GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.11 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe240-il-1000000.txt Download as CSV file: xf-goe240-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 240 (KOLLER) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3183 0.09666 0.09509 -0.0258 1.0000 0.0119
-8.250 -0.3165 0.09441 0.09286 -0.0257 1.0000 0.0122
-8.000 -0.3108 0.09165 0.09013 -0.0268 0.9988 0.0126
-7.750 -0.2928 0.08728 0.08576 -0.0325 0.9953 0.0138
-7.500 -0.2718 0.08180 0.08027 -0.0427 0.9882 0.0142
-7.250 -0.2477 0.07669 0.07514 -0.0508 0.9829 0.0142
-7.000 -0.2287 0.07220 0.07064 -0.0564 0.9733 0.0142
-6.750 -0.2179 0.06779 0.06621 -0.0589 0.9630 0.0146
-6.500 -0.2028 0.06540 0.06380 -0.0604 0.9506 0.0148
-6.250 -0.1860 0.06282 0.06117 -0.0626 0.9335 0.0151
-6.000 -0.1677 0.06008 0.05834 -0.0651 0.8998 0.0158
-5.750 -0.1331 0.05482 0.05278 -0.0738 0.8530 0.0180
-5.500 -0.1054 0.05017 0.04794 -0.0789 0.8329 0.0181
-5.250 -0.0764 0.04537 0.04296 -0.0836 0.8214 0.0182
-4.750 -0.0303 0.03902 0.03640 -0.0885 0.8057 0.0193
-4.500 -0.0040 0.03718 0.03446 -0.0901 0.7990 0.0207
-4.250 0.0361 0.03265 0.02967 -0.0937 0.7932 0.0230
-4.000 0.0668 0.02790 0.02464 -0.0958 0.7872 0.0231
-2.250 0.2586 0.01350 0.00872 -0.0996 0.7457 0.0334
-2.000 0.2867 0.01281 0.00788 -0.0996 0.7395 0.0354
-1.750 0.3150 0.01179 0.00662 -0.0996 0.7342 0.0400
-1.500 0.3429 0.01129 0.00608 -0.0997 0.7277 0.0417
-1.250 0.3722 0.00935 0.00373 -0.0991 0.7210 0.0310
-1.000 0.4003 0.00887 0.00318 -0.0990 0.7119 0.0309
-0.750 0.4282 0.00847 0.00272 -0.0989 0.7028 0.0311
-0.500 0.4560 0.00817 0.00236 -0.0988 0.6926 0.0315
-0.250 0.4840 0.00792 0.00208 -0.0987 0.6812 0.0317
0.000 0.5118 0.00775 0.00185 -0.0986 0.6660 0.0319
0.250 0.5394 0.00763 0.00166 -0.0985 0.6468 0.0321
0.500 0.5668 0.00757 0.00150 -0.0983 0.6209 0.0328
0.750 0.5932 0.00766 0.00140 -0.0980 0.5775 0.0333
1.000 0.6198 0.00778 0.00135 -0.0977 0.5455 0.0339
1.250 0.6470 0.00783 0.00132 -0.0976 0.5252 0.0350
1.500 0.6744 0.00790 0.00131 -0.0974 0.5084 0.0365
1.750 0.7018 0.00797 0.00132 -0.0973 0.4932 0.0378
2.000 0.7292 0.00806 0.00135 -0.0972 0.4766 0.0406
2.250 0.7565 0.00811 0.00143 -0.0971 0.4600 0.0705
2.500 0.7837 0.00820 0.00152 -0.0970 0.4412 0.0944
2.750 0.8106 0.00813 0.00166 -0.0970 0.4163 0.2421
3.000 0.8332 0.00688 0.00191 -0.0964 0.3877 1.0000
3.250 0.8592 0.00719 0.00205 -0.0961 0.3564 1.0000
3.500 0.8852 0.00749 0.00220 -0.0959 0.3303 1.0000
3.750 0.9111 0.00779 0.00237 -0.0956 0.3059 1.0000
4.000 0.9374 0.00803 0.00252 -0.0954 0.2878 1.0000
4.250 0.9636 0.00829 0.00269 -0.0952 0.2689 1.0000
4.500 0.9893 0.00859 0.00287 -0.0949 0.2442 1.0000
4.750 1.0126 0.00920 0.00318 -0.0943 0.1911 1.0000
5.000 1.0369 0.00967 0.00347 -0.0938 0.1616 1.0000
5.250 1.0622 0.00999 0.00373 -0.0935 0.1467 1.0000
5.500 1.0875 0.01031 0.00397 -0.0931 0.1337 1.0000
5.750 1.1128 0.01061 0.00421 -0.0928 0.1226 1.0000
6.000 1.1379 0.01093 0.00447 -0.0924 0.1113 1.0000
6.250 1.1620 0.01136 0.00477 -0.0919 0.0890 1.0000
6.500 1.1835 0.01209 0.00530 -0.0911 0.0557 1.0000
6.750 1.2084 0.01240 0.00562 -0.0907 0.0509 1.0000
7.000 1.2322 0.01282 0.00604 -0.0901 0.0440 1.0000
7.250 1.2560 0.01323 0.00640 -0.0895 0.0324 1.0000
7.500 1.2767 0.01400 0.00704 -0.0885 0.0152 1.0000
7.750 1.3002 0.01442 0.00751 -0.0878 0.0137 1.0000
8.000 1.3230 0.01489 0.00804 -0.0871 0.0127 1.0000
8.250 1.3447 0.01547 0.00869 -0.0861 0.0117 1.0000
8.500 1.3639 0.01632 0.00963 -0.0848 0.0106 1.0000
8.750 1.3851 0.01688 0.01025 -0.0839 0.0103 1.0000
9.000 1.4060 0.01745 0.01087 -0.0829 0.0099 1.0000
9.250 1.4261 0.01805 0.01154 -0.0818 0.0094 1.0000
9.500 1.4454 0.01870 0.01224 -0.0806 0.0089 1.0000
9.750 1.4630 0.01945 0.01305 -0.0792 0.0084 1.0000
10.000 1.4778 0.02040 0.01407 -0.0773 0.0080 1.0000
10.250 1.4838 0.02194 0.01573 -0.0742 0.0076 1.0000
10.500 1.4866 0.02333 0.01723 -0.0705 0.0074 1.0000
10.750 1.4986 0.02411 0.01810 -0.0684 0.0073 1.0000
11.000 1.5083 0.02508 0.01914 -0.0660 0.0072 1.0000
11.250 1.5158 0.02623 0.02038 -0.0636 0.0070 1.0000
11.500 1.5220 0.02753 0.02177 -0.0612 0.0068 1.0000
11.750 1.5273 0.02898 0.02331 -0.0589 0.0067 1.0000
12.000 1.5315 0.03060 0.02503 -0.0568 0.0065 1.0000
12.250 1.5350 0.03240 0.02692 -0.0550 0.0064 1.0000
12.500 1.5380 0.03437 0.02899 -0.0535 0.0062 1.0000
12.750 1.5412 0.03643 0.03114 -0.0522 0.0061 1.0000
13.000 1.5443 0.03859 0.03339 -0.0512 0.0059 1.0000
13.250 1.5464 0.04092 0.03580 -0.0504 0.0058 1.0000
13.500 1.5466 0.04354 0.03851 -0.0497 0.0056 1.0000
13.750 1.5437 0.04658 0.04163 -0.0491 0.0055 1.0000
14.000 1.5364 0.05019 0.04534 -0.0485 0.0054 1.0000
14.250 1.5254 0.05434 0.04961 -0.0480 0.0053 1.0000
14.500 1.5099 0.05907 0.05447 -0.0473 0.0052 1.0000
14.750 1.4976 0.06363 0.05916 -0.0469 0.0051 1.0000
15.000 1.4936 0.06751 0.06317 -0.0476 0.0051 1.0000
15.250 1.4887 0.07165 0.06744 -0.0486 0.0050 1.0000
15.500 1.4826 0.07610 0.07202 -0.0498 0.0050 1.0000
15.750 1.4753 0.08085 0.07691 -0.0511 0.0050 1.0000
16.000 1.4673 0.08580 0.08197 -0.0527 0.0049 1.0000
16.250 1.4580 0.09105 0.08736 -0.0544 0.0049 1.0000
16.500 1.4482 0.09651 0.09294 -0.0564 0.0049 1.0000
16.750 1.4376 0.10222 0.09878 -0.0585 0.0049 1.0000
17.000 1.4266 0.10812 0.10481 -0.0609 0.0048 1.0000
17.250 1.4149 0.11424 0.11106 -0.0636 0.0048 1.0000
17.500 1.4034 0.12055 0.11750 -0.0665 0.0048 1.0000
17.750 1.3917 0.12704 0.12411 -0.0697 0.0048 1.0000
18.000 1.3794 0.13377 0.13097 -0.0731 0.0048 1.0000
18.250 1.3673 0.14064 0.13796 -0.0768 0.0048 1.0000
18.500 1.3551 0.14771 0.14516 -0.0807 0.0048 1.0000
18.750 1.3433 0.15494 0.15251 -0.0850 0.0048 1.0000
19.000 1.3310 0.16254 0.16024 -0.0896 0.0048 1.0000
19.250 1.3186 0.17041 0.16822 -0.0945 0.0048 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 240 (KOLLER) AIRFOIL (goe240-il)