GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il) Reynolds number: 500,000 Max Cl/Cd: 73.11 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe100-il-500000-n5.txt Download as CSV file: xf-goe100-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3777 0.09120 0.08908 -0.0214 1.0000 0.0064
-7.500 -0.3811 0.08862 0.08655 -0.0209 1.0000 0.0066
-7.250 -0.3889 0.08644 0.08443 -0.0196 1.0000 0.0066
-7.000 -0.3854 0.08303 0.08105 -0.0218 0.9989 0.0067
-6.750 -0.3579 0.07815 0.07615 -0.0305 0.9954 0.0074
-6.500 -0.3384 0.07258 0.07056 -0.0373 0.9910 0.0071
-6.250 -0.3146 0.06478 0.06270 -0.0462 0.9867 0.0042
-6.000 -0.2887 0.05942 0.05728 -0.0528 0.9813 0.0041
-5.750 -0.2572 0.05334 0.05110 -0.0602 0.9782 0.0040
-5.500 -0.2282 0.04731 0.04495 -0.0658 0.9715 0.0040
-5.250 -0.1943 0.04051 0.03794 -0.0717 0.9677 0.0041
-4.750 -0.1314 0.02119 0.01746 -0.0786 0.9559 0.0047
-4.500 -0.1034 0.01773 0.01342 -0.0791 0.9500 0.0046
-4.250 -0.0736 0.01522 0.01040 -0.0797 0.9449 0.0047
-4.000 -0.0435 0.01329 0.00807 -0.0801 0.9393 0.0048
-3.750 -0.0142 0.01198 0.00648 -0.0804 0.9318 0.0050
-3.500 0.0151 0.01110 0.00543 -0.0805 0.9242 0.0054
-3.250 0.0439 0.01042 0.00460 -0.0806 0.9159 0.0060
-3.000 0.0719 0.00990 0.00393 -0.0803 0.9047 0.0069
-2.750 0.0991 0.00941 0.00326 -0.0800 0.8909 0.0087
-2.500 0.1262 0.00898 0.00266 -0.0795 0.8766 0.0109
-2.250 0.1535 0.00872 0.00226 -0.0792 0.8648 0.0144
-2.000 0.1808 0.00851 0.00213 -0.0790 0.8550 0.0414
-1.750 0.2081 0.00843 0.00200 -0.0788 0.8443 0.0525
-1.500 0.2353 0.00836 0.00186 -0.0786 0.8304 0.0587
-1.250 0.2622 0.00826 0.00170 -0.0783 0.8131 0.0639
-1.000 0.2891 0.00821 0.00154 -0.0780 0.7942 0.0669
-0.750 0.3161 0.00816 0.00142 -0.0777 0.7763 0.0746
-0.500 0.3429 0.00804 0.00136 -0.0775 0.7551 0.1122
-0.250 0.3692 0.00806 0.00130 -0.0771 0.7237 0.1413
0.000 0.3943 0.00819 0.00126 -0.0765 0.6725 0.1597
0.250 0.4184 0.00846 0.00127 -0.0757 0.6077 0.1747
0.500 0.4426 0.00877 0.00133 -0.0751 0.5447 0.1946
0.750 0.4677 0.00899 0.00141 -0.0747 0.4957 0.2201
1.000 0.4929 0.00898 0.00153 -0.0745 0.4537 0.3410
1.250 0.5096 0.00784 0.00167 -0.0725 0.4161 0.8609
1.500 0.5423 0.00792 0.00174 -0.0734 0.3741 1.0000
1.750 0.5680 0.00817 0.00183 -0.0731 0.3454 1.0000
2.000 0.5940 0.00840 0.00194 -0.0729 0.3217 1.0000
2.500 0.6463 0.00884 0.00218 -0.0724 0.2830 1.0000
2.750 0.6710 0.00923 0.00235 -0.0720 0.2418 1.0000
3.000 0.6963 0.00957 0.00253 -0.0717 0.2091 1.0000
3.250 0.7215 0.00992 0.00273 -0.0714 0.1810 1.0000
3.500 0.7461 0.01035 0.00295 -0.0710 0.1462 1.0000
3.750 0.7648 0.01165 0.00360 -0.0697 0.0234 1.0000
4.000 0.7906 0.01196 0.00399 -0.0693 0.0124 1.0000
4.250 0.8165 0.01226 0.00437 -0.0690 0.0100 1.0000
4.500 0.8421 0.01260 0.00479 -0.0686 0.0081 1.0000
4.750 0.8663 0.01317 0.00550 -0.0679 0.0065 1.0000
5.000 0.8910 0.01364 0.00608 -0.0673 0.0060 1.0000
5.250 0.9147 0.01431 0.00685 -0.0666 0.0055 1.0000
5.500 0.9384 0.01491 0.00750 -0.0659 0.0047 1.0000
5.750 0.9604 0.01574 0.00839 -0.0650 0.0039 1.0000
6.000 0.9820 0.01662 0.00937 -0.0639 0.0036 1.0000
6.250 1.0020 0.01771 0.01054 -0.0624 0.0033 1.0000
6.500 1.0209 0.01892 0.01186 -0.0608 0.0032 1.0000
6.750 1.0396 0.02023 0.01322 -0.0592 0.0032 1.0000
7.000 1.0588 0.02166 0.01471 -0.0577 0.0032 1.0000
7.250 1.0790 0.02323 0.01632 -0.0563 0.0033 1.0000
7.500 1.1004 0.02496 0.01811 -0.0551 0.0034 1.0000
7.750 1.1222 0.02693 0.02016 -0.0541 0.0035 1.0000
8.000 1.1438 0.02896 0.02232 -0.0530 0.0036 1.0000
8.250 1.1633 0.03016 0.02373 -0.0515 0.0030 1.0000
8.500 1.1809 0.03170 0.02536 -0.0505 0.0026 1.0000
8.750 1.1955 0.03513 0.02892 -0.0493 0.0024 1.0000
9.000 1.2101 0.03645 0.03060 -0.0469 0.0022 1.0000
9.250 1.2214 0.03887 0.03331 -0.0444 0.0021 1.0000
9.500 1.2292 0.04151 0.03625 -0.0417 0.0021 1.0000
9.750 1.2332 0.04430 0.03933 -0.0387 0.0021 1.0000
10.000 1.2336 0.04719 0.04246 -0.0356 0.0021 1.0000
10.250 1.2298 0.05009 0.04561 -0.0323 0.0021 1.0000
10.500 1.2193 0.05277 0.04849 -0.0282 0.0021 1.0000
10.750 1.2065 0.05565 0.05155 -0.0247 0.0022 1.0000
11.000 1.1921 0.05884 0.05492 -0.0219 0.0022 1.0000
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Polar data table (+)
Polar graphs
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