GOE 427 AIRFOIL (goe427-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 427 AIRFOIL (goe427-il) Reynolds number: 500,000 Max Cl/Cd: 94.74 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe427-il-500000-n5.txt Download as CSV file: xf-goe427-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 427 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 -0.3272 0.11441 0.11214 -0.0248 1.0000 0.0053
-9.250 -0.3254 0.11187 0.10962 -0.0244 1.0000 0.0053
-9.000 -0.3249 0.10915 0.10690 -0.0238 1.0000 0.0052
-8.750 -0.3189 0.10486 0.10262 -0.0247 0.9993 0.0048
-8.500 -0.3065 0.10087 0.09864 -0.0278 0.9976 0.0046
-8.250 -0.2918 0.09724 0.09502 -0.0314 0.9953 0.0043
-8.000 -0.2783 0.09372 0.09149 -0.0346 0.9925 0.0041
-7.750 -0.2639 0.08992 0.08771 -0.0384 0.9892 0.0040
-7.500 -0.2475 0.08627 0.08407 -0.0427 0.9861 0.0039
-7.250 -0.2332 0.08258 0.08039 -0.0465 0.9807 0.0040
-7.000 -0.2105 0.07831 0.07611 -0.0527 0.9776 0.0041
-6.750 -0.1907 0.07420 0.07199 -0.0579 0.9721 0.0043
-6.500 -0.1588 0.06920 0.06698 -0.0668 0.9682 0.0051
-6.250 -0.1335 0.06526 0.06303 -0.0728 0.9661 0.0063
-6.000 -0.1153 0.06455 0.06232 -0.0737 0.9605 0.0101
-5.750 -0.0841 0.06025 0.05799 -0.0806 0.9563 0.0095
-5.500 -0.0519 0.05569 0.05337 -0.0877 0.9514 0.0084
-5.250 -0.0216 0.05149 0.04912 -0.0935 0.9444 0.0079
-5.000 0.0145 0.04707 0.04461 -0.1003 0.9394 0.0078
-4.750 0.0454 0.04333 0.04080 -0.1049 0.9308 0.0082
-4.500 0.0790 0.03968 0.03703 -0.1095 0.9234 0.0091
-4.250 0.1129 0.03625 0.03343 -0.1135 0.9154 0.0106
-4.000 0.1458 0.03294 0.02996 -0.1166 0.9060 0.0117
-3.750 0.1790 0.02927 0.02609 -0.1196 0.8962 0.0115
-3.500 0.2122 0.02548 0.02204 -0.1219 0.8856 0.0114
-3.250 0.2441 0.02150 0.01774 -0.1234 0.8748 0.0117
-3.000 0.2744 0.01794 0.01381 -0.1239 0.8644 0.0128
-2.750 0.3021 0.01521 0.01063 -0.1243 0.8534 0.0154
-2.500 0.3287 0.01476 0.01005 -0.1243 0.8416 0.0176
-2.250 0.3558 0.01363 0.00863 -0.1241 0.8297 0.0193
-2.000 0.3828 0.01279 0.00745 -0.1238 0.8169 0.0235
-1.750 0.4092 0.01207 0.00647 -0.1233 0.8008 0.0231
-1.500 0.4352 0.01128 0.00544 -0.1228 0.7835 0.0213
-1.250 0.4610 0.01032 0.00420 -0.1222 0.7675 0.0204
-1.000 0.4871 0.00963 0.00332 -0.1216 0.7543 0.0196
-0.750 0.5130 0.00912 0.00266 -0.1211 0.7416 0.0189
-0.500 0.5388 0.00874 0.00217 -0.1205 0.7287 0.0183
-0.250 0.5646 0.00849 0.00182 -0.1199 0.7149 0.0178
0.000 0.5903 0.00833 0.00155 -0.1194 0.7004 0.0174
0.250 0.6158 0.00828 0.00138 -0.1188 0.6833 0.0172
0.500 0.6390 0.00838 0.00127 -0.1177 0.6394 0.0171
0.750 0.6597 0.00870 0.00122 -0.1162 0.5731 0.0173
1.000 0.6815 0.00905 0.00125 -0.1150 0.5239 0.0178
1.250 0.7054 0.00926 0.00129 -0.1142 0.4937 0.0198
1.500 0.7304 0.00933 0.00136 -0.1137 0.4747 0.0531
1.750 0.7550 0.00941 0.00150 -0.1131 0.4492 0.1106
2.000 0.7790 0.00958 0.00163 -0.1125 0.4134 0.1500
2.250 0.8062 0.00851 0.00200 -0.1132 0.3573 1.0000
2.500 0.8274 0.00909 0.00227 -0.1122 0.2964 1.0000
2.750 0.8431 0.01032 0.00279 -0.1103 0.1528 1.0000
3.000 0.8630 0.01114 0.00322 -0.1090 0.0710 1.0000
3.250 0.8860 0.01160 0.00352 -0.1082 0.0356 1.0000
3.500 0.9106 0.01185 0.00375 -0.1077 0.0332 1.0000
3.750 0.9353 0.01210 0.00401 -0.1071 0.0317 1.0000
4.000 0.9598 0.01236 0.00434 -0.1066 0.0308 1.0000
4.250 0.9842 0.01263 0.00465 -0.1060 0.0303 1.0000
4.500 1.0083 0.01292 0.00498 -0.1054 0.0299 1.0000
4.750 1.0321 0.01324 0.00534 -0.1047 0.0292 1.0000
5.000 1.0563 0.01345 0.00546 -0.1043 0.0209 1.0000
5.250 1.0806 0.01366 0.00557 -0.1039 0.0082 1.0000
5.500 1.1032 0.01412 0.00599 -0.1030 0.0042 1.0000
5.750 1.1260 0.01452 0.00648 -0.1021 0.0037 1.0000
6.000 1.1484 0.01497 0.00701 -0.1012 0.0035 1.0000
6.250 1.1701 0.01548 0.00772 -0.1001 0.0034 1.0000
6.500 1.1910 0.01607 0.00843 -0.0989 0.0034 1.0000
6.750 1.2109 0.01674 0.00922 -0.0975 0.0033 1.0000
7.000 1.2294 0.01752 0.01014 -0.0959 0.0033 1.0000
7.250 1.2464 0.01842 0.01118 -0.0941 0.0033 1.0000
7.500 1.2629 0.01934 0.01222 -0.0923 0.0031 1.0000
7.750 1.2790 0.02025 0.01324 -0.0904 0.0029 1.0000
8.000 1.2948 0.02117 0.01426 -0.0886 0.0025 1.0000
8.250 1.3089 0.02225 0.01547 -0.0864 0.0024 1.0000
8.500 1.3211 0.02354 0.01690 -0.0840 0.0023 1.0000
8.750 1.3321 0.02484 0.01834 -0.0814 0.0021 1.0000
9.000 1.3422 0.02628 0.01995 -0.0787 0.0020 1.0000
9.250 1.3519 0.02777 0.02160 -0.0761 0.0019 1.0000
9.500 1.3608 0.02942 0.02343 -0.0734 0.0018 1.0000
9.750 1.3684 0.03120 0.02540 -0.0708 0.0017 1.0000
10.000 1.3742 0.03310 0.02762 -0.0680 0.0016 1.0000
10.250 1.3780 0.03528 0.03004 -0.0652 0.0015 1.0000
10.500 1.3791 0.03757 0.03256 -0.0623 0.0015 1.0000
10.750 1.3765 0.04014 0.03536 -0.0593 0.0014 1.0000
11.000 1.3721 0.04303 0.03850 -0.0565 0.0014 1.0000
11.250 1.3652 0.04628 0.04202 -0.0540 0.0014 1.0000
11.500 1.3557 0.04980 0.04577 -0.0519 0.0014 1.0000
11.750 1.3430 0.05375 0.04995 -0.0504 0.0013 1.0000
12.000 1.3288 0.05820 0.05463 -0.0496 0.0013 1.0000
12.250 1.3142 0.06311 0.05977 -0.0496 0.0013 1.0000
12.500 1.2980 0.06863 0.06551 -0.0505 0.0014 1.0000
12.750 1.2804 0.07481 0.07188 -0.0523 0.0013 1.0000
13.000 1.2624 0.08172 0.07900 -0.0551 0.0014 1.0000
13.250 1.2432 0.08949 0.08695 -0.0590 0.0014 1.0000
13.500 1.2240 0.09798 0.09560 -0.0637 0.0014 1.0000
13.750 1.2046 0.10726 0.10504 -0.0691 0.0014 1.0000
14.000 1.1819 0.11854 0.11648 -0.0758 0.0014 1.0000
14.250 1.1561 0.13255 0.13063 -0.0840 0.0015 1.0000
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Polar data table (+)
Polar graphs
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