GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Reynolds number: 1,000,000 Max Cl/Cd: 67.57 at α=1° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe114-il-1000000-n5.txt Download as CSV file: xf-goe114-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 114 (MVA MK.1) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2799 0.10949 0.10798 -0.0406 1.0000 0.0021
-11.000 -0.2786 0.10606 0.10456 -0.0412 1.0000 0.0021
-10.750 -0.2776 0.10244 0.10096 -0.0417 1.0000 0.0021
-10.500 -0.2742 0.09835 0.09687 -0.0432 0.9949 0.0021
-10.250 -0.2694 0.09399 0.09251 -0.0453 0.9913 0.0021
-10.000 -0.2646 0.08924 0.08777 -0.0477 0.9878 0.0021
-9.750 -0.2594 0.08458 0.08310 -0.0501 0.9831 0.0021
-9.500 -0.2538 0.07948 0.07800 -0.0531 0.9790 0.0021
-9.250 -0.2477 0.07418 0.07270 -0.0563 0.9733 0.0021
-9.000 -0.2404 0.06858 0.06709 -0.0602 0.9676 0.0021
-8.750 -0.2327 0.06272 0.06122 -0.0646 0.9593 0.0021
-8.500 -0.2246 0.05662 0.05509 -0.0694 0.9480 0.0021
-8.250 -0.2191 0.05045 0.04888 -0.0739 0.9310 0.0021
-8.000 -0.2193 0.04460 0.04296 -0.0770 0.9088 0.0021
-7.750 -0.2253 0.03914 0.03739 -0.0798 0.8869 0.0021
-7.500 -0.2383 0.03403 0.03219 -0.0830 0.8670 0.0021
-7.250 -0.2514 0.03000 0.02805 -0.0884 0.8497 0.0021
-7.000 -0.2560 0.02545 0.02326 -0.0937 0.8371 0.0021
-5.500 -0.1881 0.02137 0.01722 -0.1030 0.8041 0.0016
-5.250 -0.1659 0.01900 0.01452 -0.1020 0.7969 0.0014
-5.000 -0.1424 0.01681 0.01200 -0.1008 0.7903 0.0013
-4.750 -0.1176 0.01498 0.00993 -0.0999 0.7835 0.0013
-4.500 -0.0923 0.01348 0.00821 -0.0990 0.7772 0.0016
-4.250 -0.0668 0.01212 0.00672 -0.0982 0.7708 0.0018
-3.750 -0.0161 0.01065 0.00503 -0.0973 0.7582 0.0029
-3.500 0.0085 0.00970 0.00396 -0.0966 0.7518 0.0028
-3.250 0.0339 0.00895 0.00308 -0.0961 0.7459 0.0027
-3.000 0.0600 0.00841 0.00238 -0.0957 0.7391 0.0030
-2.750 0.0867 0.00804 0.00186 -0.0955 0.7329 0.0036
-2.500 0.1138 0.00780 0.00154 -0.0954 0.7266 0.0053
-2.250 0.1409 0.00763 0.00127 -0.0953 0.7204 0.0087
-2.000 0.1682 0.00751 0.00110 -0.0952 0.7125 0.0190
-1.750 0.1911 0.00654 0.00077 -0.0949 0.7032 0.2464
-1.500 0.2177 0.00648 0.00076 -0.0948 0.6925 0.2833
-1.250 0.2448 0.00647 0.00074 -0.0947 0.6822 0.2977
-1.000 0.2722 0.00649 0.00070 -0.0947 0.6744 0.3037
-0.750 0.2994 0.00650 0.00068 -0.0947 0.6656 0.3074
-0.500 0.3267 0.00651 0.00067 -0.0947 0.6560 0.3104
-0.250 0.3538 0.00655 0.00067 -0.0947 0.6464 0.3135
0.000 0.3809 0.00659 0.00068 -0.0947 0.6365 0.3164
0.250 0.4079 0.00662 0.00070 -0.0946 0.6252 0.3194
0.500 0.4349 0.00666 0.00074 -0.0945 0.6135 0.3230
0.750 0.4591 0.00688 0.00081 -0.0940 0.5715 0.3266
1.000 0.4831 0.00715 0.00090 -0.0934 0.5267 0.3298
1.250 0.5037 0.00770 0.00110 -0.0922 0.4401 0.3333
1.500 0.5077 0.00985 0.00189 -0.0884 0.1012 0.3357
1.750 0.5310 0.01027 0.00215 -0.0877 0.0122 0.3392
2.000 0.5567 0.01046 0.00243 -0.0873 0.0070 0.3434
2.250 0.5824 0.01062 0.00262 -0.0870 0.0045 0.3473
2.500 0.6067 0.01095 0.00305 -0.0863 0.0034 0.3512
2.750 0.6300 0.01139 0.00360 -0.0854 0.0031 0.3550
3.000 0.6518 0.01197 0.00429 -0.0842 0.0030 0.3586
3.250 0.6737 0.01245 0.00482 -0.0832 0.0022 0.3622
3.500 0.6955 0.01297 0.00544 -0.0820 0.0017 0.3660
3.750 0.7132 0.01388 0.00646 -0.0799 0.0014 0.3698
4.000 0.7307 0.01493 0.00758 -0.0778 0.0013 0.3732
4.250 0.7504 0.01618 0.00890 -0.0759 0.0013 0.3774
4.500 0.7756 0.01787 0.01065 -0.0748 0.0014 0.3821
4.750 0.8048 0.01975 0.01262 -0.0744 0.0018 0.3871
7.750 1.0326 0.04799 0.04461 -0.0539 0.0021 1.0000
8.000 1.0450 0.05072 0.04757 -0.0510 0.0019 1.0000
8.250 1.0497 0.05388 0.05092 -0.0480 0.0019 1.0000
8.500 1.0518 0.05707 0.05429 -0.0450 0.0018 1.0000
8.750 1.0505 0.06037 0.05776 -0.0419 0.0017 1.0000
9.000 1.0452 0.06349 0.06104 -0.0388 0.0018 1.0000
9.250 1.0362 0.06650 0.06418 -0.0353 0.0017 1.0000
9.500 1.0201 0.06905 0.06685 -0.0312 0.0018 1.0000
9.750 1.0027 0.07190 0.06981 -0.0282 0.0018 1.0000
10.000 0.9842 0.07522 0.07323 -0.0263 0.0018 1.0000
10.250 0.9642 0.07907 0.07718 -0.0255 0.0018 1.0000
10.500 0.9453 0.08341 0.08162 -0.0259 0.0018 1.0000
10.750 0.9256 0.08841 0.08672 -0.0274 0.0018 1.0000
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Polar data table (+)
Polar graphs
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