GOE 438 AIRFOIL (goe438-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 438 AIRFOIL (goe438-il) Reynolds number: 500,000 Max Cl/Cd: 95.04 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe438-il-500000.txt Download as CSV file: xf-goe438-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 438 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2739 0.10121 0.09895 -0.0360 1.0000 0.0364
-10.500 -0.3731 0.10202 0.09960 -0.0355 1.0000 0.0354
-10.250 -0.3663 0.09995 0.09754 -0.0352 1.0000 0.0358
-10.000 -0.3598 0.09808 0.09569 -0.0349 1.0000 0.0367
-9.750 -0.3586 0.09533 0.09296 -0.0353 1.0000 0.0380
-9.500 -0.3163 0.07936 0.07722 -0.0398 1.0000 0.0411
-9.250 -0.3101 0.07859 0.07648 -0.0373 1.0000 0.0416
-9.000 -0.3115 0.07731 0.07523 -0.0349 1.0000 0.0421
-8.750 -0.3010 0.07425 0.07217 -0.0367 0.9986 0.0435
-8.500 -0.4371 0.07206 0.06991 -0.0442 0.9966 0.0400
-8.250 -0.3430 0.04809 0.04584 -0.0691 0.9842 0.0474
-8.000 -0.3844 0.06988 0.06771 -0.0484 0.9912 0.0450
-7.750 -0.3822 0.05018 0.04761 -0.0733 0.9791 0.0485
-7.500 -0.3527 0.05113 0.04863 -0.0731 0.9763 0.0494
-7.250 -0.2976 0.02510 0.02205 -0.0848 0.9632 0.0566
-7.000 -0.2687 0.02394 0.02099 -0.0860 0.9599 0.0574
-6.750 -0.2396 0.02268 0.01974 -0.0875 0.9566 0.0584
-6.500 -0.2180 0.02132 0.01833 -0.0877 0.9485 0.0599
-6.250 -0.1909 0.02010 0.01658 -0.0884 0.9407 0.0658
-6.000 -0.1892 0.01413 0.01029 -0.0878 0.9290 0.0675
-5.750 -0.1668 0.01291 0.00906 -0.0876 0.9196 0.0684
-5.500 -0.1442 0.01179 0.00786 -0.0873 0.9098 0.0695
-5.250 -0.1235 0.01081 0.00676 -0.0865 0.8980 0.0709
-5.000 -0.1014 0.00993 0.00572 -0.0858 0.8869 0.0736
-4.750 -0.0877 0.01732 0.01192 -0.0875 0.8971 0.0600
-4.500 -0.0623 0.01637 0.01081 -0.0869 0.8859 0.0606
-4.250 -0.0359 0.01548 0.00973 -0.0864 0.8751 0.0610
-4.000 -0.0100 0.01462 0.00870 -0.0858 0.8637 0.0611
-3.750 0.0157 0.01393 0.00787 -0.0852 0.8522 0.0615
-3.500 0.0420 0.01332 0.00713 -0.0846 0.8409 0.0620
-3.000 0.0942 0.01240 0.00600 -0.0834 0.8167 0.0634
-2.750 0.1203 0.01210 0.00561 -0.0828 0.8040 0.0644
-2.500 0.1463 0.01179 0.00523 -0.0822 0.7907 0.0650
-2.250 0.1721 0.01151 0.00486 -0.0816 0.7768 0.0655
-2.000 0.1979 0.01129 0.00457 -0.0809 0.7613 0.0659
-1.750 0.2220 0.01062 0.00385 -0.0800 0.7445 0.0671
-1.500 0.2463 0.01023 0.00341 -0.0791 0.7261 0.0684
-1.250 0.2709 0.01002 0.00313 -0.0782 0.7067 0.0698
-1.000 0.2956 0.00990 0.00294 -0.0774 0.6878 0.0714
-0.750 0.3203 0.00982 0.00278 -0.0766 0.6704 0.0734
-0.500 0.3453 0.00975 0.00263 -0.0758 0.6549 0.0750
-0.250 0.3706 0.00970 0.00251 -0.0752 0.6407 0.0766
0.000 0.3961 0.00967 0.00243 -0.0745 0.6273 0.0779
0.250 0.4211 0.00954 0.00225 -0.0738 0.6152 0.0813
0.500 0.4464 0.00951 0.00218 -0.0731 0.6032 0.0857
0.750 0.4721 0.00949 0.00213 -0.0725 0.5905 0.0906
1.000 0.4976 0.00943 0.00210 -0.0719 0.5778 0.1036
1.250 0.5172 0.00862 0.00213 -0.0707 0.5658 0.4029
1.500 0.5918 0.00739 0.00241 -0.0805 0.5470 0.9883
1.750 0.6422 0.00754 0.00243 -0.0853 0.5273 1.0000
2.000 0.6642 0.00767 0.00246 -0.0840 0.5102 1.0000
2.250 0.6859 0.00782 0.00251 -0.0827 0.4923 1.0000
2.500 0.7077 0.00799 0.00257 -0.0814 0.4749 1.0000
2.750 0.7296 0.00817 0.00266 -0.0801 0.4581 1.0000
3.000 0.7512 0.00837 0.00276 -0.0788 0.4395 1.0000
3.250 0.7729 0.00858 0.00287 -0.0775 0.4225 1.0000
3.500 0.7948 0.00880 0.00300 -0.0762 0.4080 1.0000
3.750 0.8168 0.00902 0.00314 -0.0750 0.3957 1.0000
4.000 0.8394 0.00921 0.00327 -0.0739 0.3835 1.0000
4.250 0.8622 0.00940 0.00342 -0.0729 0.3721 1.0000
4.500 0.8846 0.00962 0.00357 -0.0717 0.3614 1.0000
4.750 0.9071 0.00982 0.00373 -0.0706 0.3515 1.0000
5.000 0.9302 0.01001 0.00390 -0.0697 0.3423 1.0000
5.250 0.9521 0.01025 0.00408 -0.0685 0.3332 1.0000
5.500 0.9757 0.01041 0.00425 -0.0676 0.3251 1.0000
5.750 0.9977 0.01066 0.00445 -0.0665 0.3173 1.0000
6.000 1.0214 0.01082 0.00463 -0.0656 0.3098 1.0000
6.500 1.0669 0.01125 0.00505 -0.0637 0.2950 1.0000
7.000 1.1120 0.01170 0.00549 -0.0617 0.2783 1.0000
7.250 1.1335 0.01197 0.00573 -0.0605 0.2707 1.0000
7.500 1.1566 0.01217 0.00596 -0.0596 0.2626 1.0000
7.750 1.1780 0.01245 0.00622 -0.0585 0.2542 1.0000
8.000 1.1999 0.01269 0.00648 -0.0574 0.2449 1.0000
8.250 1.2212 0.01297 0.00676 -0.0563 0.2353 1.0000
8.500 1.2414 0.01329 0.00706 -0.0550 0.2236 1.0000
8.750 1.2606 0.01367 0.00740 -0.0536 0.2070 1.0000
9.000 1.2769 0.01420 0.00780 -0.0517 0.1836 1.0000
9.250 1.2900 0.01489 0.00833 -0.0494 0.1531 1.0000
9.500 1.2979 0.01576 0.00900 -0.0462 0.1230 1.0000
9.750 1.3056 0.01661 0.00972 -0.0429 0.1007 1.0000
10.000 1.3125 0.01752 0.01049 -0.0397 0.0774 1.0000
10.250 1.3218 0.01833 0.01123 -0.0370 0.0679 1.0000
10.500 1.3329 0.01906 0.01197 -0.0346 0.0642 1.0000
10.750 1.3423 0.01988 0.01281 -0.0321 0.0608 1.0000
11.000 1.3527 0.02067 0.01365 -0.0298 0.0583 1.0000
11.250 1.3644 0.02141 0.01448 -0.0278 0.0566 1.0000
11.500 1.3738 0.02230 0.01544 -0.0257 0.0547 1.0000
11.750 1.3805 0.02340 0.01659 -0.0234 0.0527 1.0000
12.000 1.3823 0.02486 0.01811 -0.0208 0.0504 1.0000
12.250 1.3912 0.02594 0.01927 -0.0192 0.0488 1.0000
12.500 1.4022 0.02692 0.02034 -0.0178 0.0469 1.0000
12.750 1.4103 0.02815 0.02164 -0.0164 0.0450 1.0000
13.000 1.4129 0.02987 0.02340 -0.0148 0.0427 1.0000
13.250 1.4160 0.03164 0.02526 -0.0134 0.0407 1.0000
13.500 1.4292 0.03264 0.02634 -0.0127 0.0379 1.0000
13.750 1.4338 0.03443 0.02815 -0.0117 0.0353 1.0000
14.000 1.4403 0.03613 0.02993 -0.0110 0.0323 1.0000
14.250 1.4445 0.03811 0.03194 -0.0104 0.0295 1.0000
14.500 1.4450 0.04059 0.03448 -0.0099 0.0272 1.0000
14.750 1.4465 0.04305 0.03700 -0.0097 0.0254 1.0000
15.000 1.4411 0.04640 0.04040 -0.0097 0.0239 1.0000
15.250 1.4378 0.04963 0.04374 -0.0098 0.0231 1.0000
15.500 1.4335 0.05310 0.04731 -0.0102 0.0223 1.0000
15.750 1.4279 0.05681 0.05113 -0.0108 0.0216 1.0000
16.000 1.4192 0.06106 0.05545 -0.0116 0.0207 1.0000
16.250 1.4089 0.06568 0.06017 -0.0128 0.0202 1.0000
16.500 1.3948 0.07091 0.06550 -0.0142 0.0198 1.0000
16.750 1.3846 0.07575 0.07046 -0.0156 0.0194 1.0000
17.000 1.3767 0.08034 0.07517 -0.0170 0.0191 1.0000
17.250 1.3671 0.08525 0.08019 -0.0186 0.0187 1.0000
17.500 1.3582 0.09013 0.08517 -0.0203 0.0183 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 438 AIRFOIL (goe438-il)