GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.05 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe100-il-1000000-n5.txt Download as CSV file: xf-goe100-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 100 (SOPWITH) 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2915 0.10113 0.09963 -0.0244 1.0000 0.0033
-9.500 -0.2903 0.09776 0.09628 -0.0247 1.0000 0.0034
-7.000 -0.3551 0.07629 0.07483 -0.0341 0.9926 0.0023
-6.750 -0.3333 0.07111 0.06963 -0.0415 0.9887 0.0022
-6.500 -0.3103 0.06571 0.06420 -0.0487 0.9836 0.0022
-6.000 -0.2580 0.05402 0.05238 -0.0628 0.9700 0.0020
-5.750 -0.2292 0.04739 0.04563 -0.0692 0.9613 0.0021
-5.500 -0.1984 0.03941 0.03744 -0.0753 0.9513 0.0022
-5.250 -0.1733 0.01785 0.01469 -0.0805 0.9365 0.0023
-5.000 -0.1476 0.01458 0.01082 -0.0804 0.9262 0.0024
-4.750 -0.1211 0.01316 0.00905 -0.0801 0.9154 0.0025
-4.500 -0.0950 0.01154 0.00705 -0.0798 0.9054 0.0028
-4.250 -0.0681 0.01093 0.00631 -0.0797 0.8968 0.0030
-4.000 -0.0412 0.01010 0.00526 -0.0794 0.8876 0.0032
-3.750 -0.0141 0.00941 0.00437 -0.0791 0.8767 0.0033
-3.500 0.0127 0.00889 0.00367 -0.0787 0.8628 0.0035
-3.250 0.0397 0.00847 0.00310 -0.0783 0.8476 0.0040
-3.000 0.0670 0.00818 0.00268 -0.0781 0.8349 0.0044
-2.750 0.0946 0.00781 0.00219 -0.0779 0.8248 0.0052
-2.500 0.1221 0.00763 0.00194 -0.0778 0.8145 0.0066
-2.250 0.1496 0.00749 0.00170 -0.0777 0.8006 0.0080
-2.000 0.1768 0.00732 0.00142 -0.0774 0.7794 0.0130
-1.750 0.2036 0.00720 0.00130 -0.0772 0.7535 0.0382
-1.500 0.2306 0.00723 0.00123 -0.0770 0.7270 0.0449
-1.250 0.2572 0.00727 0.00114 -0.0767 0.6909 0.0504
-1.000 0.2827 0.00749 0.00110 -0.0762 0.6298 0.0540
-0.750 0.3081 0.00775 0.00108 -0.0758 0.5651 0.0551
-0.500 0.3345 0.00792 0.00107 -0.0756 0.5219 0.0581
-0.250 0.3609 0.00808 0.00106 -0.0754 0.4797 0.0639
0.250 0.4136 0.00831 0.00114 -0.0751 0.3945 0.1316
0.500 0.4402 0.00848 0.00119 -0.0750 0.3593 0.1456
0.750 0.4672 0.00860 0.00124 -0.0750 0.3342 0.1574
1.000 0.4942 0.00872 0.00129 -0.0749 0.3135 0.1688
1.250 0.5213 0.00880 0.00135 -0.0749 0.2954 0.1860
1.500 0.5484 0.00887 0.00142 -0.0748 0.2788 0.2136
1.750 0.5752 0.00875 0.00155 -0.0749 0.2614 0.3525
2.000 0.5976 0.00769 0.00171 -0.0744 0.2449 0.8450
2.250 0.6235 0.00766 0.00183 -0.0738 0.2105 1.0000
2.500 0.6496 0.00793 0.00195 -0.0736 0.1859 1.0000
2.750 0.6760 0.00814 0.00207 -0.0735 0.1692 1.0000
3.000 0.7018 0.00845 0.00224 -0.0732 0.1431 1.0000
3.250 0.7268 0.00886 0.00245 -0.0729 0.1065 1.0000
3.500 0.7486 0.00978 0.00299 -0.0720 0.0152 1.0000
3.750 0.7753 0.00997 0.00320 -0.0718 0.0102 1.0000
4.000 0.8018 0.01019 0.00347 -0.0716 0.0081 1.0000
4.250 0.8280 0.01046 0.00377 -0.0713 0.0060 1.0000
4.500 0.8541 0.01072 0.00407 -0.0711 0.0050 1.0000
4.750 0.8795 0.01110 0.00449 -0.0707 0.0042 1.0000
5.000 0.9046 0.01155 0.00502 -0.0702 0.0037 1.0000
5.250 0.9302 0.01186 0.00535 -0.0699 0.0030 1.0000
5.500 0.9553 0.01226 0.00578 -0.0695 0.0027 1.0000
5.750 0.9787 0.01296 0.00657 -0.0687 0.0023 1.0000
6.000 1.0020 0.01365 0.00736 -0.0679 0.0021 1.0000
6.250 1.0227 0.01470 0.00856 -0.0666 0.0019 1.0000
6.500 1.0411 0.01602 0.00998 -0.0648 0.0018 1.0000
6.750 1.0590 0.01743 0.01145 -0.0629 0.0018 1.0000
7.000 1.0777 0.01892 0.01298 -0.0612 0.0018 1.0000
7.250 1.0979 0.02043 0.01454 -0.0598 0.0018 1.0000
7.500 1.1196 0.02170 0.01587 -0.0587 0.0016 1.0000
7.750 1.1409 0.02268 0.01692 -0.0578 0.0014 1.0000
8.000 1.1611 0.02367 0.01800 -0.0569 0.0013 1.0000
8.250 1.1798 0.02536 0.01980 -0.0557 0.0012 1.0000
8.500 1.1991 0.02773 0.02232 -0.0542 0.0012 1.0000
8.750 1.2186 0.02978 0.02458 -0.0526 0.0011 1.0000
9.000 1.2350 0.03253 0.02759 -0.0504 0.0009 1.0000
9.250 1.2474 0.03527 0.03059 -0.0479 0.0008 1.0000
9.500 1.2572 0.03807 0.03363 -0.0453 0.0008 1.0000
9.750 1.2631 0.04096 0.03677 -0.0424 0.0008 1.0000
10.000 1.2648 0.04388 0.03994 -0.0392 0.0008 1.0000
10.250 1.2622 0.04682 0.04312 -0.0357 0.0008 1.0000
10.500 1.2543 0.04966 0.04619 -0.0317 0.0008 1.0000
10.750 1.2404 0.05217 0.04888 -0.0271 0.0008 1.0000
11.000 1.2248 0.05502 0.05190 -0.0235 0.0008 1.0000
11.250 1.2081 0.05831 0.05536 -0.0209 0.0008 1.0000
11.500 1.1909 0.06208 0.05929 -0.0196 0.0008 1.0000
11.750 1.1735 0.06640 0.06377 -0.0196 0.0009 1.0000
12.000 1.1560 0.07135 0.06887 -0.0208 0.0009 1.0000
12.250 1.1383 0.07703 0.07469 -0.0234 0.0009 1.0000
12.500 1.1205 0.08365 0.08145 -0.0274 0.0009 1.0000
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Polar data table (+)
Polar graphs
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