GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.26 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe116-il-1000000.txt Download as CSV file: xf-goe116-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 116 (MVA MK.3) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4160 0.08252 0.08107 -0.0335 1.0000 0.0080
-8.750 -0.4168 0.07537 0.07386 -0.0395 0.9450 0.0080
-8.500 -0.4268 0.06977 0.06803 -0.0424 0.8797 0.0080
-8.250 -0.4322 0.06258 0.06067 -0.0502 0.8460 0.0080
-8.000 -0.4240 0.05032 0.04817 -0.0683 0.8268 0.0080
-7.750 -0.4078 0.04037 0.03776 -0.0811 0.8133 0.0080
-7.500 -0.3931 0.03560 0.03258 -0.0849 0.8022 0.0080
-7.250 -0.3757 0.03169 0.02829 -0.0870 0.7923 0.0080
-7.000 -0.3560 0.02828 0.02450 -0.0882 0.7837 0.0080
-6.750 -0.3415 0.02099 0.01669 -0.0891 0.7761 0.0076
-6.250 -0.2931 0.01651 0.01157 -0.0896 0.7616 0.0091
-6.000 -0.2661 0.01523 0.01008 -0.0896 0.7548 0.0088
-5.750 -0.2390 0.01424 0.00891 -0.0895 0.7481 0.0087
-5.500 -0.2122 0.01310 0.00767 -0.0897 0.7417 0.0090
-5.250 -0.1849 0.01233 0.00679 -0.0898 0.7355 0.0097
-5.000 -0.1570 0.01149 0.00581 -0.0899 0.7298 0.0094
-4.750 -0.1288 0.01078 0.00497 -0.0899 0.7239 0.0095
-4.500 -0.1006 0.01022 0.00428 -0.0901 0.7186 0.0100
-4.250 -0.0720 0.00975 0.00372 -0.0903 0.7131 0.0110
-4.000 -0.0435 0.00940 0.00325 -0.0904 0.7078 0.0120
-3.750 -0.0148 0.00911 0.00287 -0.0906 0.7029 0.0127
-3.500 0.0139 0.00888 0.00257 -0.0907 0.6978 0.0132
-3.250 0.0425 0.00860 0.00213 -0.0908 0.6929 0.0158
-3.000 0.0714 0.00840 0.00186 -0.0910 0.6882 0.0198
-2.750 0.0993 0.00774 0.00159 -0.0914 0.6834 0.1228
-2.500 0.1280 0.00787 0.00174 -0.0915 0.6788 0.1363
-2.250 0.1570 0.00804 0.00188 -0.0917 0.6743 0.1407
-2.000 0.1857 0.00795 0.00178 -0.0920 0.6698 0.1451
-1.750 0.2143 0.00798 0.00179 -0.0922 0.6655 0.1481
-1.500 0.2433 0.00814 0.00194 -0.0924 0.6616 0.1531
-1.250 0.2721 0.00813 0.00192 -0.0926 0.6575 0.1542
-1.000 0.3007 0.00810 0.00185 -0.0928 0.6535 0.1546
-0.750 0.3292 0.00798 0.00170 -0.0930 0.6497 0.1561
-0.500 0.3579 0.00785 0.00159 -0.0933 0.6460 0.1577
-0.250 0.3866 0.00779 0.00154 -0.0936 0.6421 0.1591
0.000 0.4152 0.00776 0.00150 -0.0938 0.6383 0.1603
0.250 0.4439 0.00774 0.00149 -0.0940 0.6344 0.1617
0.500 0.4726 0.00770 0.00147 -0.0942 0.6296 0.1633
0.750 0.5011 0.00770 0.00146 -0.0944 0.6245 0.1647
1.000 0.5297 0.00768 0.00146 -0.0946 0.6198 0.1659
1.250 0.5584 0.00766 0.00146 -0.0949 0.6152 0.1671
1.500 0.5868 0.00768 0.00147 -0.0950 0.6100 0.1681
1.750 0.6155 0.00764 0.00147 -0.0953 0.6041 0.1703
2.000 0.6440 0.00762 0.00149 -0.0955 0.5983 0.1732
2.250 0.6724 0.00761 0.00151 -0.0957 0.5900 0.1761
2.500 0.7006 0.00763 0.00153 -0.0958 0.5773 0.1789
2.750 0.7287 0.00767 0.00157 -0.0959 0.5649 0.1816
3.000 0.7567 0.00770 0.00162 -0.0960 0.5485 0.1866
3.250 0.7840 0.00782 0.00169 -0.0961 0.5183 0.1929
3.500 0.8093 0.00823 0.00187 -0.0958 0.4539 0.2033
3.750 0.8192 0.01078 0.00304 -0.0938 0.1567 0.2217
4.000 0.8334 0.01045 0.00393 -0.0921 0.0203 1.0000
4.250 0.8591 0.01084 0.00437 -0.0917 0.0147 1.0000
4.500 0.8848 0.01120 0.00477 -0.0914 0.0135 1.0000
4.750 0.9103 0.01157 0.00517 -0.0910 0.0125 1.0000
5.000 0.9351 0.01202 0.00565 -0.0906 0.0113 1.0000
5.250 0.9592 0.01252 0.00620 -0.0900 0.0102 1.0000
5.500 0.9806 0.01330 0.00705 -0.0890 0.0090 1.0000
5.750 0.9946 0.01485 0.00874 -0.0867 0.0084 1.0000
6.000 1.0168 0.01545 0.00937 -0.0859 0.0082 1.0000
6.250 1.0391 0.01601 0.00997 -0.0850 0.0079 1.0000
6.500 1.0598 0.01673 0.01073 -0.0839 0.0074 1.0000
6.750 1.0786 0.01764 0.01169 -0.0825 0.0069 1.0000
7.000 1.0961 0.01877 0.01288 -0.0808 0.0066 1.0000
7.250 1.1131 0.02028 0.01448 -0.0789 0.0065 1.0000
7.500 1.1337 0.02271 0.01702 -0.0774 0.0070 1.0000
7.750 1.1578 0.02480 0.01922 -0.0765 0.0071 1.0000
8.000 1.1821 0.02753 0.02210 -0.0757 0.0074 1.0000
8.750 1.2308 0.04025 0.03558 -0.0708 0.0083 1.0000
9.000 1.2524 0.03793 0.03336 -0.0693 0.0074 1.0000
9.250 1.2688 0.03908 0.03465 -0.0677 0.0064 1.0000
9.500 1.2795 0.04084 0.03655 -0.0658 0.0060 1.0000
9.750 1.2877 0.04263 0.03850 -0.0638 0.0057 1.0000
10.000 1.2937 0.04453 0.04052 -0.0617 0.0055 1.0000
10.250 1.2977 0.04668 0.04276 -0.0594 0.0054 1.0000
10.500 1.2933 0.04949 0.04574 -0.0562 0.0052 1.0000
10.750 1.2781 0.05289 0.04933 -0.0518 0.0051 1.0000
11.000 1.2476 0.05839 0.05510 -0.0472 0.0050 1.0000
11.250 1.2031 0.06586 0.06289 -0.0432 0.0049 1.0000
11.500 1.1852 0.06969 0.06688 -0.0418 0.0049 1.0000
11.750 1.1664 0.07395 0.07129 -0.0411 0.0049 1.0000
12.000 1.1479 0.07855 0.07604 -0.0411 0.0049 1.0000
12.250 1.1289 0.08356 0.08118 -0.0417 0.0049 1.0000
12.500 1.1095 0.08901 0.08677 -0.0431 0.0049 1.0000
12.750 1.0899 0.09493 0.09281 -0.0451 0.0049 1.0000
13.000 1.0712 0.10120 0.09920 -0.0478 0.0049 1.0000
13.250 1.0528 0.10795 0.10606 -0.0512 0.0049 1.0000
13.500 1.0359 0.11529 0.11351 -0.0554 0.0049 1.0000
13.750 0.8713 0.10744 0.10585 -0.0356 0.0057 1.0000
14.000 0.8285 0.11805 0.11662 -0.0416 0.0061 1.0000
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Polar data table (+)
Polar graphs
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