GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 655 AIRFOIL (goe655-il) Reynolds number: 100,000 Max Cl/Cd: 49.03 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe655-il-100000-n5.txt Download as CSV file: xf-goe655-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 655 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 -0.3436 0.09301 0.08809 -0.0471 1.0000 0.0480
-9.750 -0.3598 0.08845 0.08361 -0.0477 1.0000 0.0481
-9.500 -0.3761 0.08453 0.07978 -0.0475 1.0000 0.0481
-9.250 -0.3958 0.08077 0.07612 -0.0470 1.0000 0.0479
-9.000 -0.4223 0.07698 0.07244 -0.0461 1.0000 0.0477
-8.750 -0.4501 0.06017 0.05539 -0.0662 0.9839 0.0472
-8.500 -0.4653 0.04971 0.04426 -0.0753 0.9680 0.0477
-8.250 -0.4566 0.04369 0.03755 -0.0795 0.9586 0.0488
-8.000 -0.4363 0.04176 0.03555 -0.0801 0.9493 0.0499
-7.750 -0.4082 0.03918 0.03270 -0.0826 0.9440 0.0510
-7.500 -0.3907 0.03666 0.02983 -0.0827 0.9336 0.0519
-7.250 -0.3611 0.03419 0.02694 -0.0847 0.9285 0.0536
-7.000 -0.3412 0.03224 0.02458 -0.0843 0.9183 0.0553
-6.750 -0.3096 0.03021 0.02202 -0.0857 0.9131 0.0568
-6.500 -0.2851 0.02863 0.02027 -0.0855 0.9042 0.0578
-6.250 -0.2532 0.02728 0.01882 -0.0866 0.8982 0.0592
-6.000 -0.2243 0.02626 0.01768 -0.0870 0.8907 0.0612
-5.750 -0.1950 0.02525 0.01648 -0.0873 0.8829 0.0637
-5.500 -0.1632 0.02419 0.01522 -0.0880 0.8762 0.0657
-5.250 -0.1356 0.02327 0.01416 -0.0877 0.8670 0.0673
-5.000 -0.1057 0.02230 0.01321 -0.0881 0.8589 0.0695
-4.750 -0.0758 0.02152 0.01239 -0.0882 0.8485 0.0730
-4.500 -0.0483 0.02083 0.01159 -0.0878 0.8355 0.0769
-4.250 -0.0202 0.02006 0.01078 -0.0875 0.8230 0.0806
-4.000 0.0097 0.01938 0.01004 -0.0875 0.8116 0.0854
-3.750 0.0372 0.01883 0.00942 -0.0872 0.7997 0.0923
-3.500 0.0634 0.01832 0.00891 -0.0867 0.7881 0.1025
-3.250 0.0920 0.01778 0.00838 -0.0866 0.7777 0.1189
-3.000 0.1194 0.01723 0.00798 -0.0863 0.7665 0.1525
-2.750 0.1452 0.01681 0.00771 -0.0858 0.7544 0.2021
-2.500 0.1727 0.01647 0.00749 -0.0856 0.7431 0.2538
-2.250 0.2008 0.01621 0.00728 -0.0853 0.7316 0.3010
-2.000 0.2259 0.01602 0.00716 -0.0846 0.7185 0.3433
-1.750 0.2515 0.01582 0.00706 -0.0839 0.7059 0.3931
-1.500 0.2772 0.01558 0.00696 -0.0832 0.6937 0.4542
-1.250 0.3028 0.01535 0.00686 -0.0824 0.6810 0.5122
-1.000 0.3272 0.01514 0.00679 -0.0814 0.6671 0.5671
-0.750 0.3508 0.01489 0.00675 -0.0801 0.6531 0.6411
-0.500 0.3771 0.01462 0.00675 -0.0789 0.6387 0.7528
-0.250 0.4366 0.01447 0.00671 -0.0843 0.6213 0.8990
0.000 0.4954 0.01452 0.00656 -0.0903 0.6032 0.9794
0.250 0.5311 0.01466 0.00649 -0.0919 0.5868 1.0000
0.500 0.5522 0.01480 0.00644 -0.0905 0.5716 1.0000
0.750 0.5734 0.01497 0.00642 -0.0891 0.5565 1.0000
1.000 0.5947 0.01516 0.00643 -0.0878 0.5418 1.0000
1.250 0.6162 0.01537 0.00645 -0.0865 0.5279 1.0000
1.500 0.6380 0.01559 0.00651 -0.0852 0.5149 1.0000
1.750 0.6597 0.01583 0.00661 -0.0840 0.5022 1.0000
2.000 0.6819 0.01608 0.00673 -0.0829 0.4910 1.0000
2.250 0.7044 0.01635 0.00685 -0.0818 0.4809 1.0000
2.500 0.7267 0.01662 0.00703 -0.0807 0.4704 1.0000
2.750 0.7494 0.01691 0.00720 -0.0797 0.4613 1.0000
3.000 0.7717 0.01720 0.00739 -0.0787 0.4516 1.0000
3.250 0.7942 0.01750 0.00760 -0.0776 0.4425 1.0000
3.500 0.8167 0.01781 0.00781 -0.0766 0.4340 1.0000
3.750 0.8390 0.01812 0.00806 -0.0757 0.4254 1.0000
4.000 0.8614 0.01844 0.00829 -0.0747 0.4175 1.0000
4.250 0.8835 0.01876 0.00858 -0.0737 0.4094 1.0000
4.500 0.9058 0.01909 0.00883 -0.0727 0.4021 1.0000
4.750 0.9281 0.01944 0.00914 -0.0717 0.3950 1.0000
5.000 0.9498 0.01977 0.00946 -0.0707 0.3877 1.0000
5.250 0.9719 0.02013 0.00974 -0.0697 0.3811 1.0000
5.500 0.9934 0.02049 0.01013 -0.0687 0.3743 1.0000
5.750 1.0157 0.02086 0.01047 -0.0678 0.3687 1.0000
6.000 1.0378 0.02126 0.01086 -0.0669 0.3634 1.0000
6.250 1.0591 0.02165 0.01130 -0.0659 0.3576 1.0000
6.500 1.0808 0.02205 0.01169 -0.0649 0.3523 1.0000
6.750 1.1017 0.02247 0.01213 -0.0639 0.3466 1.0000
7.000 1.1213 0.02289 0.01262 -0.0627 0.3404 1.0000
7.250 1.1418 0.02331 0.01301 -0.0615 0.3347 1.0000
7.500 1.1605 0.02377 0.01354 -0.0602 0.3285 1.0000
7.750 1.1785 0.02422 0.01406 -0.0587 0.3221 1.0000
8.000 1.1984 0.02468 0.01447 -0.0576 0.3169 1.0000
8.250 1.2142 0.02519 0.01514 -0.0558 0.3103 1.0000
8.500 1.2306 0.02568 0.01568 -0.0542 0.3042 1.0000
8.750 1.2468 0.02618 0.01619 -0.0525 0.2986 1.0000
9.000 1.2586 0.02674 0.01689 -0.0502 0.2917 1.0000
9.250 1.2721 0.02727 0.01745 -0.0481 0.2856 1.0000
9.500 1.2830 0.02791 0.01820 -0.0458 0.2787 1.0000
9.750 1.2941 0.02855 0.01890 -0.0436 0.2721 1.0000
10.000 1.3052 0.02925 0.01965 -0.0415 0.2658 1.0000
10.250 1.3149 0.03003 0.02055 -0.0394 0.2590 1.0000
10.500 1.3266 0.03077 0.02130 -0.0376 0.2541 1.0000
10.750 1.3356 0.03174 0.02243 -0.0356 0.2477 1.0000
11.000 1.3453 0.03266 0.02341 -0.0338 0.2426 1.0000
11.250 1.3556 0.03360 0.02439 -0.0321 0.2382 1.0000
11.500 1.3635 0.03477 0.02572 -0.0304 0.2330 1.0000
11.750 1.3720 0.03588 0.02690 -0.0288 0.2287 1.0000
12.000 1.3816 0.03696 0.02799 -0.0274 0.2250 1.0000
12.250 1.3868 0.03844 0.02964 -0.0258 0.2205 1.0000
12.500 1.3925 0.03985 0.03115 -0.0244 0.2163 1.0000
12.750 1.3995 0.04113 0.03244 -0.0231 0.2125 1.0000
13.000 1.4015 0.04296 0.03443 -0.0218 0.2083 1.0000
13.250 1.4019 0.04491 0.03650 -0.0206 0.2036 1.0000
13.500 1.4053 0.04659 0.03820 -0.0196 0.1993 1.0000
13.750 1.4045 0.04884 0.04057 -0.0188 0.1952 1.0000
14.000 1.4011 0.05143 0.04331 -0.0181 0.1909 1.0000
14.250 1.4012 0.05369 0.04564 -0.0176 0.1870 1.0000
14.500 1.4024 0.05592 0.04789 -0.0171 0.1830 1.0000
14.750 1.3947 0.05936 0.05155 -0.0171 0.1795 1.0000
15.000 1.3889 0.06265 0.05499 -0.0172 0.1759 1.0000
15.250 1.3883 0.06538 0.05778 -0.0173 0.1724 1.0000
15.500 1.3888 0.06803 0.06047 -0.0174 0.1687 1.0000
15.750 1.3746 0.07286 0.06554 -0.0184 0.1660 1.0000
16.000 1.3612 0.07777 0.07064 -0.0196 0.1629 1.0000
16.250 1.3535 0.08195 0.07495 -0.0207 0.1596 1.0000
16.500 1.3640 0.08327 0.07621 -0.0206 0.1553 1.0000
16.750 1.3394 0.09037 0.08358 -0.0232 0.1532 1.0000
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