GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 114 (MVA MK.1) AIRFOIL (goe114-il) Reynolds number: 200,000 Max Cl/Cd: 50.81 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe114-il-200000-n5.txt Download as CSV file: xf-goe114-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3634 0.08750 0.08424 -0.0472 1.0000 0.0125
-8.250 -0.3673 0.08382 0.08064 -0.0479 1.0000 0.0125
-8.000 -0.3745 0.08059 0.07749 -0.0478 1.0000 0.0125
-7.750 -0.3791 0.07683 0.07377 -0.0494 0.9978 0.0125
-7.500 -0.3659 0.06943 0.06633 -0.0608 0.9864 0.0125
-7.250 -0.3459 0.06141 0.05812 -0.0755 0.9750 0.0125
-7.000 -0.3281 0.05527 0.05167 -0.0849 0.9661 0.0125
-6.750 -0.3094 0.05030 0.04634 -0.0909 0.9576 0.0125
-6.500 -0.2992 0.04255 0.03832 -0.0954 0.9481 0.0132
-6.250 -0.2778 0.03741 0.03295 -0.0987 0.9426 0.0139
-6.000 -0.2588 0.03372 0.02902 -0.1002 0.9338 0.0154
-5.750 -0.2333 0.03074 0.02560 -0.1019 0.9276 0.0181
-5.500 -0.2121 0.02773 0.02205 -0.1025 0.9192 0.0242
-5.250 -0.1887 0.02521 0.01909 -0.1032 0.9123 0.0334
-4.750 -0.1249 0.02148 0.01459 -0.1014 0.9001 0.0109
-4.500 -0.0990 0.01954 0.01238 -0.1008 0.8925 0.0099
-4.250 -0.0709 0.01798 0.01059 -0.1005 0.8863 0.0093
-4.000 -0.0449 0.01671 0.00916 -0.0998 0.8786 0.0090
-3.750 -0.0186 0.01557 0.00792 -0.0992 0.8719 0.0090
-3.500 0.0065 0.01465 0.00691 -0.0987 0.8642 0.0094
-3.250 0.0328 0.01403 0.00617 -0.0984 0.8573 0.0118
-3.000 0.0591 0.01334 0.00526 -0.0980 0.8502 0.0128
-2.750 0.0857 0.01265 0.00420 -0.0976 0.8433 0.0156
-2.500 0.1130 0.01229 0.00360 -0.0974 0.8364 0.0222
-2.250 0.1364 0.01109 0.00334 -0.0972 0.8295 0.3022
-2.000 0.1638 0.01133 0.00348 -0.0970 0.8226 0.3454
-1.750 0.1908 0.01135 0.00338 -0.0969 0.8155 0.3565
-1.500 0.2181 0.01130 0.00322 -0.0968 0.8087 0.3614
-1.250 0.2450 0.01126 0.00311 -0.0967 0.8017 0.3661
-1.000 0.2722 0.01123 0.00298 -0.0966 0.7947 0.3715
-0.750 0.2991 0.01119 0.00291 -0.0965 0.7877 0.3764
-0.500 0.3261 0.01115 0.00285 -0.0964 0.7805 0.3812
-0.250 0.3529 0.01113 0.00281 -0.0962 0.7732 0.3861
0.000 0.3798 0.01109 0.00277 -0.0961 0.7661 0.3902
0.250 0.4064 0.01105 0.00278 -0.0960 0.7583 0.3942
0.500 0.4333 0.01104 0.00277 -0.0958 0.7511 0.3991
0.750 0.4597 0.01101 0.00284 -0.0956 0.7428 0.4039
1.000 0.4865 0.01099 0.00287 -0.0955 0.7356 0.4088
1.250 0.5127 0.01098 0.00296 -0.0952 0.7260 0.4142
1.500 0.5369 0.01092 0.00296 -0.0943 0.7010 0.4195
1.750 0.5569 0.01096 0.00279 -0.0923 0.6367 0.4255
2.000 0.5701 0.01157 0.00279 -0.0891 0.5103 0.4315
2.750 0.6033 0.01562 0.00512 -0.0807 0.0133 0.4570
3.250 0.6460 0.01644 0.00658 -0.0782 0.0099 0.5108
3.500 0.6605 0.01640 0.00749 -0.0755 0.0095 0.7863
4.000 0.7080 0.01864 0.01005 -0.0743 0.0095 1.0000
4.250 0.7258 0.01985 0.01131 -0.0723 0.0098 1.0000
4.500 0.7471 0.02138 0.01285 -0.0707 0.0106 1.0000
4.750 0.7725 0.02287 0.01439 -0.0698 0.0099 1.0000
5.000 0.7992 0.02475 0.01625 -0.0696 0.0081 1.0000
5.250 0.8318 0.02668 0.01838 -0.0691 0.0108 1.0000
6.750 0.9266 0.03181 0.02533 -0.0568 0.0132 1.0000
7.000 0.9389 0.03324 0.02713 -0.0539 0.0127 1.0000
7.250 0.9521 0.03458 0.02884 -0.0508 0.0117 1.0000
7.500 0.9610 0.03755 0.03211 -0.0481 0.0110 1.0000
7.750 0.9667 0.04089 0.03571 -0.0453 0.0105 1.0000
8.000 0.9689 0.04441 0.03949 -0.0424 0.0102 1.0000
8.250 0.9677 0.04801 0.04332 -0.0394 0.0099 1.0000
8.500 0.9625 0.05159 0.04711 -0.0363 0.0097 1.0000
8.750 0.9522 0.05491 0.05066 -0.0327 0.0095 1.0000
9.000 0.9370 0.05801 0.05393 -0.0290 0.0095 1.0000
9.250 0.9195 0.06131 0.05738 -0.0260 0.0094 1.0000
9.500 0.9002 0.06499 0.06122 -0.0238 0.0095 1.0000
9.750 0.8791 0.06912 0.06550 -0.0225 0.0095 1.0000
10.000 0.8569 0.07373 0.07027 -0.0220 0.0096 1.0000
10.250 0.8338 0.07884 0.07546 -0.0225 0.0097 1.0000
10.500 0.8102 0.08442 0.08117 -0.0239 0.0099 1.0000
10.750 0.7865 0.09042 0.08729 -0.0262 0.0102 1.0000
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Polar data table (+)
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