GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 257 AIRFOIL (goe257-il) Reynolds number: 50,000 Max Cl/Cd: 38.5 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe257-il-50000.txt Download as CSV file: xf-goe257-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 257 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4232 0.11109 0.10460 -0.0159 1.0000 0.1550
-8.000 -0.4000 0.10478 0.09827 -0.0135 1.0000 0.1641
-7.750 -0.4111 0.10368 0.09729 -0.0171 1.0000 0.1694
-7.500 -0.3963 0.09864 0.09228 -0.0150 1.0000 0.1773
-7.250 -0.4038 0.09742 0.09116 -0.0217 1.0000 0.1847
-7.000 -0.3884 0.09238 0.08616 -0.0177 1.0000 0.1953
-6.500 -0.3787 0.08584 0.07973 -0.0203 1.0000 0.2185
-6.250 -0.3719 0.08262 0.07658 -0.0201 1.0000 0.2345
-6.000 -0.3654 0.07956 0.07358 -0.0198 1.0000 0.2526
-5.750 -0.3633 0.07731 0.07138 -0.0234 1.0000 0.2744
-5.500 -0.3551 0.07361 0.06778 -0.0187 1.0000 0.2935
-5.250 -0.3518 0.07104 0.06529 -0.0180 1.0000 0.3207
-5.000 -0.3485 0.06839 0.06275 -0.0148 1.0000 0.3508
-4.750 -0.0004 0.04596 0.03929 -0.0217 1.0000 1.0000
-4.500 0.0122 0.04381 0.03720 -0.0231 1.0000 1.0000
-4.250 0.0247 0.04175 0.03518 -0.0245 1.0000 1.0000
-4.000 0.0372 0.03978 0.03327 -0.0259 1.0000 1.0000
-3.750 0.0085 0.04013 0.03379 -0.0177 1.0000 0.9821
-3.500 -0.0470 0.04142 0.03538 -0.0045 1.0000 0.9429
-3.250 -0.0974 0.04203 0.03630 0.0060 1.0000 0.9025
-3.000 -0.1479 0.04263 0.03721 0.0162 1.0000 0.8765
-2.750 -0.2004 0.04335 0.03819 0.0267 1.0000 0.8645
-2.500 -0.2627 0.04418 0.03926 0.0390 1.0000 0.8557
-2.250 -0.1241 0.03981 0.03242 -0.0472 1.0000 0.2919
-1.750 -0.0470 0.03659 0.02772 -0.0531 1.0000 0.1941
-1.500 -0.0137 0.03542 0.02602 -0.0548 0.9986 0.1752
-1.250 0.0436 0.03393 0.02390 -0.0602 0.9886 0.1606
-1.000 0.0978 0.03296 0.02237 -0.0651 0.9780 0.1533
-0.750 0.1504 0.03215 0.02120 -0.0700 0.9674 0.1550
-0.500 0.2005 0.03136 0.02017 -0.0741 0.9564 0.1563
-0.250 0.2464 0.03077 0.01944 -0.0775 0.9443 0.1585
0.000 0.2913 0.03036 0.01895 -0.0809 0.9321 0.1644
0.250 0.3369 0.03000 0.01856 -0.0845 0.9200 0.1761
0.500 0.3871 0.02940 0.01821 -0.0891 0.9089 0.2220
0.750 0.4274 0.02748 0.01795 -0.0907 0.8975 1.0000
1.000 0.4657 0.02799 0.01799 -0.0927 0.8840 1.0000
1.250 0.5012 0.02853 0.01827 -0.0945 0.8706 1.0000
1.500 0.5343 0.02914 0.01869 -0.0960 0.8576 1.0000
1.750 0.5662 0.02977 0.01919 -0.0972 0.8450 1.0000
2.000 0.5987 0.03037 0.01971 -0.0983 0.8331 1.0000
2.250 0.6367 0.03073 0.01999 -0.1001 0.8228 1.0000
2.500 0.6631 0.03151 0.02074 -0.1003 0.8102 1.0000
2.750 0.6909 0.03212 0.02135 -0.1003 0.7966 1.0000
3.000 0.7237 0.03221 0.02142 -0.1002 0.7815 1.0000
3.250 0.7574 0.03202 0.02123 -0.0996 0.7658 1.0000
3.500 0.7850 0.03221 0.02142 -0.0985 0.7495 1.0000
3.750 0.8126 0.03251 0.02178 -0.0975 0.7352 1.0000
4.000 0.8392 0.03295 0.02227 -0.0966 0.7215 1.0000
4.250 0.8634 0.03359 0.02298 -0.0956 0.7071 1.0000
4.500 0.8880 0.03416 0.02368 -0.0945 0.6924 1.0000
4.750 0.9129 0.03468 0.02428 -0.0933 0.6774 1.0000
5.000 0.9347 0.03548 0.02520 -0.0920 0.6609 1.0000
5.250 0.9547 0.03641 0.02628 -0.0906 0.6429 1.0000
5.500 0.9774 0.03705 0.02709 -0.0891 0.6251 1.0000
5.750 1.0020 0.03746 0.02764 -0.0875 0.6076 1.0000
6.000 1.0287 0.03763 0.02794 -0.0859 0.5905 1.0000
6.250 1.0518 0.03821 0.02867 -0.0844 0.5720 1.0000
6.500 1.0703 0.03938 0.03008 -0.0830 0.5524 1.0000
6.750 1.0927 0.04028 0.03116 -0.0817 0.5359 1.0000
7.000 1.1159 0.04102 0.03208 -0.0804 0.5202 1.0000
7.250 1.1427 0.04100 0.03223 -0.0789 0.5043 1.0000
7.500 1.1747 0.03989 0.03128 -0.0769 0.4875 1.0000
7.750 1.1923 0.04053 0.03219 -0.0750 0.4676 1.0000
8.000 1.2272 0.03652 0.02811 -0.0711 0.4340 1.0000
8.250 1.2477 0.03402 0.02558 -0.0671 0.3935 1.0000
8.500 1.2554 0.03261 0.02423 -0.0625 0.3422 1.0000
8.750 1.2471 0.03333 0.02468 -0.0569 0.2565 1.0000
9.000 1.2308 0.03669 0.02733 -0.0518 0.1783 1.0000
9.250 1.2212 0.03984 0.03008 -0.0479 0.1390 1.0000
9.500 1.2139 0.04259 0.03259 -0.0444 0.1221 1.0000
9.750 1.2108 0.04534 0.03521 -0.0416 0.1103 1.0000
10.000 1.2126 0.04799 0.03782 -0.0392 0.1012 1.0000
10.250 1.2249 0.05027 0.03999 -0.0369 0.0942 1.0000
10.500 1.2627 0.05218 0.04201 -0.0355 0.0873 1.0000
10.750 1.3135 0.05576 0.04575 -0.0367 0.0812 1.0000
11.000 1.3294 0.05916 0.04954 -0.0355 0.0783 1.0000
11.250 1.3414 0.06295 0.05372 -0.0341 0.0769 1.0000
11.500 1.3421 0.06689 0.05807 -0.0319 0.0769 1.0000
11.750 1.3328 0.07084 0.06242 -0.0293 0.0772 1.0000
12.000 1.3181 0.07509 0.06702 -0.0272 0.0777 1.0000
12.250 1.2990 0.07976 0.07203 -0.0260 0.0783 1.0000
12.500 1.2767 0.08499 0.07755 -0.0259 0.0789 1.0000
12.750 1.2520 0.09089 0.08372 -0.0270 0.0797 1.0000
13.000 1.2255 0.09756 0.09061 -0.0293 0.0804 1.0000
13.250 1.1984 0.10501 0.09824 -0.0327 0.0813 1.0000
13.500 1.1728 0.11310 0.10645 -0.0368 0.0823 1.0000
13.750 1.1523 0.12130 0.11473 -0.0409 0.0832 1.0000
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Polar data table (+)
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