GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Reynolds number: 100,000 Max Cl/Cd: 57.97 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe116-il-100000.txt Download as CSV file: xf-goe116-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3614 0.09661 0.09216 -0.0336 1.0000 0.1121
-8.000 -0.3902 0.09626 0.09209 -0.0409 1.0000 0.1146
-7.750 -0.3940 0.09279 0.08876 -0.0427 1.0000 0.1150
-7.000 -0.3538 0.06332 0.05976 -0.0466 0.9827 0.0624
-6.750 -0.4387 0.07194 0.06816 -0.0454 0.9948 0.0646
-6.500 -0.4147 0.05528 0.05120 -0.0634 0.9860 0.0523
-6.250 -0.3874 0.03907 0.03407 -0.0783 0.9792 0.0468
-6.000 -0.3510 0.03069 0.02420 -0.0849 0.9733 0.0436
-5.750 -0.3085 0.02743 0.02028 -0.0887 0.9691 0.0432
-5.500 -0.2742 0.02526 0.01786 -0.0908 0.9618 0.0456
-5.250 -0.2323 0.02357 0.01582 -0.0939 0.9570 0.0503
-5.000 -0.1945 0.02226 0.01420 -0.0960 0.9506 0.0531
-4.750 -0.1542 0.02084 0.01263 -0.0987 0.9450 0.0610
-4.500 -0.1096 0.02096 0.01303 -0.1016 0.9398 0.1349
-4.250 -0.0759 0.02371 0.01556 -0.1025 0.9307 0.1832
-4.000 -0.0408 0.02415 0.01595 -0.1041 0.9247 0.2008
-3.750 -0.0090 0.02462 0.01625 -0.1053 0.9173 0.2234
-3.500 0.0269 0.02432 0.01579 -0.1071 0.9123 0.2379
-3.250 0.0526 0.02415 0.01577 -0.1073 0.9044 0.2570
-3.000 0.0903 0.02367 0.01487 -0.1093 0.9000 0.2654
-2.750 0.1159 0.02313 0.01421 -0.1094 0.8916 0.2674
-2.500 0.1502 0.02252 0.01346 -0.1107 0.8869 0.2704
-2.250 0.1763 0.02230 0.01310 -0.1107 0.8791 0.2739
-2.000 0.2087 0.02191 0.01250 -0.1115 0.8738 0.2762
-1.750 0.2355 0.02177 0.01222 -0.1116 0.8668 0.2779
-1.500 0.2655 0.02150 0.01183 -0.1120 0.8610 0.2799
-1.250 0.2929 0.02130 0.01162 -0.1122 0.8548 0.2828
-1.000 0.3203 0.02118 0.01148 -0.1122 0.8483 0.2871
-0.750 0.3501 0.02103 0.01125 -0.1125 0.8435 0.2916
-0.500 0.3744 0.02110 0.01136 -0.1122 0.8359 0.2950
-0.250 0.4040 0.02087 0.01118 -0.1123 0.8313 0.2995
0.000 0.4275 0.02109 0.01145 -0.1121 0.8238 0.3043
0.250 0.4557 0.02098 0.01140 -0.1120 0.8187 0.3104
0.500 0.4799 0.02117 0.01168 -0.1116 0.8121 0.3180
0.750 0.5066 0.02122 0.01183 -0.1115 0.8062 0.3286
1.000 0.5347 0.02120 0.01195 -0.1115 0.8015 0.3467
1.250 0.5581 0.02141 0.01246 -0.1114 0.7940 0.3827
1.500 0.5866 0.02000 0.01253 -0.1106 0.7900 1.0000
1.750 0.6091 0.02073 0.01316 -0.1103 0.7824 1.0000
2.000 0.6367 0.02105 0.01340 -0.1101 0.7773 1.0000
2.250 0.6604 0.02169 0.01405 -0.1098 0.7707 1.0000
2.500 0.6856 0.02219 0.01455 -0.1096 0.7646 1.0000
2.750 0.7152 0.02238 0.01475 -0.1095 0.7609 1.0000
3.000 0.7337 0.02343 0.01588 -0.1091 0.7519 1.0000
3.250 0.7628 0.02365 0.01619 -0.1089 0.7479 1.0000
3.500 0.7811 0.02478 0.01744 -0.1085 0.7393 1.0000
3.750 0.8111 0.02480 0.01754 -0.1081 0.7343 1.0000
4.000 0.8310 0.02558 0.01846 -0.1073 0.7243 1.0000
4.250 0.8605 0.02477 0.01778 -0.1054 0.7114 1.0000
4.500 0.8952 0.02172 0.01471 -0.1011 0.6853 1.0000
4.750 0.9241 0.01943 0.01238 -0.0972 0.6549 1.0000
5.000 0.9489 0.01740 0.01027 -0.0930 0.6093 1.0000
5.250 0.9588 0.01654 0.00881 -0.0872 0.4494 1.0000
5.750 0.9500 0.02259 0.01221 -0.0782 0.0650 1.0000
6.000 0.9639 0.02392 0.01372 -0.0760 0.0576 1.0000
6.250 0.9750 0.02538 0.01531 -0.0734 0.0542 1.0000
6.500 0.9872 0.02667 0.01673 -0.0710 0.0503 1.0000
6.750 0.9967 0.02818 0.01824 -0.0684 0.0465 1.0000
7.000 1.0074 0.03004 0.02005 -0.0658 0.0449 1.0000
7.250 1.0352 0.03246 0.02231 -0.0651 0.0441 1.0000
7.500 1.0753 0.03502 0.02483 -0.0658 0.0442 1.0000
7.750 1.1082 0.03685 0.02689 -0.0655 0.0452 1.0000
8.000 1.1414 0.03915 0.02953 -0.0649 0.0472 1.0000
8.250 1.1682 0.04202 0.03273 -0.0640 0.0473 1.0000
8.500 1.1913 0.04539 0.03663 -0.0623 0.0500 1.0000
8.750 1.2256 0.05050 0.04190 -0.0623 0.0569 1.0000
13.750 0.9494 0.17525 0.17082 -0.0853 0.1274 1.0000
14.000 0.9614 0.17837 0.17396 -0.0845 0.1204 1.0000
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Polar data table (+)
Polar graphs
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