GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 379 AIRFOIL (goe379-il) Reynolds number: 500,000 Max Cl/Cd: 103.82 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe379-il-500000-n5.txt Download as CSV file: xf-goe379-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 379 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2841 0.10032 0.09819 -0.0282 1.0000 0.0059
-8.250 -0.2811 0.09728 0.09518 -0.0277 1.0000 0.0060
-8.000 -0.2792 0.09484 0.09277 -0.0273 1.0000 0.0061
-7.750 -0.2670 0.09152 0.08946 -0.0300 0.9919 0.0062
-7.500 -0.2517 0.08791 0.08586 -0.0340 0.9817 0.0062
-7.250 -0.2340 0.08437 0.08231 -0.0383 0.9714 0.0065
-7.000 -0.2105 0.08021 0.07814 -0.0448 0.9602 0.0066
-6.750 -0.1827 0.07596 0.07386 -0.0521 0.9488 0.0071
-6.500 -0.1534 0.07166 0.06952 -0.0597 0.9348 0.0071
-6.250 -0.1265 0.06762 0.06541 -0.0662 0.9166 0.0074
-6.000 -0.1052 0.06415 0.06184 -0.0707 0.8975 0.0076
-5.750 -0.0870 0.06095 0.05855 -0.0739 0.8787 0.0079
-5.500 -0.0671 0.05788 0.05537 -0.0770 0.8621 0.0086
-4.500 0.0154 0.04306 0.04005 -0.0870 0.8060 0.0054
-4.250 0.0390 0.03952 0.03634 -0.0887 0.7912 0.0053
-4.000 0.0635 0.03596 0.03259 -0.0900 0.7762 0.0054
-3.750 0.0898 0.03204 0.02843 -0.0908 0.7621 0.0058
-3.500 0.1137 0.02850 0.02465 -0.0914 0.7492 0.0063
-3.250 0.1379 0.02684 0.02281 -0.0914 0.7369 0.0070
-3.000 0.1618 0.01991 0.01528 -0.0900 0.7282 0.0064
-2.750 0.1827 0.01360 0.00805 -0.0878 0.7190 0.0062
-2.500 0.2074 0.01215 0.00621 -0.0870 0.7071 0.0065
-2.250 0.2328 0.01128 0.00505 -0.0863 0.6949 0.0069
-2.000 0.2584 0.01064 0.00419 -0.0856 0.6826 0.0078
-1.750 0.2841 0.01023 0.00360 -0.0850 0.6691 0.0090
-1.500 0.3092 0.00967 0.00284 -0.0842 0.6551 0.0107
-1.250 0.3344 0.00928 0.00226 -0.0834 0.6402 0.0131
-1.000 0.3599 0.00909 0.00196 -0.0828 0.6255 0.0185
-0.750 0.3854 0.00898 0.00185 -0.0823 0.6112 0.0354
-0.500 0.4114 0.00902 0.00180 -0.0819 0.5966 0.0455
-0.250 0.4371 0.00904 0.00173 -0.0814 0.5816 0.0517
0.000 0.4629 0.00907 0.00169 -0.0810 0.5674 0.0583
0.250 0.4884 0.00907 0.00158 -0.0805 0.5537 0.0611
0.500 0.5140 0.00906 0.00150 -0.0800 0.5418 0.0648
0.750 0.5398 0.00907 0.00147 -0.0796 0.5304 0.0706
1.000 0.5656 0.00910 0.00145 -0.0792 0.5188 0.0786
1.250 0.5911 0.00914 0.00145 -0.0788 0.5061 0.0892
1.500 0.6165 0.00918 0.00147 -0.0783 0.4923 0.1048
1.750 0.6417 0.00922 0.00151 -0.0778 0.4778 0.1320
2.000 0.6664 0.00916 0.00160 -0.0773 0.4653 0.2192
2.500 0.7774 0.00796 0.00190 -0.0908 0.4354 1.0000
2.750 0.8019 0.00812 0.00198 -0.0902 0.4223 1.0000
3.000 0.8261 0.00830 0.00208 -0.0895 0.4064 1.0000
3.250 0.8504 0.00849 0.00220 -0.0889 0.3926 1.0000
3.500 0.8746 0.00867 0.00234 -0.0882 0.3809 1.0000
3.750 0.8987 0.00886 0.00248 -0.0876 0.3693 1.0000
4.000 0.9230 0.00905 0.00264 -0.0869 0.3589 1.0000
4.250 0.9473 0.00922 0.00282 -0.0863 0.3508 1.0000
4.500 0.9714 0.00941 0.00301 -0.0857 0.3431 1.0000
4.750 0.9956 0.00959 0.00320 -0.0850 0.3350 1.0000
5.000 1.0181 0.00991 0.00343 -0.0842 0.3153 1.0000
5.250 1.0401 0.01026 0.00371 -0.0832 0.2896 1.0000
5.500 1.0609 0.01071 0.00401 -0.0821 0.2551 1.0000
5.750 1.0737 0.01189 0.00464 -0.0798 0.1626 1.0000
6.000 1.0767 0.01402 0.00599 -0.0760 0.0174 1.0000
6.250 1.0972 0.01453 0.00656 -0.0747 0.0100 1.0000
6.500 1.1182 0.01495 0.00708 -0.0735 0.0081 1.0000
6.750 1.1372 0.01554 0.00778 -0.0720 0.0067 1.0000
7.000 1.1557 0.01618 0.00853 -0.0705 0.0057 1.0000
7.250 1.1747 0.01672 0.00913 -0.0691 0.0048 1.0000
7.500 1.1913 0.01744 0.00992 -0.0673 0.0043 1.0000
7.750 1.2035 0.01849 0.01109 -0.0647 0.0038 1.0000
8.000 1.2165 0.01939 0.01210 -0.0624 0.0037 1.0000
8.250 1.2264 0.02045 0.01332 -0.0595 0.0035 1.0000
8.500 1.2338 0.02155 0.01454 -0.0563 0.0033 1.0000
8.750 1.2367 0.02268 0.01578 -0.0524 0.0033 1.0000
9.000 1.2390 0.02394 0.01714 -0.0485 0.0031 1.0000
9.250 1.2439 0.02514 0.01843 -0.0455 0.0029 1.0000
9.500 1.2469 0.02662 0.02001 -0.0424 0.0028 1.0000
9.750 1.2567 0.02753 0.02096 -0.0408 0.0025 1.0000
10.000 1.2579 0.02935 0.02289 -0.0381 0.0023 1.0000
10.250 1.2609 0.03125 0.02494 -0.0357 0.0022 1.0000
10.500 1.2647 0.03324 0.02706 -0.0335 0.0022 1.0000
10.750 1.2694 0.03566 0.02967 -0.0311 0.0019 1.0000
11.000 1.2756 0.03804 0.03222 -0.0291 0.0019 1.0000
11.250 1.2818 0.04063 0.03500 -0.0271 0.0018 1.0000
11.500 1.2859 0.04354 0.03813 -0.0252 0.0017 1.0000
11.750 1.2866 0.04664 0.04146 -0.0234 0.0017 1.0000
12.000 1.2837 0.05019 0.04524 -0.0218 0.0017 1.0000
12.250 1.2797 0.05347 0.04872 -0.0206 0.0017 1.0000
12.500 1.2717 0.05737 0.05284 -0.0196 0.0018 1.0000
12.750 1.2612 0.06154 0.05721 -0.0192 0.0018 1.0000
13.000 1.2479 0.06622 0.06211 -0.0192 0.0017 1.0000
13.250 1.2351 0.07091 0.06699 -0.0199 0.0017 1.0000
13.500 1.2213 0.07595 0.07221 -0.0211 0.0018 1.0000
13.750 1.2043 0.08181 0.07825 -0.0229 0.0018 1.0000
14.000 1.1890 0.08768 0.08429 -0.0252 0.0018 1.0000
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Polar data table (+)
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