GOE 647 AIRFOIL (goe647-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 647 AIRFOIL (goe647-il) Reynolds number: 100,000 Max Cl/Cd: 44.5 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe647-il-100000-n5.txt Download as CSV file: xf-goe647-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 647 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2641 0.08523 0.08034 -0.0649 0.9756 0.0531
-9.750 -0.2800 0.07458 0.06967 -0.0742 0.9653 0.0530
-9.500 -0.3514 0.05421 0.04893 -0.0972 0.9420 0.0522
-9.250 -0.3713 0.04658 0.04070 -0.1035 0.9258 0.0524
-9.000 -0.3764 0.04175 0.03521 -0.1050 0.9120 0.0531
-8.750 -0.3510 0.03932 0.03260 -0.1070 0.9060 0.0539
-8.500 -0.3358 0.03752 0.03063 -0.1065 0.8943 0.0545
-8.250 -0.3092 0.03531 0.02813 -0.1080 0.8881 0.0552
-8.000 -0.2932 0.03367 0.02626 -0.1070 0.8761 0.0559
-7.750 -0.2653 0.03179 0.02408 -0.1081 0.8696 0.0570
-7.500 -0.2471 0.03044 0.02247 -0.1069 0.8578 0.0582
-7.250 -0.2195 0.02887 0.02050 -0.1074 0.8503 0.0599
-7.000 -0.1977 0.02786 0.01942 -0.1065 0.8391 0.0610
-6.750 -0.1687 0.02683 0.01830 -0.1068 0.8311 0.0624
-6.500 -0.1456 0.02595 0.01732 -0.1060 0.8199 0.0636
-6.250 -0.1184 0.02502 0.01623 -0.1058 0.8109 0.0652
-6.000 -0.0936 0.02421 0.01525 -0.1051 0.8001 0.0671
-5.750 -0.0687 0.02349 0.01448 -0.1045 0.7894 0.0692
-5.500 -0.0419 0.02284 0.01378 -0.1041 0.7788 0.0719
-5.250 -0.0191 0.02228 0.01312 -0.1029 0.7655 0.0749
-5.000 0.0057 0.02166 0.01239 -0.1021 0.7534 0.0778
-4.750 0.0310 0.02109 0.01177 -0.1014 0.7417 0.0816
-4.500 0.0538 0.02066 0.01123 -0.1002 0.7287 0.0870
-4.250 0.0780 0.02015 0.01069 -0.0994 0.7176 0.0937
-4.000 0.1023 0.01964 0.01013 -0.0985 0.7068 0.1029
-3.750 0.1253 0.01918 0.00965 -0.0975 0.6953 0.1151
-3.500 0.1504 0.01867 0.00917 -0.0968 0.6852 0.1348
-3.250 0.1735 0.01832 0.00899 -0.0959 0.6735 0.1680
-3.000 0.1986 0.01813 0.00883 -0.0952 0.6629 0.2097
-2.750 0.2243 0.01800 0.00866 -0.0945 0.6521 0.2436
-2.500 0.2482 0.01792 0.00859 -0.0936 0.6404 0.2727
-2.250 0.2741 0.01786 0.00846 -0.0929 0.6300 0.2998
-2.000 0.2980 0.01780 0.00841 -0.0919 0.6184 0.3224
-1.750 0.3226 0.01775 0.00832 -0.0911 0.6071 0.3421
-1.500 0.3479 0.01771 0.00821 -0.0903 0.5964 0.3612
-1.250 0.3715 0.01769 0.00819 -0.0893 0.5843 0.3819
-1.000 0.3963 0.01767 0.00813 -0.0885 0.5733 0.4034
-0.750 0.4205 0.01765 0.00808 -0.0875 0.5615 0.4265
-0.500 0.4444 0.01765 0.00807 -0.0866 0.5493 0.4519
-0.250 0.4691 0.01761 0.00800 -0.0858 0.5380 0.4783
0.000 0.4936 0.01759 0.00797 -0.0850 0.5258 0.5055
0.250 0.5174 0.01756 0.00798 -0.0840 0.5138 0.5350
0.500 0.5409 0.01750 0.00796 -0.0830 0.5024 0.5746
1.000 0.6132 0.01703 0.00820 -0.0854 0.4763 0.8599
1.250 0.6733 0.01728 0.00827 -0.0920 0.4618 1.0000
1.500 0.6941 0.01754 0.00831 -0.0906 0.4520 1.0000
1.750 0.7145 0.01780 0.00844 -0.0892 0.4414 1.0000
2.000 0.7353 0.01808 0.00853 -0.0879 0.4326 1.0000
2.250 0.7560 0.01837 0.00871 -0.0865 0.4234 1.0000
2.500 0.7772 0.01868 0.00884 -0.0853 0.4161 1.0000
2.750 0.7981 0.01899 0.00907 -0.0841 0.4080 1.0000
3.000 0.8192 0.01932 0.00925 -0.0828 0.4012 1.0000
3.250 0.8403 0.01966 0.00950 -0.0817 0.3942 1.0000
3.500 0.8611 0.02000 0.00975 -0.0804 0.3874 1.0000
3.750 0.8828 0.02037 0.00996 -0.0794 0.3820 1.0000
4.000 0.9035 0.02074 0.01031 -0.0782 0.3758 1.0000
4.250 0.9247 0.02112 0.01062 -0.0771 0.3704 1.0000
4.500 0.9469 0.02151 0.01089 -0.0762 0.3660 1.0000
4.750 0.9681 0.02193 0.01127 -0.0751 0.3613 1.0000
5.000 0.9887 0.02234 0.01167 -0.0740 0.3564 1.0000
5.250 1.0097 0.02276 0.01203 -0.0730 0.3519 1.0000
5.500 1.0325 0.02320 0.01234 -0.0722 0.3481 1.0000
5.750 1.0521 0.02366 0.01283 -0.0710 0.3438 1.0000
6.000 1.0717 0.02414 0.01331 -0.0698 0.3395 1.0000
6.250 1.0925 0.02461 0.01376 -0.0688 0.3359 1.0000
6.500 1.1144 0.02508 0.01419 -0.0680 0.3327 1.0000
6.750 1.1385 0.02560 0.01461 -0.0676 0.3299 1.0000
7.000 1.1556 0.02616 0.01526 -0.0661 0.3265 1.0000
7.250 1.1732 0.02672 0.01588 -0.0647 0.3231 1.0000
7.500 1.1914 0.02726 0.01643 -0.0634 0.3199 1.0000
7.750 1.2111 0.02779 0.01694 -0.0624 0.3168 1.0000
8.000 1.2339 0.02832 0.01741 -0.0618 0.3141 1.0000
8.250 1.2517 0.02897 0.01810 -0.0606 0.3115 1.0000
8.500 1.2646 0.02969 0.01893 -0.0586 0.3087 1.0000
8.750 1.2788 0.03041 0.01973 -0.0569 0.3060 1.0000
9.000 1.2947 0.03112 0.02051 -0.0555 0.3035 1.0000
9.250 1.3124 0.03180 0.02122 -0.0544 0.3011 1.0000
9.500 1.3324 0.03245 0.02188 -0.0537 0.2989 1.0000
9.750 1.3560 0.03307 0.02246 -0.0534 0.2968 1.0000
10.000 1.3668 0.03398 0.02349 -0.0515 0.2945 1.0000
10.250 1.3703 0.03510 0.02478 -0.0488 0.2920 1.0000
10.500 1.3762 0.03621 0.02603 -0.0466 0.2894 1.0000
10.750 1.3849 0.03730 0.02723 -0.0449 0.2872 1.0000
11.000 1.3960 0.03835 0.02837 -0.0434 0.2851 1.0000
11.250 1.4100 0.03931 0.02938 -0.0423 0.2832 1.0000
11.500 1.4281 0.04014 0.03024 -0.0416 0.2815 1.0000
11.750 1.4528 0.04077 0.03087 -0.0416 0.2797 1.0000
12.000 1.4440 0.04275 0.03306 -0.0387 0.2776 1.0000
12.250 1.4248 0.04545 0.03601 -0.0355 0.2751 1.0000
12.500 1.4078 0.04840 0.03918 -0.0331 0.2725 1.0000
12.750 1.3938 0.05146 0.04241 -0.0313 0.2702 1.0000
13.000 1.3855 0.05432 0.04540 -0.0301 0.2680 1.0000
13.250 1.3910 0.05615 0.04731 -0.0294 0.2660 1.0000
13.500 1.4118 0.05676 0.04794 -0.0290 0.2644 1.0000
13.750 1.4469 0.05631 0.04746 -0.0291 0.2629 1.0000
14.750 0.9877 0.13329 0.12544 -0.0489 0.2181 1.0000
15.000 0.9609 0.14186 0.13408 -0.0525 0.2103 1.0000
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Polar data table (+)
Polar graphs
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