GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Reynolds number: 50,000 Max Cl/Cd: 15.26 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe190-il-50000.txt Download as CSV file: xf-goe190-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 190 (MVA MK.18) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2630 0.11483 0.10795 -0.0235 1.0000 0.2518
-8.250 -0.2776 0.11501 0.10825 -0.0228 1.0000 0.2574
-8.000 -0.2793 0.11245 0.10578 -0.0219 1.0000 0.2598
-7.750 -0.2634 0.10836 0.10169 -0.0205 1.0000 0.2663
-7.500 -0.2767 0.10812 0.10158 -0.0190 1.0000 0.2725
-7.250 -0.3102 0.11018 0.10386 -0.0164 1.0000 0.2741
-7.000 -0.2747 0.10289 0.09650 -0.0160 1.0000 0.2793
-6.750 -0.2781 0.10115 0.09486 -0.0141 1.0000 0.2839
-6.500 -0.2993 0.10134 0.09521 -0.0111 1.0000 0.2882
-6.250 -0.3373 0.10329 0.09738 -0.0074 1.0000 0.2900
-6.000 -0.3371 0.10009 0.09427 -0.0054 1.0000 0.2914
-5.750 -0.3340 0.09714 0.09137 -0.0032 1.0000 0.2936
-5.500 -0.3381 0.09530 0.08960 -0.0009 1.0000 0.2966
-5.250 -0.3478 0.09410 0.08849 0.0011 1.0000 0.3006
-5.000 -0.3642 0.09359 0.08810 0.0014 1.0000 0.3047
-4.750 -0.3780 0.09300 0.08759 -0.0014 1.0000 0.3065
-4.250 -0.3009 0.05234 0.04598 -0.0626 1.0000 0.1668
-4.000 -0.2334 0.03920 0.03148 -0.0835 1.0000 0.1679
-3.750 -0.2220 0.03955 0.03208 -0.0812 1.0000 0.1723
-3.500 -0.1951 0.03715 0.02930 -0.0841 1.0000 0.1780
-3.250 -0.1695 0.03524 0.02698 -0.0863 1.0000 0.1849
-3.000 -0.1190 0.03566 0.02745 -0.0910 0.9864 0.2022
-2.750 -0.0693 0.03591 0.02765 -0.0955 0.9725 0.2257
-2.500 -0.0282 0.03779 0.02977 -0.0973 0.9573 0.2607
-2.250 0.0041 0.04068 0.03295 -0.0960 0.9418 0.3119
-2.000 0.0299 0.04320 0.03551 -0.0934 0.9270 0.3752
-1.750 0.0506 0.04443 0.03677 -0.0907 0.9136 0.4126
-1.500 0.0734 0.04498 0.03727 -0.0891 0.9009 0.4486
-1.250 0.0970 0.04525 0.03749 -0.0878 0.8892 0.4900
-1.000 0.1259 0.04508 0.03726 -0.0871 0.8790 0.5350
-0.750 0.1434 0.04456 0.03672 -0.0854 0.8670 0.5597
-0.500 0.1753 0.04420 0.03618 -0.0876 0.8553 0.5708
-0.250 0.2153 0.04387 0.03562 -0.0911 0.8444 0.5780
0.000 0.2622 0.04342 0.03495 -0.0955 0.8342 0.5846
0.250 0.2869 0.04346 0.03487 -0.0964 0.8221 0.5897
0.500 0.3217 0.04352 0.03476 -0.0989 0.8113 0.5949
0.750 0.3689 0.04309 0.03417 -0.1026 0.8018 0.6014
1.000 0.3887 0.04358 0.03458 -0.1027 0.7896 0.6052
1.250 0.4228 0.04382 0.03469 -0.1048 0.7792 0.6104
1.500 0.4656 0.04372 0.03446 -0.1077 0.7694 0.6165
1.750 0.4846 0.04457 0.03524 -0.1078 0.7575 0.6206
2.000 0.5351 0.04429 0.03482 -0.1114 0.7491 0.6273
2.250 0.5547 0.04529 0.03575 -0.1116 0.7370 0.6324
2.500 0.5755 0.04629 0.03671 -0.1118 0.7259 0.6379
2.750 0.6274 0.04594 0.03626 -0.1152 0.7175 0.6456
3.000 0.6339 0.04783 0.03814 -0.1142 0.7049 0.6497
3.250 0.6722 0.04814 0.03841 -0.1160 0.6961 0.6589
3.500 0.6935 0.04937 0.03963 -0.1163 0.6851 0.6663
3.750 0.7023 0.05140 0.04168 -0.1157 0.6740 0.6723
4.000 0.7510 0.05114 0.04144 -0.1181 0.6662 0.6836
4.250 0.7423 0.05434 0.04467 -0.1163 0.6543 0.6887
4.500 0.8075 0.05291 0.04335 -0.1195 0.6479 0.7089
4.750 0.7800 0.05757 0.04804 -0.1169 0.6359 0.7123
5.000 0.7985 0.05925 0.04987 -0.1171 0.6270 0.7271
5.250 0.8171 0.06084 0.05166 -0.1173 0.6179 0.7460
5.500 0.8185 0.06367 0.05471 -0.1167 0.6091 0.7702
5.750 0.8432 0.06429 0.05550 -0.1163 0.6002 1.0000
6.000 0.8306 0.06845 0.05964 -0.1154 0.5908 1.0000
6.250 0.8796 0.06845 0.05961 -0.1168 0.5808 1.0000
6.500 0.8619 0.07294 0.06410 -0.1157 0.5708 1.0000
6.750 0.8769 0.07522 0.06636 -0.1156 0.5607 1.0000
7.000 0.9201 0.07535 0.06647 -0.1161 0.5499 1.0000
7.250 0.8910 0.08096 0.07209 -0.1151 0.5405 1.0000
7.500 0.9250 0.08185 0.07299 -0.1151 0.5299 1.0000
7.750 0.9132 0.08623 0.07740 -0.1147 0.5202 1.0000
8.000 0.9227 0.08910 0.08029 -0.1144 0.5104 1.0000
8.250 0.9455 0.09085 0.08206 -0.1141 0.4999 1.0000
8.500 0.9268 0.09619 0.08742 -0.1140 0.4916 1.0000
8.750 0.9644 0.09666 0.08794 -0.1133 0.4794 1.0000
9.000 0.9321 0.10357 0.09487 -0.1141 0.4749 1.0000
9.250 0.9674 0.10435 0.09570 -0.1132 0.4626 1.0000
9.500 0.9391 0.11103 0.10242 -0.1144 0.4592 1.0000
9.750 0.9291 0.11653 0.10797 -0.1156 0.4586 1.0000
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Polar data table (+)
Polar graphs
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