GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 417 AIRFOIL (goe417-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.21 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe417-il-1000000.txt Download as CSV file: xf-goe417-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 417 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1786 0.08940 0.08792 -0.0397 0.9938 0.0097
-8.750 -0.1687 0.08552 0.08404 -0.0422 0.9916 0.0097
-8.500 -0.1593 0.08076 0.07929 -0.0440 0.9896 0.0098
-8.250 -0.1460 0.07710 0.07563 -0.0464 0.9875 0.0100
-8.000 -0.1315 0.07350 0.07202 -0.0493 0.9854 0.0102
-7.750 -0.1167 0.06985 0.06837 -0.0525 0.9838 0.0106
-7.500 -0.2025 0.08436 0.08282 -0.0453 0.9867 0.0101
-7.250 -0.1801 0.08109 0.07954 -0.0503 0.9841 0.0107
-7.000 -0.1590 0.07752 0.07597 -0.0553 0.9793 0.0109
-6.750 -0.1326 0.07360 0.07204 -0.0619 0.9752 0.0123
-6.500 -0.0956 0.06900 0.06741 -0.0725 0.9722 0.0126
-6.250 -0.0608 0.06455 0.06292 -0.0821 0.9666 0.0127
-6.000 -0.0329 0.06069 0.05902 -0.0880 0.9593 0.0127
-5.750 -0.0144 0.05651 0.05482 -0.0909 0.9517 0.0130
-5.500 0.0069 0.05396 0.05223 -0.0933 0.9426 0.0132
-5.250 0.0271 0.05163 0.04985 -0.0954 0.9317 0.0137
-5.000 0.0499 0.04905 0.04721 -0.0981 0.9206 0.0149
-4.750 0.0868 0.04509 0.04310 -0.1045 0.9096 0.0162
-4.500 0.1134 0.04177 0.03968 -0.1073 0.8998 0.0162
-4.250 0.1406 0.03850 0.03630 -0.1097 0.8903 0.0163
-4.000 0.1590 0.03541 0.03313 -0.1109 0.8812 0.0168
-3.750 0.1828 0.03374 0.03138 -0.1118 0.8710 0.0174
-3.500 0.2099 0.03167 0.02921 -0.1131 0.8615 0.0188
-3.250 0.2487 0.02841 0.02570 -0.1153 0.8527 0.0205
-3.000 0.2781 0.02531 0.02238 -0.1163 0.8431 0.0206
-2.750 0.3013 0.02176 0.01865 -0.1173 0.8332 0.0214
-2.500 0.3263 0.02071 0.01749 -0.1174 0.8222 0.0221
-2.250 0.3527 0.01939 0.01601 -0.1174 0.8105 0.0234
-2.000 0.3837 0.01815 0.01448 -0.1168 0.7982 0.0261
-1.750 0.4110 0.01660 0.01264 -0.1165 0.7853 0.0262
1.250 0.7139 0.00898 0.00256 -0.1096 0.4775 0.0356
1.500 0.7386 0.00915 0.00256 -0.1089 0.4401 0.0333
1.750 0.7632 0.00907 0.00234 -0.1082 0.4105 0.0332
2.000 0.7886 0.00915 0.00231 -0.1077 0.3889 0.0340
2.250 0.8139 0.00907 0.00216 -0.1072 0.3725 0.0343
2.500 0.8396 0.00907 0.00209 -0.1068 0.3591 0.0347
2.750 0.8655 0.00908 0.00206 -0.1063 0.3481 0.0352
3.000 0.8915 0.00913 0.00208 -0.1059 0.3386 0.0364
3.250 0.9174 0.00922 0.00212 -0.1055 0.3297 0.0369
3.500 0.9436 0.00929 0.00217 -0.1052 0.3224 0.0382
3.750 0.9695 0.00939 0.00224 -0.1048 0.3148 0.0413
4.000 0.9956 0.00947 0.00234 -0.1044 0.3084 0.0538
4.250 1.0247 0.00818 0.00274 -0.1054 0.3012 1.0000
4.500 1.0505 0.00833 0.00286 -0.1050 0.2949 1.0000
4.750 1.0761 0.00849 0.00299 -0.1045 0.2876 1.0000
5.000 1.1016 0.00866 0.00313 -0.1041 0.2787 1.0000
5.250 1.1265 0.00888 0.00328 -0.1036 0.2633 1.0000
5.500 1.1512 0.00912 0.00345 -0.1031 0.2473 1.0000
5.750 1.1757 0.00938 0.00364 -0.1025 0.2315 1.0000
6.000 1.1992 0.00972 0.00388 -0.1018 0.2098 1.0000
6.250 1.2216 0.01017 0.00417 -0.1010 0.1837 1.0000
6.500 1.2440 0.01062 0.00450 -0.1001 0.1616 1.0000
6.750 1.2668 0.01102 0.00482 -0.0994 0.1467 1.0000
7.000 1.2895 0.01141 0.00516 -0.0986 0.1333 1.0000
7.250 1.3123 0.01179 0.00548 -0.0978 0.1212 1.0000
7.500 1.3341 0.01227 0.00587 -0.0969 0.1044 1.0000
7.750 1.3450 0.01384 0.00699 -0.0943 0.0308 1.0000
8.000 1.3630 0.01468 0.00773 -0.0928 0.0157 1.0000
8.250 1.3846 0.01513 0.00824 -0.0918 0.0141 1.0000
8.500 1.4051 0.01565 0.00881 -0.0906 0.0128 1.0000
8.750 1.4240 0.01632 0.00954 -0.0892 0.0115 1.0000
9.000 1.4413 0.01711 0.01044 -0.0875 0.0106 1.0000
9.250 1.4605 0.01766 0.01106 -0.0862 0.0102 1.0000
9.500 1.4787 0.01825 0.01171 -0.0847 0.0096 1.0000
9.750 1.4961 0.01886 0.01238 -0.0832 0.0090 1.0000
10.000 1.5120 0.01953 0.01311 -0.0814 0.0085 1.0000
10.250 1.5226 0.02041 0.01405 -0.0787 0.0079 1.0000
10.500 1.5245 0.02166 0.01543 -0.0747 0.0076 1.0000
10.750 1.5252 0.02299 0.01689 -0.0706 0.0073 1.0000
11.000 1.5350 0.02381 0.01779 -0.0682 0.0072 1.0000
11.250 1.5425 0.02481 0.01888 -0.0655 0.0070 1.0000
11.500 1.5483 0.02595 0.02011 -0.0628 0.0068 1.0000
11.750 1.5539 0.02716 0.02140 -0.0603 0.0066 1.0000
12.000 1.5576 0.02856 0.02290 -0.0579 0.0064 1.0000
12.250 1.5562 0.03044 0.02489 -0.0551 0.0063 1.0000
12.500 1.5595 0.03206 0.02660 -0.0531 0.0061 1.0000
12.750 1.5594 0.03408 0.02872 -0.0512 0.0060 1.0000
13.000 1.5602 0.03614 0.03087 -0.0496 0.0058 1.0000
13.250 1.5610 0.03834 0.03316 -0.0483 0.0057 1.0000
13.500 1.5588 0.04098 0.03589 -0.0473 0.0055 1.0000
13.750 1.5558 0.04387 0.03888 -0.0466 0.0054 1.0000
14.000 1.5493 0.04740 0.04251 -0.0463 0.0053 1.0000
14.250 1.5366 0.05195 0.04718 -0.0463 0.0052 1.0000
14.500 1.5148 0.05799 0.05338 -0.0468 0.0050 1.0000
14.750 1.5037 0.06287 0.05840 -0.0476 0.0049 1.0000
15.000 1.4977 0.06723 0.06288 -0.0486 0.0049 1.0000
15.250 1.4942 0.07148 0.06725 -0.0500 0.0049 1.0000
15.500 1.4886 0.07613 0.07202 -0.0515 0.0048 1.0000
15.750 1.4827 0.08101 0.07702 -0.0533 0.0047 1.0000
16.000 1.4755 0.08619 0.08232 -0.0553 0.0047 1.0000
16.250 1.4681 0.09153 0.08779 -0.0575 0.0046 1.0000
16.500 1.4602 0.09703 0.09341 -0.0598 0.0046 1.0000
16.750 1.4524 0.10269 0.09919 -0.0623 0.0046 1.0000
17.000 1.4438 0.10856 0.10519 -0.0650 0.0045 1.0000
17.250 1.4358 0.11442 0.11117 -0.0678 0.0045 1.0000
17.500 1.4266 0.12058 0.11746 -0.0708 0.0045 1.0000
17.750 1.4183 0.12673 0.12372 -0.0740 0.0044 1.0000
18.000 1.4088 0.13316 0.13029 -0.0775 0.0044 1.0000
18.250 1.3998 0.13964 0.13689 -0.0811 0.0044 1.0000
18.500 1.3900 0.14640 0.14377 -0.0850 0.0044 1.0000
18.750 1.3801 0.15333 0.15083 -0.0892 0.0044 1.0000
19.000 1.3704 0.16036 0.15799 -0.0936 0.0043 1.0000
19.250 1.3599 0.16779 0.16554 -0.0983 0.0043 1.0000
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