GOE 369 AIRFOIL (goe369-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 369 AIRFOIL (goe369-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.56 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe369-il-1000000-n5.txt Download as CSV file: xf-goe369-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 369 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1933 0.08654 0.08427 -0.0461 0.8000 0.0042
-7.750 -0.1887 0.08436 0.08198 -0.0462 0.7730 0.0042
-7.500 -0.1843 0.08224 0.07980 -0.0464 0.7524 0.0042
-7.250 -0.1820 0.07983 0.07735 -0.0470 0.7366 0.0042
-7.000 -0.1729 0.07717 0.07465 -0.0488 0.7235 0.0042
-6.750 -0.1618 0.07440 0.07184 -0.0511 0.7119 0.0042
-6.500 -0.1491 0.07149 0.06888 -0.0537 0.7007 0.0042
-6.250 -0.1343 0.06848 0.06583 -0.0564 0.6916 0.0042
-6.000 -0.1177 0.06543 0.06274 -0.0594 0.6826 0.0043
-5.750 -0.1042 0.06216 0.05944 -0.0613 0.6749 0.0044
-5.500 -0.0847 0.05916 0.05640 -0.0642 0.6678 0.0044
-5.000 -0.0430 0.05394 0.05108 -0.0693 0.6539 0.0052
-4.750 -0.0178 0.05099 0.04806 -0.0723 0.6476 0.0060
-4.500 0.0115 0.04792 0.04489 -0.0756 0.6423 0.0062
-4.250 0.0400 0.04479 0.04168 -0.0786 0.6368 0.0063
-3.750 0.0961 0.03888 0.03557 -0.0830 0.6246 0.0063
-3.500 0.1242 0.03609 0.03265 -0.0846 0.6177 0.0063
-3.250 0.1529 0.03324 0.02967 -0.0861 0.6117 0.0063
-3.000 0.1772 0.03068 0.02700 -0.0872 0.6051 0.0057
-2.750 0.2069 0.02780 0.02395 -0.0881 0.5988 0.0051
-2.500 0.2368 0.02509 0.02105 -0.0887 0.5920 0.0050
-2.250 0.2659 0.02268 0.01844 -0.0888 0.5858 0.0051
-2.000 0.2951 0.02040 0.01595 -0.0887 0.5807 0.0054
-1.750 0.3244 0.01802 0.01332 -0.0883 0.5759 0.0060
-1.500 0.3525 0.01584 0.01086 -0.0877 0.5705 0.0059
-1.250 0.3810 0.01288 0.00750 -0.0868 0.5647 0.0059
-1.000 0.4071 0.00899 0.00293 -0.0854 0.5588 0.0067
-0.750 0.4341 0.00869 0.00256 -0.0850 0.5527 0.0072
-0.500 0.4612 0.00851 0.00232 -0.0848 0.5454 0.0081
-0.250 0.4881 0.00831 0.00204 -0.0844 0.5377 0.0091
0.000 0.5148 0.00799 0.00164 -0.0840 0.5297 0.0103
0.250 0.5420 0.00794 0.00157 -0.0838 0.5220 0.0118
0.500 0.5692 0.00793 0.00151 -0.0835 0.5136 0.0135
0.750 0.5962 0.00783 0.00138 -0.0832 0.5039 0.0162
1.000 0.6230 0.00786 0.00134 -0.0829 0.4867 0.0191
1.250 0.6496 0.00797 0.00136 -0.0826 0.4665 0.0211
1.500 0.6760 0.00795 0.00126 -0.0823 0.4474 0.0234
1.750 0.7024 0.00803 0.00126 -0.0819 0.4275 0.0260
2.000 0.7285 0.00815 0.00128 -0.0816 0.4041 0.0275
2.250 0.7539 0.00838 0.00134 -0.0811 0.3694 0.0289
2.500 0.7790 0.00865 0.00144 -0.0807 0.3363 0.0300
2.750 0.8048 0.00884 0.00152 -0.0803 0.3130 0.0333
3.250 0.8569 0.00910 0.00175 -0.0796 0.2814 0.0898
3.500 0.8728 0.00791 0.00207 -0.0777 0.2676 0.8613
4.000 0.9399 0.00835 0.00244 -0.0806 0.2112 1.0000
4.250 0.9642 0.00872 0.00265 -0.0801 0.1852 1.0000
4.500 0.9888 0.00904 0.00287 -0.0796 0.1667 1.0000
4.750 1.0140 0.00929 0.00307 -0.0791 0.1558 1.0000
5.000 1.0391 0.00955 0.00327 -0.0787 0.1464 1.0000
5.250 1.0645 0.00976 0.00346 -0.0783 0.1383 1.0000
5.500 1.0896 0.01001 0.00367 -0.0779 0.1303 1.0000
5.750 1.1144 0.01027 0.00389 -0.0774 0.1205 1.0000
6.000 1.1393 0.01053 0.00412 -0.0770 0.1112 1.0000
6.250 1.1637 0.01082 0.00437 -0.0765 0.1024 1.0000
6.500 1.1883 0.01110 0.00464 -0.0761 0.0959 1.0000
6.750 1.2128 0.01138 0.00490 -0.0756 0.0908 1.0000
7.000 1.2374 0.01163 0.00517 -0.0751 0.0876 1.0000
7.250 1.2617 0.01191 0.00546 -0.0747 0.0844 1.0000
7.500 1.2856 0.01222 0.00578 -0.0741 0.0804 1.0000
7.750 1.3097 0.01249 0.00608 -0.0736 0.0766 1.0000
8.000 1.3329 0.01285 0.00643 -0.0730 0.0698 1.0000
8.250 1.3559 0.01322 0.00679 -0.0724 0.0638 1.0000
8.500 1.3776 0.01370 0.00722 -0.0716 0.0535 1.0000
8.750 1.3990 0.01420 0.00768 -0.0708 0.0451 1.0000
9.000 1.4191 0.01479 0.00823 -0.0698 0.0361 1.0000
9.250 1.4305 0.01620 0.00945 -0.0675 0.0087 1.0000
9.500 1.4483 0.01696 0.01024 -0.0662 0.0050 1.0000
9.750 1.4675 0.01755 0.01089 -0.0650 0.0038 1.0000
10.000 1.4859 0.01818 0.01160 -0.0638 0.0031 1.0000
10.250 1.5040 0.01880 0.01228 -0.0625 0.0027 1.0000
10.500 1.5201 0.01953 0.01309 -0.0610 0.0023 1.0000
10.750 1.5362 0.02021 0.01384 -0.0595 0.0020 1.0000
11.000 1.5512 0.02093 0.01463 -0.0578 0.0018 1.0000
11.250 1.5625 0.02169 0.01547 -0.0555 0.0016 1.0000
11.500 1.5712 0.02254 0.01640 -0.0529 0.0015 1.0000
11.750 1.5782 0.02351 0.01746 -0.0502 0.0013 1.0000
12.000 1.5830 0.02469 0.01874 -0.0475 0.0013 1.0000
12.250 1.5893 0.02582 0.02000 -0.0452 0.0012 1.0000
12.500 1.5939 0.02717 0.02145 -0.0431 0.0012 1.0000
12.750 1.5993 0.02853 0.02291 -0.0414 0.0011 1.0000
13.000 1.6015 0.03031 0.02481 -0.0397 0.0010 1.0000
13.250 1.6048 0.03212 0.02673 -0.0385 0.0010 1.0000
13.500 1.6059 0.03428 0.02900 -0.0375 0.0009 1.0000
13.750 1.6034 0.03696 0.03183 -0.0367 0.0009 1.0000
14.000 1.6050 0.03931 0.03427 -0.0362 0.0009 1.0000
14.250 1.6032 0.04217 0.03725 -0.0360 0.0008 1.0000
14.500 1.6000 0.04528 0.04047 -0.0359 0.0008 1.0000
14.750 1.5934 0.04896 0.04429 -0.0362 0.0008 1.0000
15.000 1.5862 0.05282 0.04828 -0.0366 0.0008 1.0000
15.250 1.5766 0.05719 0.05279 -0.0375 0.0008 1.0000
15.500 1.5663 0.06179 0.05752 -0.0386 0.0007 1.0000
15.750 1.5554 0.06675 0.06262 -0.0400 0.0007 1.0000
16.000 1.5252 0.07517 0.07122 -0.0432 0.0006 1.0000
16.250 1.5207 0.07965 0.07581 -0.0449 0.0007 1.0000
16.500 1.4986 0.08756 0.08388 -0.0484 0.0006 1.0000
16.750 1.4858 0.09403 0.09049 -0.0513 0.0007 1.0000
17.000 1.4581 0.10375 0.10038 -0.0561 0.0007 1.0000
17.250 1.4473 0.11029 0.10704 -0.0592 0.0007 1.0000
17.500 1.4264 0.11910 0.11598 -0.0637 0.0007 1.0000
17.750 1.4048 0.12830 0.12533 -0.0686 0.0007 1.0000
18.000 1.3827 0.13792 0.13508 -0.0738 0.0007 1.0000
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Polar data table (+)
Polar graphs
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