GOE 437 AIRFOIL (goe437-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 437 AIRFOIL (goe437-il) Reynolds number: 50,000 Max Cl/Cd: 41.18 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe437-il-50000.txt Download as CSV file: xf-goe437-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 437 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3268 0.10470 0.09808 -0.0247 1.0000 0.1328
-7.750 -0.3322 0.10347 0.09697 -0.0250 1.0000 0.1364
-7.500 -0.3465 0.10357 0.09726 -0.0255 1.0000 0.1380
-7.250 -0.3349 0.09841 0.09214 -0.0238 1.0000 0.1415
-7.000 -0.3317 0.09557 0.08938 -0.0228 1.0000 0.1470
-6.750 -0.3390 0.09467 0.08861 -0.0246 1.0000 0.1514
-6.500 -0.3396 0.09206 0.08612 -0.0252 1.0000 0.1539
-6.250 -0.3323 0.08828 0.08239 -0.0224 1.0000 0.1612
-6.000 -0.3378 0.08795 0.08215 -0.0271 1.0000 0.1664
-5.500 -0.3322 0.08275 0.07709 -0.0278 1.0000 0.1808
-5.250 -0.3285 0.07854 0.07297 -0.0220 1.0000 0.1904
-4.750 -0.3215 0.07378 0.06830 -0.0243 1.0000 0.2097
-4.500 -0.3150 0.07143 0.06595 -0.0254 1.0000 0.2228
-4.250 -0.3081 0.06877 0.06326 -0.0254 1.0000 0.2365
-4.000 -0.3016 0.06582 0.06035 -0.0244 1.0000 0.2508
-3.750 -0.2958 0.06284 0.05743 -0.0225 1.0000 0.2663
-3.500 -0.2890 0.06015 0.05478 -0.0207 1.0000 0.2860
-3.250 -0.2815 0.05757 0.05223 -0.0194 1.0000 0.3138
-3.000 -0.2760 0.05511 0.04983 -0.0172 1.0000 0.3524
-2.750 -0.2753 0.05283 0.04765 -0.0124 1.0000 0.3975
-1.750 -0.0529 0.03713 0.02920 -0.0525 1.0000 0.1639
-1.500 -0.0246 0.03486 0.02652 -0.0536 1.0000 0.1588
-1.250 0.0020 0.03315 0.02437 -0.0542 1.0000 0.1607
-1.000 0.0282 0.03160 0.02234 -0.0545 1.0000 0.1598
-0.750 0.0511 0.03061 0.02102 -0.0546 1.0000 0.1714
-0.500 0.0776 0.02977 0.01985 -0.0553 0.9982 0.1851
-0.250 0.1366 0.02886 0.01842 -0.0612 0.9842 0.2234
0.000 0.1975 0.02780 0.01725 -0.0673 0.9703 0.2891
0.500 0.3059 0.02561 0.01622 -0.0769 0.9371 1.0000
0.750 0.3545 0.02626 0.01642 -0.0812 0.9182 1.0000
1.000 0.4057 0.02679 0.01663 -0.0857 0.9009 1.0000
1.250 0.4434 0.02727 0.01692 -0.0879 0.8816 1.0000
1.500 0.4862 0.02764 0.01712 -0.0907 0.8639 1.0000
1.750 0.5322 0.02787 0.01723 -0.0938 0.8477 1.0000
2.000 0.5796 0.02795 0.01725 -0.0968 0.8323 1.0000
2.250 0.6161 0.02822 0.01748 -0.0981 0.8156 1.0000
2.500 0.6491 0.02853 0.01778 -0.0987 0.7984 1.0000
2.750 0.6842 0.02875 0.01800 -0.0994 0.7823 1.0000
3.000 0.7188 0.02897 0.01828 -0.0999 0.7668 1.0000
3.250 0.7523 0.02919 0.01853 -0.1002 0.7515 1.0000
3.500 0.7838 0.02949 0.01888 -0.1002 0.7366 1.0000
3.750 0.8136 0.02988 0.01933 -0.0999 0.7218 1.0000
4.000 0.8416 0.03037 0.01990 -0.0995 0.7072 1.0000
4.250 0.8676 0.03100 0.02068 -0.0988 0.6930 1.0000
4.500 0.8920 0.03174 0.02153 -0.0980 0.6789 1.0000
4.750 0.9144 0.03263 0.02254 -0.0972 0.6652 1.0000
5.000 0.9357 0.03361 0.02367 -0.0962 0.6517 1.0000
5.250 0.9553 0.03476 0.02497 -0.0952 0.6385 1.0000
5.500 0.9744 0.03596 0.02641 -0.0941 0.6256 1.0000
5.750 0.9929 0.03723 0.02786 -0.0930 0.6128 1.0000
6.000 1.0120 0.03845 0.02929 -0.0919 0.6001 1.0000
6.250 1.0311 0.03967 0.03074 -0.0907 0.5874 1.0000
6.500 1.0508 0.04084 0.03215 -0.0894 0.5746 1.0000
6.750 1.0710 0.04200 0.03365 -0.0882 0.5618 1.0000
7.000 1.1471 0.03273 0.02438 -0.0820 0.5022 1.0000
7.250 1.1727 0.03002 0.02160 -0.0772 0.4549 1.0000
7.500 1.1740 0.02851 0.02011 -0.0705 0.3949 1.0000
7.750 1.1683 0.02843 0.01982 -0.0640 0.3141 1.0000
8.000 1.1545 0.03075 0.02104 -0.0583 0.1676 1.0000
8.250 1.1461 0.03410 0.02375 -0.0545 0.1210 1.0000
8.500 1.1432 0.03671 0.02620 -0.0510 0.1061 1.0000
8.750 1.1425 0.03913 0.02861 -0.0477 0.0979 1.0000
9.000 1.1446 0.04150 0.03098 -0.0449 0.0917 1.0000
9.250 1.1581 0.04374 0.03332 -0.0425 0.0861 1.0000
9.500 1.1947 0.04643 0.03582 -0.0422 0.0776 1.0000
9.750 1.2363 0.04938 0.03921 -0.0425 0.0728 1.0000
10.000 1.2740 0.05340 0.04363 -0.0426 0.0718 1.0000
10.250 1.2930 0.05754 0.04825 -0.0414 0.0720 1.0000
10.500 1.3016 0.06179 0.05305 -0.0396 0.0729 1.0000
10.750 1.3028 0.06611 0.05779 -0.0375 0.0739 1.0000
11.000 1.2991 0.07045 0.06250 -0.0353 0.0749 1.0000
11.250 1.2903 0.07465 0.06698 -0.0330 0.0757 1.0000
11.500 1.2791 0.07896 0.07154 -0.0311 0.0764 1.0000
11.750 1.2678 0.08368 0.07645 -0.0298 0.0771 1.0000
12.000 1.2592 0.08893 0.08191 -0.0293 0.0777 1.0000
12.250 1.2193 0.09240 0.08570 -0.0294 0.0787 1.0000
12.500 1.1780 0.09849 0.09203 -0.0326 0.0794 1.0000
12.750 1.1381 0.10658 0.10022 -0.0383 0.0800 1.0000
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Polar data table (+)
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