GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 610 B AIRFOIL (goe610b-il) Reynolds number: 200,000 Max Cl/Cd: 84.02 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe610b-il-200000-n5.txt Download as CSV file: xf-goe610b-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610 B AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2876 0.10405 0.10058 -0.0358 1.0000 0.0175
-9.000 -0.2868 0.10131 0.09789 -0.0357 1.0000 0.0173
-8.750 -0.2873 0.09879 0.09542 -0.0355 1.0000 0.0173
-8.500 -0.2832 0.09563 0.09231 -0.0372 0.9977 0.0178
-8.250 -0.2693 0.09146 0.08813 -0.0417 0.9874 0.0179
-8.000 -0.2567 0.08700 0.08368 -0.0472 0.9753 0.0184
-7.750 -0.2422 0.08271 0.07940 -0.0521 0.9632 0.0183
-7.500 -0.2245 0.07807 0.07473 -0.0582 0.9506 0.0184
-7.250 -0.2046 0.07295 0.06958 -0.0655 0.9372 0.0186
-7.000 -0.1804 0.06742 0.06398 -0.0742 0.9236 0.0193
-6.750 -0.1598 0.06424 0.06078 -0.0779 0.9127 0.0205
-6.500 -0.1350 0.06191 0.05838 -0.0813 0.9025 0.0217
-6.000 -0.0888 0.05407 0.05033 -0.0910 0.8794 0.0231
-5.750 -0.0663 0.05047 0.04658 -0.0948 0.8687 0.0246
-5.500 -0.0426 0.04633 0.04225 -0.0988 0.8591 0.0269
-5.250 -0.0185 0.04042 0.03602 -0.1030 0.8496 0.0287
-5.000 0.0043 0.03551 0.03078 -0.1051 0.8407 0.0313
-4.500 0.0492 0.03356 0.02861 -0.1052 0.8238 0.0347
-4.250 0.0732 0.03116 0.02594 -0.1056 0.8160 0.0377
-4.000 0.0973 0.02746 0.02176 -0.1057 0.8076 0.0411
-3.750 0.1203 0.02436 0.01815 -0.1053 0.8000 0.0440
-3.500 0.1440 0.02416 0.01795 -0.1050 0.7914 0.0458
-3.250 0.1680 0.02284 0.01639 -0.1046 0.7831 0.0477
-3.000 0.1924 0.02114 0.01433 -0.1040 0.7748 0.0487
-2.750 0.2169 0.01970 0.01255 -0.1033 0.7658 0.0498
-2.500 0.2424 0.01859 0.01107 -0.1027 0.7574 0.0516
-2.250 0.2674 0.01753 0.00976 -0.1020 0.7475 0.0515
-2.000 0.2930 0.01662 0.00859 -0.1014 0.7380 0.0514
-1.750 0.3189 0.01585 0.00758 -0.1009 0.7283 0.0516
-1.500 0.3447 0.01523 0.00676 -0.1003 0.7173 0.0520
-1.250 0.3708 0.01475 0.00608 -0.0998 0.7067 0.0528
-1.000 0.3967 0.01416 0.00538 -0.0993 0.6964 0.0539
-0.750 0.4222 0.01370 0.00487 -0.0987 0.6851 0.0554
-0.500 0.4476 0.01340 0.00450 -0.0982 0.6728 0.0571
-0.250 0.4729 0.01317 0.00418 -0.0975 0.6600 0.0586
0.000 0.4981 0.01298 0.00391 -0.0969 0.6480 0.0598
0.250 0.5233 0.01285 0.00369 -0.0963 0.6364 0.0608
0.500 0.5487 0.01277 0.00354 -0.0957 0.6269 0.0621
0.750 0.5735 0.01259 0.00337 -0.0951 0.6172 0.0651
1.000 0.5988 0.01254 0.00328 -0.0946 0.6085 0.0669
1.250 0.6243 0.01248 0.00321 -0.0940 0.6007 0.0674
1.500 0.6497 0.01248 0.00315 -0.0935 0.5936 0.0679
1.750 0.6752 0.01248 0.00314 -0.0930 0.5853 0.0686
2.000 0.7006 0.01252 0.00313 -0.0924 0.5779 0.0697
2.250 0.7262 0.01255 0.00317 -0.0920 0.5708 0.0711
2.500 0.7519 0.01260 0.00324 -0.0915 0.5654 0.0742
2.750 0.7776 0.01263 0.00335 -0.0911 0.5595 0.0836
3.000 0.8028 0.01265 0.00346 -0.0905 0.5526 0.1268
3.500 0.8937 0.01142 0.00391 -0.0988 0.5357 1.0000
3.750 0.9178 0.01157 0.00407 -0.0980 0.5277 1.0000
4.000 0.9415 0.01175 0.00422 -0.0972 0.5188 1.0000
4.250 0.9653 0.01190 0.00440 -0.0964 0.5097 1.0000
4.500 0.9887 0.01208 0.00460 -0.0955 0.4998 1.0000
4.750 1.0118 0.01225 0.00479 -0.0945 0.4881 1.0000
5.000 1.0349 0.01242 0.00501 -0.0936 0.4752 1.0000
5.250 1.0572 0.01262 0.00522 -0.0925 0.4582 1.0000
5.500 1.0788 0.01284 0.00546 -0.0913 0.4324 1.0000
5.750 1.0964 0.01322 0.00568 -0.0894 0.3877 1.0000
6.000 1.1119 0.01376 0.00602 -0.0872 0.3537 1.0000
6.250 1.1288 0.01429 0.00646 -0.0853 0.3325 1.0000
6.500 1.1462 0.01482 0.00696 -0.0835 0.3159 1.0000
6.750 1.1618 0.01544 0.00749 -0.0815 0.2965 1.0000
7.000 1.1787 0.01599 0.00801 -0.0797 0.2775 1.0000
7.250 1.1954 0.01653 0.00853 -0.0779 0.2564 1.0000
7.500 1.2109 0.01712 0.00906 -0.0760 0.2336 1.0000
7.750 1.2249 0.01778 0.00964 -0.0738 0.1985 1.0000
8.000 1.2261 0.01918 0.01055 -0.0699 0.1326 1.0000
8.250 1.2338 0.02010 0.01139 -0.0668 0.1176 1.0000
8.500 1.2427 0.02094 0.01224 -0.0639 0.1047 1.0000
8.750 1.2544 0.02166 0.01301 -0.0615 0.0869 1.0000
9.000 1.2560 0.02303 0.01408 -0.0580 0.0483 1.0000
9.500 1.2611 0.02583 0.01680 -0.0517 0.0239 1.0000
9.750 1.2670 0.02712 0.01816 -0.0493 0.0212 1.0000
10.000 1.2744 0.02837 0.01955 -0.0471 0.0198 1.0000
10.250 1.2805 0.02977 0.02108 -0.0450 0.0183 1.0000
10.500 1.2853 0.03133 0.02276 -0.0430 0.0168 1.0000
10.750 1.2880 0.03314 0.02468 -0.0410 0.0155 1.0000
11.000 1.2876 0.03529 0.02696 -0.0390 0.0147 1.0000
11.250 1.2843 0.03779 0.02960 -0.0371 0.0140 1.0000
11.500 1.2845 0.04008 0.03201 -0.0356 0.0136 1.0000
11.750 1.2864 0.04227 0.03434 -0.0342 0.0131 1.0000
12.000 1.2882 0.04455 0.03674 -0.0331 0.0128 1.0000
12.250 1.2899 0.04691 0.03923 -0.0320 0.0125 1.0000
12.500 1.2919 0.04931 0.04174 -0.0311 0.0119 1.0000
12.750 1.2939 0.05175 0.04436 -0.0304 0.0114 1.0000
13.000 1.2963 0.05420 0.04691 -0.0299 0.0108 1.0000
13.250 1.2970 0.05691 0.04973 -0.0293 0.0105 1.0000
13.500 1.2971 0.05975 0.05267 -0.0289 0.0102 1.0000
13.750 1.2967 0.06273 0.05575 -0.0285 0.0099 1.0000
14.000 1.2960 0.06584 0.05896 -0.0279 0.0097 1.0000
14.250 1.2954 0.06904 0.06227 -0.0274 0.0095 1.0000
14.500 1.2959 0.07220 0.06560 -0.0273 0.0094 1.0000
14.750 1.2950 0.07563 0.06921 -0.0274 0.0092 1.0000
15.000 1.2929 0.07931 0.07308 -0.0277 0.0091 1.0000
15.250 1.2885 0.08342 0.07741 -0.0283 0.0090 1.0000
15.500 1.2835 0.08772 0.08190 -0.0292 0.0089 1.0000
15.750 1.2759 0.09258 0.08698 -0.0305 0.0087 1.0000
16.000 1.2674 0.09770 0.09230 -0.0322 0.0086 1.0000
16.250 1.2574 0.10325 0.09806 -0.0342 0.0086 1.0000
16.500 1.2469 0.10911 0.10411 -0.0368 0.0085 1.0000
16.750 1.2352 0.11541 0.11061 -0.0397 0.0085 1.0000
17.000 1.2227 0.12215 0.11755 -0.0432 0.0084 1.0000
17.250 1.2109 0.12908 0.12466 -0.0471 0.0082 1.0000
17.500 1.1981 0.13652 0.13227 -0.0515 0.0082 1.0000
17.750 1.1829 0.14491 0.14085 -0.0565 0.0083 1.0000
18.000 1.1683 0.15352 0.14963 -0.0619 0.0083 1.0000
18.250 1.1502 0.16355 0.15982 -0.0681 0.0084 1.0000
18.500 1.1320 0.17425 0.17066 -0.0748 0.0087 1.0000
18.750 1.1135 0.18604 0.18255 -0.0819 0.0090 1.0000
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Polar data table (+)
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