GOE 611 AIRFOIL (goe611-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 611 AIRFOIL (goe611-il) Reynolds number: 100,000 Max Cl/Cd: 52.71 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe611-il-100000.txt Download as CSV file: xf-goe611-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 611 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3201 0.12357 0.11939 -0.0313 1.0000 0.0553
-9.000 -0.3381 0.12329 0.11920 -0.0296 1.0000 0.0555
-8.750 -0.3563 0.12287 0.11887 -0.0279 1.0000 0.0556
-8.500 -0.3633 0.12116 0.11721 -0.0320 0.9958 0.0559
-8.250 -0.3377 0.11351 0.10956 -0.0326 0.9937 0.0571
-8.000 -0.3105 0.10850 0.10452 -0.0331 0.9902 0.0599
-7.750 -0.2940 0.10463 0.10064 -0.0376 0.9848 0.0631
-7.500 -0.2874 0.10140 0.09743 -0.0422 0.9763 0.0659
-7.250 -0.2771 0.09781 0.09379 -0.0566 0.9635 0.0686
-7.000 -0.2606 0.09239 0.08828 -0.0665 0.9550 0.0698
-6.750 -0.2444 0.08802 0.08400 -0.0610 0.9510 0.0723
-6.500 -0.2203 0.08394 0.07989 -0.0649 0.9455 0.0762
-6.250 -0.2041 0.08020 0.07607 -0.0709 0.9353 0.0811
-6.000 -0.1726 0.07433 0.06997 -0.0822 0.9293 0.0855
-5.750 -0.1627 0.07151 0.06723 -0.0800 0.9199 0.0884
-5.500 -0.1297 0.06954 0.06463 -0.0900 0.9097 0.0994
-5.250 -0.1126 0.06374 0.05918 -0.0887 0.9047 0.1031
-5.000 -0.0742 0.05954 0.05474 -0.0952 0.9006 0.1176
-4.750 -0.0546 0.05755 0.05245 -0.0970 0.8896 0.1318
-4.500 -0.0173 0.05336 0.04821 -0.1011 0.8863 0.1484
-4.000 0.0391 0.04787 0.04252 -0.1049 0.8724 0.1960
-2.500 0.2337 0.03312 0.02673 -0.1137 0.8302 0.2945
-2.250 0.3094 0.02990 0.02143 -0.1165 0.8267 0.1123
-2.000 0.3363 0.02869 0.02000 -0.1158 0.8169 0.1085
-1.750 0.3755 0.02718 0.01817 -0.1168 0.8115 0.1050
-1.500 0.4026 0.02657 0.01731 -0.1158 0.8014 0.1014
-1.250 0.4396 0.02553 0.01609 -0.1164 0.7957 0.1002
-1.000 0.4634 0.02491 0.01550 -0.1155 0.7851 0.1020
-0.750 0.4985 0.02388 0.01449 -0.1160 0.7795 0.1065
-0.500 0.5201 0.02367 0.01428 -0.1147 0.7684 0.1084
-0.250 0.5552 0.02290 0.01340 -0.1151 0.7632 0.1124
0.000 0.5766 0.02286 0.01333 -0.1138 0.7517 0.1176
0.250 0.6033 0.02266 0.01308 -0.1133 0.7429 0.1322
0.500 0.6419 0.02008 0.01277 -0.1144 0.7357 1.0000
0.750 0.6661 0.02034 0.01272 -0.1134 0.7261 1.0000
1.000 0.6974 0.02022 0.01231 -0.1134 0.7192 1.0000
1.250 0.7193 0.02056 0.01251 -0.1124 0.7087 1.0000
1.500 0.7527 0.02035 0.01208 -0.1128 0.7029 1.0000
1.750 0.7732 0.02076 0.01241 -0.1117 0.6920 1.0000
2.000 0.8002 0.02088 0.01241 -0.1114 0.6840 1.0000
2.250 0.8275 0.02097 0.01239 -0.1111 0.6756 1.0000
2.500 0.8515 0.02124 0.01259 -0.1105 0.6662 1.0000
2.750 0.8834 0.02106 0.01227 -0.1108 0.6589 1.0000
3.000 0.9053 0.02138 0.01256 -0.1098 0.6482 1.0000
3.250 0.9332 0.02138 0.01247 -0.1095 0.6391 1.0000
3.500 0.9618 0.02134 0.01234 -0.1094 0.6299 1.0000
3.750 0.9847 0.02161 0.01258 -0.1085 0.6192 1.0000
4.000 1.0138 0.02162 0.01249 -0.1085 0.6107 1.0000
4.250 1.0388 0.02184 0.01270 -0.1080 0.6010 1.0000
4.500 1.0624 0.02213 0.01299 -0.1073 0.5912 1.0000
4.750 1.0941 0.02208 0.01280 -0.1078 0.5831 1.0000
5.000 1.1141 0.02252 0.01330 -0.1066 0.5723 1.0000
5.250 1.1391 0.02281 0.01360 -0.1061 0.5634 1.0000
5.500 1.1661 0.02304 0.01380 -0.1060 0.5549 1.0000
5.750 1.1874 0.02353 0.01436 -0.1051 0.5457 1.0000
6.000 1.2177 0.02367 0.01444 -0.1055 0.5383 1.0000
6.250 1.2359 0.02425 0.01515 -0.1041 0.5283 1.0000
6.500 1.2624 0.02452 0.01541 -0.1039 0.5200 1.0000
6.750 1.2848 0.02488 0.01582 -0.1031 0.5105 1.0000
7.000 1.3058 0.02536 0.01640 -0.1022 0.5014 1.0000
7.250 1.3339 0.02556 0.01658 -0.1023 0.4934 1.0000
7.500 1.3504 0.02611 0.01728 -0.1006 0.4831 1.0000
7.750 1.3740 0.02637 0.01759 -0.0999 0.4737 1.0000
8.000 1.3966 0.02666 0.01793 -0.0991 0.4642 1.0000
8.250 1.4131 0.02720 0.01862 -0.0975 0.4545 1.0000
8.500 1.4380 0.02742 0.01885 -0.0970 0.4454 1.0000
8.750 1.4555 0.02764 0.01917 -0.0953 0.4336 1.0000
9.000 1.4680 0.02785 0.01947 -0.0928 0.4200 1.0000
9.250 1.4788 0.02806 0.01975 -0.0900 0.4057 1.0000
9.500 1.4871 0.02838 0.02014 -0.0868 0.3914 1.0000
9.750 1.4926 0.02881 0.02064 -0.0833 0.3771 1.0000
10.000 1.4926 0.02935 0.02126 -0.0790 0.3628 1.0000
10.250 1.4925 0.03011 0.02207 -0.0750 0.3481 1.0000
10.500 1.4928 0.03105 0.02308 -0.0713 0.3334 1.0000
10.750 1.4927 0.03220 0.02428 -0.0680 0.3182 1.0000
11.000 1.4913 0.03357 0.02568 -0.0649 0.3024 1.0000
11.250 1.4887 0.03519 0.02730 -0.0619 0.2862 1.0000
11.500 1.4842 0.03711 0.02922 -0.0592 0.2695 1.0000
11.750 1.4785 0.03934 0.03149 -0.0568 0.2526 1.0000
12.000 1.4743 0.04165 0.03381 -0.0547 0.2381 1.0000
12.250 1.4716 0.04399 0.03614 -0.0530 0.2262 1.0000
12.500 1.4689 0.04643 0.03863 -0.0514 0.2154 1.0000
12.750 1.4668 0.04897 0.04125 -0.0501 0.2052 1.0000
13.000 1.4639 0.05164 0.04398 -0.0490 0.1963 1.0000
13.250 1.4570 0.05480 0.04714 -0.0480 0.1865 1.0000
13.500 1.4519 0.05804 0.05050 -0.0473 0.1768 1.0000
13.750 1.4473 0.06131 0.05385 -0.0468 0.1689 1.0000
14.000 1.4428 0.06466 0.05730 -0.0464 0.1621 1.0000
14.250 1.4361 0.06845 0.06120 -0.0464 0.1540 1.0000
14.500 1.4281 0.07245 0.06523 -0.0464 0.1472 1.0000
14.750 1.4201 0.07671 0.06962 -0.0467 0.1391 1.0000
15.000 1.4089 0.08137 0.07430 -0.0472 0.1315 1.0000
15.250 1.3975 0.08630 0.07933 -0.0479 0.1231 1.0000
15.500 1.3868 0.09127 0.08442 -0.0488 0.1148 1.0000
15.750 1.3723 0.09685 0.09001 -0.0500 0.1064 1.0000
16.000 1.3617 0.10224 0.09563 -0.0515 0.0946 1.0000
16.250 1.3500 0.10788 0.10135 -0.0531 0.0650 1.0000
16.500 1.3308 0.11458 0.10788 -0.0553 0.0564 1.0000
16.750 1.3159 0.12066 0.11391 -0.0573 0.0512 1.0000
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