GOE 410 AIRFOIL (goe410-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 410 AIRFOIL (goe410-il) Reynolds number: 50,000 Max Cl/Cd: 20.94 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe410-il-50000.txt Download as CSV file: xf-goe410-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 410 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5363 0.10226 0.09367 0.0064 1.0000 0.3058
-9.500 -0.5677 0.09212 0.08356 0.0008 1.0000 0.2887
-9.250 -0.5609 0.08808 0.07952 0.0001 1.0000 0.2899
-9.000 -0.5541 0.08435 0.07579 -0.0006 1.0000 0.2918
-8.750 -0.6377 0.06875 0.06029 -0.0094 1.0000 0.2858
-8.500 -0.7727 0.05145 0.04289 -0.0138 1.0000 0.2819
-8.250 -0.8048 0.04553 0.03664 -0.0125 1.0000 0.2854
-8.000 -0.8076 0.04204 0.03292 -0.0112 1.0000 0.2905
-7.750 -0.7821 0.04123 0.03221 -0.0104 1.0000 0.2981
-7.500 -0.7851 0.03802 0.02866 -0.0088 1.0000 0.3063
-7.250 -0.7557 0.03770 0.02857 -0.0079 1.0000 0.3156
-7.000 -0.7458 0.03568 0.02642 -0.0065 1.0000 0.3257
-6.750 -0.7270 0.03472 0.02551 -0.0052 1.0000 0.3377
-6.500 -0.7049 0.03420 0.02514 -0.0038 1.0000 0.3504
-6.250 -0.6877 0.03340 0.02441 -0.0020 1.0000 0.3651
-6.000 -0.6713 0.03280 0.02390 -0.0001 1.0000 0.3817
-5.750 -0.6548 0.03252 0.02376 0.0022 1.0000 0.4001
-5.500 -0.6394 0.03245 0.02384 0.0049 1.0000 0.4202
-5.250 -0.6277 0.03249 0.02403 0.0081 1.0000 0.4421
-5.000 -0.6225 0.03240 0.02402 0.0118 1.0000 0.4649
-4.750 -0.6230 0.03211 0.02375 0.0157 1.0000 0.4880
-4.500 -0.6175 0.03241 0.02416 0.0194 1.0000 0.5081
-4.250 -0.6134 0.03258 0.02438 0.0229 1.0000 0.5274
-4.000 -0.6055 0.03309 0.02499 0.0263 1.0000 0.5443
-3.750 -0.5977 0.03352 0.02549 0.0295 1.0000 0.5604
-3.500 -0.5712 0.03402 0.02600 0.0294 0.9930 0.5811
-3.250 -0.5202 0.03438 0.02625 0.0248 0.9744 0.6063
-3.000 -0.4689 0.03502 0.02688 0.0213 0.9574 0.6263
-2.750 -0.4187 0.03556 0.02737 0.0181 0.9410 0.6449
-2.500 -0.3692 0.03623 0.02804 0.0156 0.9257 0.6641
-2.250 -0.3193 0.03680 0.02859 0.0131 0.9113 0.6854
-2.000 -0.2447 0.03756 0.02935 0.0078 0.8993 0.7063
-1.750 -0.1957 0.03779 0.02956 0.0053 0.8847 0.7207
-1.500 -0.1539 0.03755 0.02928 0.0028 0.8706 0.7321
-1.250 -0.1344 0.03681 0.02847 0.0022 0.8577 0.7441
-1.000 -0.0818 0.03677 0.02842 -0.0012 0.8446 0.7533
-0.750 -0.0886 0.03629 0.02790 0.0020 0.8310 0.7646
-0.500 -0.0297 0.03627 0.02787 -0.0021 0.8203 0.7741
-0.250 -0.0291 0.03606 0.02765 0.0006 0.8075 0.7857
0.000 0.0000 0.03619 0.02778 0.0000 0.7959 0.7959
0.250 0.0296 0.03606 0.02764 -0.0006 0.7856 0.8075
0.500 0.0302 0.03627 0.02787 0.0020 0.7740 0.8202
0.750 0.0887 0.03629 0.02790 -0.0020 0.7646 0.8309
1.000 0.0820 0.03677 0.02842 0.0012 0.7533 0.8447
1.250 0.1341 0.03681 0.02847 -0.0021 0.7441 0.8576
1.500 0.1541 0.03755 0.02928 -0.0028 0.7320 0.8706
1.750 0.1957 0.03778 0.02955 -0.0053 0.7207 0.8847
2.000 0.2454 0.03753 0.02932 -0.0078 0.7062 0.8993
2.250 0.3190 0.03680 0.02860 -0.0131 0.6855 0.9113
2.500 0.3691 0.03622 0.02803 -0.0156 0.6640 0.9257
2.750 0.4189 0.03554 0.02736 -0.0181 0.6450 0.9410
3.000 0.4690 0.03502 0.02687 -0.0213 0.6263 0.9575
3.250 0.5202 0.03437 0.02624 -0.0248 0.6063 0.9745
3.500 0.5712 0.03400 0.02598 -0.0294 0.5809 0.9930
3.750 0.5977 0.03352 0.02549 -0.0295 0.5605 1.0000
4.000 0.6055 0.03308 0.02498 -0.0263 0.5444 1.0000
4.250 0.6133 0.03258 0.02438 -0.0229 0.5274 1.0000
4.500 0.6174 0.03241 0.02416 -0.0194 0.5081 1.0000
4.750 0.6228 0.03212 0.02377 -0.0157 0.4881 1.0000
5.000 0.6225 0.03239 0.02402 -0.0118 0.4649 1.0000
5.250 0.6277 0.03249 0.02403 -0.0081 0.4422 1.0000
5.500 0.6393 0.03246 0.02385 -0.0049 0.4203 1.0000
5.750 0.6548 0.03251 0.02375 -0.0022 0.4001 1.0000
6.000 0.6713 0.03281 0.02391 0.0001 0.3817 1.0000
6.250 0.6877 0.03341 0.02441 0.0020 0.3651 1.0000
6.500 0.7050 0.03420 0.02514 0.0038 0.3505 1.0000
6.750 0.7271 0.03472 0.02550 0.0052 0.3378 1.0000
7.000 0.7456 0.03569 0.02644 0.0065 0.3258 1.0000
7.250 0.7557 0.03770 0.02857 0.0079 0.3156 1.0000
7.500 0.7850 0.03803 0.02868 0.0088 0.3063 1.0000
7.750 0.7822 0.04122 0.03221 0.0104 0.2981 1.0000
8.000 0.8074 0.04207 0.03295 0.0112 0.2905 1.0000
8.250 0.8050 0.04551 0.03662 0.0125 0.2854 1.0000
8.500 0.7730 0.05143 0.04287 0.0138 0.2818 1.0000
8.750 0.6391 0.06861 0.06015 0.0094 0.2858 1.0000
9.000 0.5496 0.08495 0.07637 0.0001 0.2924 1.0000
9.250 0.5731 0.08662 0.07806 0.0010 0.2878 1.0000
9.500 0.5669 0.09225 0.08368 -0.0011 0.2888 1.0000
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Polar data table (+)
Polar graphs
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