FX 67-K-150/17 AIRFOIL (fx67k150-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 67-K-150/17 AIRFOIL (fx67k150-il) Reynolds number: 100,000 Max Cl/Cd: 27.13 at α=10° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx67k150-il-100000-n5.txt Download as CSV file: xf-fx67k150-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 67-K-150/17 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1240 0.11861 0.11306 -0.0922 0.8178 0.0343
-11.250 -0.1217 0.11580 0.11029 -0.0945 0.8152 0.0348
-11.000 -0.1212 0.11294 0.10746 -0.0971 0.8127 0.0353
-10.750 -0.1185 0.10982 0.10435 -0.0992 0.8105 0.0354
-10.500 -0.1163 0.10652 0.10107 -0.1011 0.8086 0.0356
-10.250 -0.1123 0.10330 0.09786 -0.1029 0.8066 0.0356
-10.000 -0.1083 0.09993 0.09454 -0.1048 0.8039 0.0356
-9.750 -0.1053 0.09645 0.09109 -0.1067 0.8013 0.0357
-9.500 -0.1034 0.09289 0.08756 -0.1087 0.7988 0.0357
-9.250 -0.0859 0.08987 0.08447 -0.1042 0.7973 0.0416
-9.000 -0.0843 0.08669 0.08130 -0.1057 0.7952 0.0416
-8.750 -0.0855 0.08081 0.07541 -0.1092 0.7928 0.0221
-8.500 -0.0867 0.07694 0.07161 -0.1119 0.7897 0.0223
-8.250 -0.0888 0.07316 0.06787 -0.1142 0.7866 0.0217
-8.000 -0.0950 0.06920 0.06390 -0.1169 0.7838 0.0215
-7.750 -0.1035 0.06630 0.06097 -0.1173 0.7814 0.0201
-7.500 -0.1129 0.06327 0.05789 -0.1182 0.7775 0.0213
-7.250 -0.1167 0.06038 0.05492 -0.1183 0.7742 0.0208
-7.000 -0.1181 0.05741 0.05180 -0.1180 0.7714 0.0206
-6.750 -0.1164 0.05439 0.04857 -0.1174 0.7690 0.0209
-6.500 -0.1124 0.05155 0.04550 -0.1166 0.7663 0.0206
-6.250 -0.1070 0.04906 0.04280 -0.1156 0.7623 0.0205
-6.000 -0.0987 0.04634 0.03978 -0.1144 0.7595 0.0202
-5.750 -0.0873 0.04357 0.03667 -0.1131 0.7571 0.0198
-5.500 -0.0723 0.04095 0.03366 -0.1119 0.7553 0.0195
-5.250 -0.0585 0.03882 0.03116 -0.1105 0.7519 0.0194
-5.000 -0.0436 0.03695 0.02893 -0.1089 0.7481 0.0194
-4.750 -0.0242 0.03507 0.02664 -0.1077 0.7456 0.0196
-4.500 -0.0019 0.03327 0.02445 -0.1067 0.7437 0.0201
-4.250 0.0228 0.03160 0.02242 -0.1058 0.7421 0.0209
-4.000 0.0447 0.03087 0.02139 -0.1048 0.7394 0.0232
-3.750 0.0595 0.02989 0.02036 -0.1033 0.7348 0.0262
-3.500 0.0808 0.02895 0.01930 -0.1023 0.7322 0.0285
-3.250 0.1033 0.02807 0.01832 -0.1013 0.7304 0.0315
-3.000 0.1261 0.02727 0.01742 -0.1005 0.7288 0.0386
-2.500 0.1552 0.02714 0.01716 -0.0972 0.7204 0.0533
-2.250 0.1770 0.02678 0.01673 -0.0964 0.7181 0.0676
-2.000 0.1946 0.02526 0.01631 -0.0955 0.7164 0.3209
-1.750 0.1980 0.02426 0.01695 -0.0893 0.7149 0.7383
-1.500 0.1895 0.02551 0.01828 -0.0832 0.7073 0.8083
-1.250 0.1933 0.02589 0.01867 -0.0771 0.7045 0.8696
-1.000 0.2119 0.02601 0.01868 -0.0735 0.7030 0.9167
-0.750 0.2483 0.02603 0.01846 -0.0749 0.7019 0.9323
-0.500 0.2618 0.02715 0.01950 -0.0745 0.6950 0.9472
-0.250 0.2968 0.02749 0.01965 -0.0767 0.6926 0.9574
0.000 0.3364 0.02765 0.01960 -0.0795 0.6910 0.9657
0.250 0.3780 0.02773 0.01952 -0.0826 0.6898 0.9721
0.500 0.4190 0.02776 0.01940 -0.0856 0.6888 0.9784
0.750 0.4597 0.02778 0.01927 -0.0885 0.6879 0.9839
1.500 0.4825 0.02986 0.02120 -0.0826 0.6736 1.0000
2.000 0.4903 0.03140 0.02263 -0.0772 0.6628 1.0000
2.250 0.5200 0.03145 0.02259 -0.0778 0.6616 1.0000
2.750 0.5369 0.03341 0.02448 -0.0745 0.6501 1.0000
3.000 0.5669 0.03348 0.02450 -0.0751 0.6487 1.0000
3.500 0.5894 0.03540 0.02639 -0.0726 0.6374 1.0000
3.750 0.6188 0.03549 0.02646 -0.0731 0.6358 1.0000
4.250 0.6443 0.03736 0.02834 -0.0709 0.6245 1.0000
4.500 0.6736 0.03743 0.02844 -0.0714 0.6227 1.0000
4.750 0.7032 0.03747 0.02850 -0.0718 0.6211 1.0000
5.000 0.7006 0.03927 0.03034 -0.0694 0.6112 1.0000
5.250 0.7300 0.03929 0.03040 -0.0699 0.6094 1.0000
5.500 0.7604 0.03924 0.03044 -0.0703 0.6079 1.0000
5.750 0.7583 0.04107 0.03231 -0.0681 0.5976 1.0000
6.000 0.7878 0.04104 0.03235 -0.0684 0.5957 1.0000
6.500 0.8175 0.04271 0.03417 -0.0668 0.5835 1.0000
6.750 0.8486 0.04246 0.03408 -0.0671 0.5817 1.0000
7.000 0.8500 0.04417 0.03585 -0.0653 0.5713 1.0000
7.250 0.8799 0.04394 0.03576 -0.0655 0.5690 1.0000
7.750 0.9127 0.04531 0.03737 -0.0641 0.5562 1.0000
8.000 0.9453 0.04476 0.03698 -0.0644 0.5544 1.0000
8.250 0.9478 0.04642 0.03880 -0.0627 0.5432 1.0000
8.500 0.9813 0.04562 0.03820 -0.0629 0.5410 1.0000
8.750 0.9878 0.04682 0.03953 -0.0613 0.5295 1.0000
9.250 1.0408 0.04510 0.03820 -0.0599 0.5140 1.0000
9.500 1.0463 0.04583 0.03906 -0.0579 0.4953 1.0000
9.750 1.0619 0.04515 0.03846 -0.0560 0.4671 1.0000
10.000 1.1053 0.04074 0.03349 -0.0536 0.3577 1.0000
10.250 1.0926 0.04326 0.03516 -0.0502 0.2574 1.0000
10.500 1.0731 0.04712 0.03837 -0.0475 0.1744 1.0000
10.750 1.0547 0.05112 0.04156 -0.0452 0.0769 1.0000
11.000 1.0461 0.05442 0.04434 -0.0434 0.0275 1.0000
11.250 1.0515 0.05657 0.04655 -0.0424 0.0170 1.0000
11.500 1.0558 0.05887 0.04887 -0.0415 0.0124 1.0000
11.750 1.0612 0.06113 0.05129 -0.0407 0.0115 1.0000
12.000 1.0659 0.06354 0.05387 -0.0400 0.0107 1.0000
12.250 1.0703 0.06603 0.05657 -0.0393 0.0103 1.0000
12.500 1.0739 0.06863 0.05936 -0.0388 0.0099 1.0000
12.750 1.0766 0.07140 0.06231 -0.0382 0.0096 1.0000
13.000 1.0800 0.07410 0.06518 -0.0377 0.0093 1.0000
13.250 1.0839 0.07674 0.06798 -0.0372 0.0091 1.0000
13.500 1.0895 0.07918 0.07057 -0.0366 0.0088 1.0000
13.750 1.0975 0.08132 0.07285 -0.0359 0.0086 1.0000
14.000 1.1084 0.08318 0.07484 -0.0351 0.0084 1.0000
14.500 1.1352 0.08674 0.07882 -0.0334 0.0081 1.0000
14.750 1.1473 0.08899 0.08129 -0.0327 0.0080 1.0000
15.000 1.1559 0.09181 0.08437 -0.0323 0.0079 1.0000
15.250 1.1604 0.09523 0.08806 -0.0321 0.0078 1.0000
15.500 1.1613 0.09906 0.09217 -0.0323 0.0078 1.0000
15.750 1.1579 0.10350 0.09688 -0.0329 0.0078 1.0000
16.000 1.1513 0.10842 0.10209 -0.0338 0.0078 1.0000
16.250 1.1421 0.11377 0.10772 -0.0352 0.0079 1.0000
16.500 1.1312 0.11949 0.11370 -0.0372 0.0079 1.0000
16.750 1.1188 0.12563 0.12009 -0.0396 0.0079 1.0000
17.000 1.1051 0.13232 0.12702 -0.0427 0.0080 1.0000
17.250 1.0904 0.13951 0.13444 -0.0464 0.0080 1.0000
17.500 1.0748 0.14736 0.14249 -0.0508 0.0082 1.0000
17.750 1.0584 0.15594 0.15126 -0.0559 0.0083 1.0000
18.000 1.0426 0.16514 0.16062 -0.0617 0.0085 1.0000
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Polar data table (+)
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