FX 67-K-150/17 AIRFOIL (fx67k150-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 67-K-150/17 AIRFOIL (fx67k150-il) Reynolds number: 200,000 Max Cl/Cd: 68.49 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx67k150-il-200000-n5.txt Download as CSV file: xf-fx67k150-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0534 0.07902 0.07476 -0.0915 0.7517 0.0124
-9.250 -0.0532 0.07498 0.07075 -0.0928 0.7498 0.0115
-9.000 -0.0536 0.07092 0.06671 -0.0942 0.7479 0.0109
-8.750 -0.0552 0.06670 0.06252 -0.0959 0.7462 0.0102
-8.500 -0.0621 0.06130 0.05715 -0.0983 0.7447 0.0094
-8.000 -0.1120 0.06042 0.05604 -0.1140 0.7459 0.0081
-7.750 -0.1242 0.05761 0.05318 -0.1137 0.7437 0.0080
-7.500 -0.1308 0.05402 0.04946 -0.1139 0.7420 0.0079
-7.250 -0.1327 0.05076 0.04608 -0.1137 0.7401 0.0077
-7.000 -0.1314 0.04748 0.04266 -0.1133 0.7374 0.0076
-6.750 -0.1268 0.04420 0.03914 -0.1127 0.7348 0.0075
-6.500 -0.1191 0.04096 0.03566 -0.1118 0.7327 0.0073
-6.250 -0.1081 0.03781 0.03221 -0.1109 0.7308 0.0072
-6.000 -0.0948 0.03458 0.02863 -0.1097 0.7292 0.0072
-5.750 -0.0788 0.03151 0.02514 -0.1086 0.7280 0.0072
-5.500 -0.0607 0.02889 0.02215 -0.1075 0.7257 0.0072
-5.250 -0.0405 0.02642 0.01927 -0.1064 0.7232 0.0074
-5.000 -0.0176 0.02436 0.01678 -0.1054 0.7210 0.0079
-4.750 0.0058 0.02313 0.01534 -0.1052 0.7190 0.0092
-4.500 0.0309 0.02263 0.01472 -0.1051 0.7173 0.0110
-4.250 0.0569 0.02138 0.01322 -0.1047 0.7160 0.0122
-4.000 0.0829 0.02018 0.01182 -0.1042 0.7148 0.0130
-3.750 0.1078 0.01940 0.01091 -0.1037 0.7127 0.0140
-3.500 0.1290 0.01820 0.00971 -0.1029 0.7100 0.0167
-3.250 0.1538 0.01781 0.00926 -0.1027 0.7077 0.0217
-3.000 0.1778 0.01710 0.00844 -0.1022 0.7057 0.0256
-2.750 0.2033 0.01666 0.00792 -0.1021 0.7041 0.0333
-2.500 0.2295 0.01626 0.00744 -0.1020 0.7027 0.0423
-2.250 0.2559 0.01584 0.00702 -0.1020 0.7016 0.0673
-2.000 0.2751 0.01475 0.00684 -0.1016 0.6991 0.3178
-1.750 0.2884 0.01374 0.00710 -0.0994 0.6961 0.6396
-1.500 0.3050 0.01390 0.00762 -0.0962 0.6937 0.7780
-1.250 0.3269 0.01409 0.00777 -0.0946 0.6919 0.8154
-1.000 0.3491 0.01421 0.00783 -0.0931 0.6904 0.8370
-0.750 0.3757 0.01421 0.00770 -0.0928 0.6891 0.8466
-0.500 0.4026 0.01420 0.00757 -0.0926 0.6879 0.8550
-0.250 0.4236 0.01445 0.00783 -0.0917 0.6843 0.8628
0.000 0.4475 0.01460 0.00792 -0.0913 0.6816 0.8709
0.250 0.4722 0.01465 0.00792 -0.0909 0.6796 0.8773
0.500 0.4985 0.01466 0.00787 -0.0908 0.6778 0.8843
0.750 0.5251 0.01463 0.00778 -0.0907 0.6764 0.8900
1.000 0.5527 0.01460 0.00769 -0.0908 0.6751 0.8959
1.250 0.5749 0.01482 0.00792 -0.0902 0.6722 0.9020
1.500 0.5964 0.01504 0.00817 -0.0895 0.6689 0.9084
1.750 0.6215 0.01512 0.00824 -0.0893 0.6665 0.9145
2.000 0.6481 0.01514 0.00825 -0.0893 0.6647 0.9201
2.250 0.6761 0.01513 0.00823 -0.0897 0.6632 0.9262
2.500 0.7062 0.01508 0.00816 -0.0903 0.6619 0.9312
2.750 0.7280 0.01539 0.00852 -0.0899 0.6585 0.9390
3.000 0.7527 0.01567 0.00886 -0.0900 0.6550 0.9461
3.250 0.7819 0.01575 0.00899 -0.0908 0.6527 0.9534
3.500 0.8153 0.01576 0.00902 -0.0923 0.6509 0.9595
3.750 0.8496 0.01573 0.00901 -0.0940 0.6494 0.9662
4.000 0.8860 0.01567 0.00897 -0.0961 0.6481 0.9724
4.500 0.9359 0.01645 0.00997 -0.0972 0.6396 1.0000
4.750 0.9634 0.01646 0.01001 -0.0975 0.6373 1.0000
5.000 0.9936 0.01639 0.00997 -0.0983 0.6356 1.0000
5.250 1.0097 0.01689 0.01061 -0.0971 0.6308 1.0000
5.500 1.0320 0.01703 0.01083 -0.0966 0.6260 1.0000
5.750 1.0674 0.01651 0.01034 -0.0978 0.6222 1.0000
6.000 1.0798 0.01693 0.01086 -0.0959 0.6143 1.0000
6.250 1.1123 0.01652 0.01049 -0.0966 0.6090 1.0000
6.500 1.1236 0.01701 0.01115 -0.0945 0.6017 1.0000
6.750 1.1470 0.01677 0.01096 -0.0938 0.5917 1.0000
7.000 1.1520 0.01682 0.01101 -0.0900 0.5713 1.0000
7.250 1.1624 0.01714 0.01137 -0.0875 0.5567 1.0000
7.500 1.1675 0.01767 0.01184 -0.0844 0.5295 1.0000
7.750 1.1618 0.01861 0.01229 -0.0797 0.4542 1.0000
8.000 1.1446 0.02068 0.01391 -0.0745 0.3930 1.0000
8.250 1.1311 0.02286 0.01581 -0.0702 0.3467 1.0000
8.500 1.1035 0.02607 0.01856 -0.0649 0.2794 1.0000
8.750 1.0865 0.02890 0.02103 -0.0611 0.2222 1.0000
9.000 1.0670 0.03207 0.02374 -0.0573 0.1524 1.0000
9.250 1.0396 0.03612 0.02709 -0.0533 0.0545 1.0000
9.500 1.0388 0.03837 0.02918 -0.0515 0.0244 1.0000
9.750 1.0426 0.04032 0.03106 -0.0502 0.0088 1.0000
10.000 1.0509 0.04195 0.03276 -0.0491 0.0069 1.0000
10.250 1.0601 0.04354 0.03447 -0.0481 0.0063 1.0000
10.500 1.0693 0.04516 0.03629 -0.0472 0.0059 1.0000
10.750 1.0780 0.04687 0.03813 -0.0464 0.0057 1.0000
11.000 1.0854 0.04872 0.04013 -0.0455 0.0055 1.0000
11.250 1.0922 0.05068 0.04223 -0.0446 0.0053 1.0000
11.500 1.0968 0.05291 0.04459 -0.0437 0.0051 1.0000
11.750 1.1021 0.05512 0.04693 -0.0430 0.0050 1.0000
12.000 1.1056 0.05753 0.04948 -0.0422 0.0049 1.0000
12.250 1.1091 0.06001 0.05207 -0.0414 0.0048 1.0000
12.500 1.1132 0.06245 0.05463 -0.0408 0.0048 1.0000
12.750 1.1171 0.06494 0.05723 -0.0401 0.0046 1.0000
13.000 1.1227 0.06726 0.05965 -0.0395 0.0045 1.0000
13.250 1.1288 0.06953 0.06201 -0.0391 0.0042 1.0000
13.500 1.1322 0.07212 0.06466 -0.0385 0.0037 1.0000
13.750 1.1392 0.07437 0.06702 -0.0378 0.0034 1.0000
14.000 1.1482 0.07646 0.06932 -0.0375 0.0032 1.0000
14.250 1.1571 0.07862 0.07165 -0.0369 0.0030 1.0000
14.500 1.1655 0.08093 0.07414 -0.0364 0.0029 1.0000
14.750 1.1727 0.08350 0.07690 -0.0359 0.0029 1.0000
15.000 1.1779 0.08641 0.08003 -0.0356 0.0028 1.0000
15.250 1.1804 0.08977 0.08363 -0.0355 0.0028 1.0000
15.500 1.1810 0.09338 0.08748 -0.0357 0.0028 1.0000
15.750 1.1782 0.09760 0.09195 -0.0361 0.0028 1.0000
16.000 1.1729 0.10226 0.09687 -0.0368 0.0027 1.0000
16.250 1.1658 0.10723 0.10208 -0.0379 0.0028 1.0000
16.500 1.1568 0.11265 0.10775 -0.0395 0.0028 1.0000
16.750 1.1456 0.11862 0.11396 -0.0415 0.0027 1.0000
17.000 1.1349 0.12463 0.12019 -0.0439 0.0028 1.0000
17.250 1.1222 0.13127 0.12705 -0.0468 0.0028 1.0000
17.500 1.1096 0.13813 0.13411 -0.0502 0.0028 1.0000
17.750 1.0954 0.14571 0.14189 -0.0543 0.0028 1.0000
18.000 1.0830 0.15321 0.14956 -0.0587 0.0029 1.0000
18.250 1.0692 0.16153 0.15804 -0.0637 0.0029 1.0000
18.500 1.0561 0.17026 0.16692 -0.0692 0.0029 1.0000
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