GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Reynolds number: 500,000 Max Cl/Cd: 74.78 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe114-il-500000-n5.txt Download as CSV file: xf-goe114-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3626 0.09160 0.08945 -0.0433 1.0000 0.0039
-8.750 -0.3629 0.08805 0.08594 -0.0441 1.0000 0.0039
-8.500 -0.3649 0.08466 0.08259 -0.0445 1.0000 0.0039
-8.250 -0.3554 0.07930 0.07725 -0.0491 0.9933 0.0039
-8.000 -0.3447 0.07383 0.07178 -0.0545 0.9849 0.0039
-7.750 -0.3322 0.06723 0.06519 -0.0615 0.9753 0.0039
-7.500 -0.3161 0.05851 0.05640 -0.0746 0.9627 0.0039
-7.250 -0.2911 0.04898 0.04662 -0.0932 0.9466 0.0039
-7.000 -0.2750 0.04347 0.04078 -0.1006 0.9302 0.0039
-6.750 -0.2619 0.03950 0.03648 -0.1034 0.9145 0.0039
-6.500 -0.2484 0.03613 0.03278 -0.1044 0.9008 0.0039
-6.000 -0.2171 0.03010 0.02603 -0.1043 0.8770 0.0039
-5.750 -0.1995 0.02707 0.02265 -0.1038 0.8668 0.0040
-5.250 -0.1625 0.02084 0.01581 -0.1029 0.8485 0.0031
-5.000 -0.1392 0.01871 0.01333 -0.1019 0.8399 0.0029
-4.750 -0.1146 0.01696 0.01127 -0.1010 0.8323 0.0029
-4.500 -0.0890 0.01574 0.00977 -0.1002 0.8246 0.0044
-4.250 -0.0639 0.01482 0.00872 -0.0998 0.8179 0.0054
-4.000 -0.0386 0.01335 0.00708 -0.0989 0.8108 0.0047
-3.750 -0.0137 0.01224 0.00583 -0.0980 0.8043 0.0044
-3.500 0.0111 0.01136 0.00485 -0.0974 0.7972 0.0043
-3.250 0.0362 0.01063 0.00398 -0.0969 0.7909 0.0045
-3.000 0.0620 0.01003 0.00326 -0.0965 0.7840 0.0050
-2.750 0.0886 0.00969 0.00277 -0.0963 0.7779 0.0066
-2.500 0.1152 0.00923 0.00214 -0.0960 0.7712 0.0091
-2.250 0.1423 0.00903 0.00176 -0.0958 0.7650 0.0156
-2.000 0.1653 0.00788 0.00140 -0.0956 0.7584 0.2668
-1.750 0.1925 0.00787 0.00138 -0.0956 0.7518 0.3033
-1.500 0.2198 0.00788 0.00138 -0.0955 0.7453 0.3196
-1.250 0.2471 0.00788 0.00132 -0.0955 0.7385 0.3238
-1.000 0.2743 0.00787 0.00125 -0.0955 0.7317 0.3273
-0.750 0.3013 0.00789 0.00120 -0.0954 0.7227 0.3306
-0.500 0.3281 0.00789 0.00117 -0.0952 0.7121 0.3337
-0.250 0.3549 0.00790 0.00116 -0.0951 0.7026 0.3370
0.000 0.3818 0.00792 0.00116 -0.0950 0.6939 0.3416
0.250 0.4089 0.00794 0.00118 -0.0950 0.6852 0.3457
0.500 0.4356 0.00795 0.00121 -0.0949 0.6766 0.3492
0.750 0.4624 0.00798 0.00126 -0.0948 0.6671 0.3528
1.000 0.4879 0.00806 0.00130 -0.0943 0.6442 0.3575
1.250 0.5106 0.00828 0.00135 -0.0934 0.5972 0.3611
1.500 0.5274 0.00892 0.00152 -0.0913 0.4937 0.3646
1.750 0.5270 0.01137 0.00242 -0.0869 0.1294 0.3674
2.000 0.5477 0.01206 0.00285 -0.0857 0.0127 0.3712
2.250 0.5728 0.01228 0.00321 -0.0852 0.0091 0.3751
2.500 0.5965 0.01264 0.00372 -0.0844 0.0060 0.3791
2.750 0.6194 0.01309 0.00430 -0.0835 0.0050 0.3835
3.250 0.6606 0.01437 0.00578 -0.0807 0.0048 0.3924
3.500 0.6787 0.01520 0.00671 -0.0788 0.0047 0.3974
3.750 0.6985 0.01587 0.00747 -0.0773 0.0030 0.4031
4.000 0.7163 0.01682 0.00854 -0.0753 0.0028 0.4093
4.250 0.7356 0.01794 0.00975 -0.0736 0.0027 0.4172
4.500 0.7586 0.01936 0.01126 -0.0723 0.0027 0.4275
4.750 0.7872 0.02117 0.01320 -0.0717 0.0032 0.4430
5.250 0.8218 0.01099 0.00440 -0.0679 0.0046 0.7191
5.750 0.9030 0.03092 0.02468 -0.0719 0.0041 1.0000
6.250 0.9415 0.03544 0.02970 -0.0682 0.0041 1.0000
6.500 0.9586 0.03773 0.03224 -0.0661 0.0041 1.0000
6.750 0.9743 0.03995 0.03473 -0.0637 0.0040 1.0000
7.000 0.9893 0.04207 0.03712 -0.0612 0.0040 1.0000
7.250 1.0072 0.04354 0.03889 -0.0583 0.0037 1.0000
7.500 1.0209 0.04608 0.04170 -0.0556 0.0035 1.0000
7.750 1.0305 0.04897 0.04482 -0.0529 0.0034 1.0000
8.000 1.0374 0.05205 0.04813 -0.0501 0.0032 1.0000
8.250 1.0416 0.05517 0.05149 -0.0472 0.0031 1.0000
8.500 1.0425 0.05834 0.05487 -0.0442 0.0031 1.0000
8.750 1.0400 0.06156 0.05827 -0.0412 0.0030 1.0000
9.000 1.0343 0.06468 0.06157 -0.0381 0.0030 1.0000
9.250 1.0225 0.06747 0.06450 -0.0343 0.0029 1.0000
9.500 1.0079 0.07021 0.06737 -0.0309 0.0030 1.0000
9.750 0.9915 0.07328 0.07056 -0.0284 0.0030 1.0000
10.000 0.9740 0.07675 0.07415 -0.0269 0.0030 1.0000
10.250 0.9555 0.08076 0.07828 -0.0265 0.0030 1.0000
10.500 0.9370 0.08529 0.08291 -0.0272 0.0030 1.0000
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Polar data table (+)
Polar graphs
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