0.0336
-2.500 0.1952 0.00979 0.00210 -0.1049 0.6138 0.0340
-2.250 0.2218 0.00967 0.00188 -0.1046 0.6059 0.0357
-2.000 0.2484 0.00956 0.00170 -0.1044 0.5985 0.0399
-1.750 0.2751 0.00948 0.00159 -0.1042 0.5919 0.0454
-1.500 0.3009 0.00914 0.00149 -0.1040 0.5855 0.1173
-1.250 0.3275 0.00911 0.00146 -0.1038 0.5801 0.1443
-1.000 0.3547 0.00909 0.00143 -0.1037 0.5751 0.1541
-0.750 0.3815 0.00906 0.00140 -0.1035 0.5702 0.1644
-0.500 0.4083 0.00904 0.00139 -0.1034 0.5657 0.1766
-0.250 0.4353 0.00899 0.00140 -0.1033 0.5612 0.1956
0.000 0.4619 0.00891 0.00147 -0.1031 0.5569 0.2443
0.250 0.4886 0.00892 0.00153 -0.1030 0.5529 0.2767
0.500 0.5157 0.00893 0.00156 -0.1029 0.5491 0.2902
0.750 0.5428 0.00894 0.00160 -0.1028 0.5450 0.2997
1.000 0.5697 0.00897 0.00164 -0.1026 0.5409 0.3093
1.250 0.5964 0.00901 0.00169 -0.1025 0.5364 0.3196
1.500 0.6234 0.00900 0.00174 -0.1023 0.5314 0.3315
1.750 0.6501 0.00901 0.00182 -0.1022 0.5269 0.3492
2.000 0.6764 0.00901 0.00190 -0.1020 0.5232 0.3809
2.250 0.7017 0.00875 0.00203 -0.1017 0.5198 0.5196
2.750 0.7681 0.00795 0.00230 -0.1042 0.5072 1.0000
3.000 0.7939 0.00804 0.00238 -0.1038 0.4979 1.0000
3.250 0.8196 0.00815 0.00250 -0.1034 0.4910 1.0000
3.500 0.8450 0.00827 0.00261 -0.1030 0.4803 1.0000
3.750 0.8704 0.00839 0.00273 -0.1025 0.4682 1.0000
4.000 0.8949 0.00856 0.00286 -0.1019 0.4497 1.0000
4.250 0.9169 0.00888 0.00302 -0.1009 0.4053 1.0000
4.500 0.9309 0.00988 0.00349 -0.0986 0.3055 1.0000
4.750 0.9324 0.01207 0.00470 -0.0946 0.0988 1.0000
5.000 0.9513 0.01276 0.00521 -0.0932 0.0519 1.0000
5.250 0.9729 0.01321 0.00560 -0.0922 0.0374 1.0000
5.500 0.9950 0.01360 0.00600 -0.0913 0.0295 1.0000
5.750 1.0170 0.01398 0.00640 -0.0904 0.0237 1.0000
6.000 1.0376 0.01446 0.00687 -0.0892 0.0168 1.0000
6.250 1.0587 0.01488 0.00733 -0.0881 0.0144 1.0000
6.500 1.0786 0.01536 0.00785 -0.0868 0.0126 1.0000
6.750 1.0960 0.01602 0.00857 -0.0851 0.0108 1.0000
7.000 1.1122 0.01670 0.00933 -0.0832 0.0097 1.0000
7.250 1.1297 0.01724 0.00993 -0.0816 0.0088 1.0000
7.500 1.1450 0.01788 0.01063 -0.0796 0.0082 1.0000
7.750 1.1579 0.01852 0.01133 -0.0772 0.0077 1.0000
8.000 1.1684 0.01924 0.01210 -0.0744 0.0072 1.0000
8.250 1.1756 0.02015 0.01308 -0.0712 0.0069 1.0000
8.500 1.1773 0.02143 0.01446 -0.0674 0.0065 1.0000
8.750 1.1851 0.02245 0.01561 -0.0647 0.0064 1.0000
9.000 1.1933 0.02351 0.01676 -0.0622 0.0061 1.0000
9.250 1.2023 0.02458 0.01792 -0.0600 0.0058 1.0000
9.500 1.2109 0.02574 0.01916 -0.0579 0.0054 1.0000
9.750 1.2209 0.02684 0.02034 -0.0562 0.0051 1.0000
10.000 1.2288 0.02818 0.02175 -0.0543 0.0049 1.0000
10.250 1.2372 0.02954 0.02319 -0.0526 0.0047 1.0000
10.500 1.2450 0.03103 0.02476 -0.0509 0.0046 1.0000
10.750 1.2514 0.03271 0.02652 -0.0493 0.0044 1.0000
11.000 1.2558 0.03489 0.02883 -0.0473 0.0043 1.0000
11.250 1.2650 0.03659 0.03069 -0.0459 0.0042 1.0000
11.500 1.2735 0.03850 0.03276 -0.0445 0.0041 1.0000
11.750 1.2816 0.04061 0.03508 -0.0431 0.0039 1.0000
12.000 1.2879 0.04316 0.03786 -0.0416 0.0039 1.0000
12.250 1.2921 0.04612 0.04113 -0.0401 0.0037 1.0000
12.500 1.2914 0.04982 0.04515 -0.0386 0.0036 1.0000
12.750 1.2839 0.05456 0.05026 -0.0371 0.0035 1.0000
13.000 1.2698 0.06015 0.05620 -0.0360 0.0035 1.0000
13.250 1.2487 0.06685 0.06325 -0.0354 0.0034 1.0000
13.500 1.2243 0.07428 0.07099 -0.0357 0.0034 1.0000
13.750 1.2000 0.08170 0.07866 -0.0369 0.0033 1.0000
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Polar data table (+)
Polar graphs
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