GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 190 (MVA MK.18) AIRFOIL (goe190-il) Reynolds number: 50,000 Max Cl/Cd: 37.2 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe190-il-50000-n5.txt Download as CSV file: xf-goe190-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3179 0.10645 0.09940 -0.0376 1.0000 0.0797
-8.750 -0.3224 0.10345 0.09649 -0.0374 1.0000 0.0797
-8.500 -0.3296 0.10043 0.09355 -0.0372 1.0000 0.0801
-8.250 -0.3380 0.09748 0.09070 -0.0367 1.0000 0.0802
-8.000 -0.3486 0.09468 0.08801 -0.0359 1.0000 0.0803
-7.750 -0.3602 0.09212 0.08556 -0.0346 1.0000 0.0800
-7.500 -0.3726 0.08934 0.08290 -0.0335 1.0000 0.0798
-7.250 -0.3828 0.08616 0.07982 -0.0333 1.0000 0.0794
-7.000 -0.3932 0.08257 0.07633 -0.0339 1.0000 0.0790
-6.750 -0.4035 0.07822 0.07207 -0.0356 1.0000 0.0788
-6.500 -0.3902 0.06611 0.05982 -0.0524 0.9914 0.0796
-6.250 -0.3426 0.04635 0.03882 -0.0868 0.9831 0.0813
-6.000 -0.3014 0.04117 0.03290 -0.0955 0.9758 0.0828
-5.750 -0.2670 0.03921 0.03085 -0.0985 0.9684 0.0861
-5.500 -0.2293 0.03709 0.02842 -0.1024 0.9607 0.0901
-5.250 -0.1934 0.03513 0.02604 -0.1053 0.9522 0.0930
-5.000 -0.1544 0.03354 0.02408 -0.1083 0.9447 0.0963
-4.750 -0.1247 0.03253 0.02315 -0.1093 0.9344 0.1010
-4.500 -0.0882 0.03149 0.02192 -0.1116 0.9260 0.1069
-4.250 -0.0554 0.03053 0.02088 -0.1129 0.9155 0.1120
-4.000 -0.0236 0.02967 0.02000 -0.1142 0.9044 0.1202
-3.750 0.0123 0.02872 0.01908 -0.1164 0.8947 0.1340
-3.500 0.0485 0.02781 0.01835 -0.1184 0.8848 0.1570
-3.250 0.0775 0.02809 0.01927 -0.1181 0.8724 0.2097
-3.000 0.1104 0.02870 0.01969 -0.1183 0.8603 0.2698
-2.750 0.1438 0.02941 0.02021 -0.1184 0.8492 0.3033
-2.500 0.1786 0.03020 0.02092 -0.1183 0.8401 0.3306
-2.250 0.2069 0.03075 0.02141 -0.1174 0.8279 0.3508
-2.000 0.2382 0.03117 0.02174 -0.1170 0.8175 0.3739
-1.750 0.2759 0.03106 0.02151 -0.1179 0.8094 0.3916
-1.500 0.3086 0.03066 0.02096 -0.1186 0.7978 0.3995
-1.250 0.3508 0.03000 0.02006 -0.1211 0.7896 0.4073
-1.000 0.3863 0.02952 0.01937 -0.1226 0.7781 0.4136
-0.750 0.4205 0.02913 0.01884 -0.1236 0.7670 0.4191
-0.500 0.4621 0.02858 0.01803 -0.1260 0.7578 0.4258
-0.250 0.4930 0.02835 0.01767 -0.1265 0.7450 0.4307
0.000 0.5267 0.02809 0.01728 -0.1274 0.7338 0.4360
0.250 0.5636 0.02780 0.01678 -0.1289 0.7232 0.4419
0.500 0.5918 0.02775 0.01661 -0.1291 0.7104 0.4463
0.750 0.6223 0.02766 0.01644 -0.1294 0.6991 0.4512
1.000 0.6560 0.02757 0.01619 -0.1303 0.6886 0.4573
1.250 0.6821 0.02770 0.01623 -0.1302 0.6764 0.4620
1.500 0.7115 0.02773 0.01619 -0.1304 0.6659 0.4664
1.750 0.7420 0.02778 0.01613 -0.1308 0.6558 0.4723
2.000 0.7673 0.02800 0.01629 -0.1305 0.6447 0.4778
2.250 0.7980 0.02803 0.01626 -0.1308 0.6357 0.4834
2.500 0.8241 0.02825 0.01644 -0.1306 0.6252 0.4890
2.750 0.8510 0.02845 0.01661 -0.1304 0.6155 0.4945
3.000 0.8812 0.02853 0.01664 -0.1307 0.6068 0.5010
3.250 0.9059 0.02887 0.01699 -0.1303 0.5968 0.5078
3.500 0.9388 0.02886 0.01694 -0.1309 0.5891 0.5146
3.750 0.9614 0.02931 0.01743 -0.1302 0.5789 0.5215
4.000 0.9921 0.02941 0.01754 -0.1305 0.5711 0.5288
4.250 1.0159 0.02985 0.01802 -0.1299 0.5615 0.5371
4.500 1.0448 0.03005 0.01826 -0.1300 0.5535 0.5456
4.750 1.0689 0.03051 0.01881 -0.1294 0.5443 0.5546
5.000 1.0968 0.03080 0.01916 -0.1293 0.5363 0.5644
5.250 1.1197 0.03129 0.01978 -0.1286 0.5271 0.5748
5.500 1.1471 0.03164 0.02023 -0.1285 0.5193 0.5876
5.750 1.1680 0.03222 0.02099 -0.1275 0.5100 0.6009
6.000 1.1942 0.03257 0.02148 -0.1271 0.5018 0.6181
6.250 1.2134 0.03307 0.02228 -0.1259 0.4919 0.6404
6.750 1.2530 0.03368 0.02337 -0.1229 0.4726 1.0000
7.000 1.2683 0.03456 0.02433 -0.1211 0.4623 1.0000
7.250 1.2958 0.03490 0.02464 -0.1207 0.4536 1.0000
7.500 1.3046 0.03608 0.02598 -0.1182 0.4434 1.0000
7.750 1.3312 0.03643 0.02632 -0.1176 0.4354 1.0000
8.000 1.3381 0.03767 0.02773 -0.1149 0.4254 1.0000
8.250 1.3581 0.03828 0.02842 -0.1135 0.4171 1.0000
8.500 1.3691 0.03928 0.02956 -0.1112 0.4078 1.0000
8.750 1.3816 0.04021 0.03059 -0.1091 0.3989 1.0000
9.000 1.3986 0.04084 0.03131 -0.1074 0.3901 1.0000
9.250 1.4018 0.04217 0.03281 -0.1042 0.3809 1.0000
9.500 1.4272 0.04228 0.03293 -0.1033 0.3723 1.0000
9.750 1.4186 0.04417 0.03502 -0.0990 0.3627 1.0000
10.000 1.4350 0.04465 0.03554 -0.0972 0.3534 1.0000
10.250 1.4375 0.04587 0.03687 -0.0941 0.3431 1.0000
10.500 1.4350 0.04750 0.03862 -0.0909 0.3327 1.0000
10.750 1.4502 0.04788 0.03902 -0.0890 0.3220 1.0000
11.000 1.4413 0.05016 0.04146 -0.0858 0.3118 1.0000
11.250 1.4391 0.05213 0.04352 -0.0834 0.3018 1.0000
11.500 1.4553 0.05255 0.04395 -0.0818 0.2916 1.0000
11.750 1.4296 0.05701 0.04863 -0.0794 0.2825 1.0000
12.000 1.4369 0.05842 0.05009 -0.0778 0.2731 1.0000
12.250 1.4214 0.06244 0.05428 -0.0766 0.2639 1.0000
12.500 1.4131 0.06590 0.05785 -0.0757 0.2549 1.0000
12.750 1.4210 0.06732 0.05933 -0.0745 0.2453 1.0000
13.000 1.3888 0.07444 0.06666 -0.0752 0.2370 1.0000
13.250 1.4003 0.07545 0.06769 -0.0741 0.2279 1.0000
13.500 1.3713 0.08274 0.07517 -0.0755 0.2195 1.0000
13.750 1.3675 0.08630 0.07880 -0.0756 0.2109 1.0000
14.000 1.3696 0.08888 0.08144 -0.0753 0.2021 1.0000
14.250 1.3393 0.09740 0.09011 -0.0780 0.1944 1.0000
14.500 1.3744 0.09406 0.08669 -0.0749 0.1852 1.0000
14.750 1.3151 0.10851 0.10140 -0.0810 0.1785 1.0000
15.000 1.3583 0.10335 0.09615 -0.0769 0.1700 1.0000
15.250 1.2823 0.12222 0.11526 -0.0861 0.1637 1.0000
15.500 1.3452 0.11243 0.10539 -0.0793 0.1553 1.0000
15.750 1.2390 0.13966 0.13280 -0.0941 0.1492 1.0000
16.000 1.2822 0.13306 0.12629 -0.0891 0.1432 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 190 (MVA MK.18) AIRFOIL (goe190-il)