FX 67-K-170/17 AIRFOIL (fx67k170-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 67-K-170/17 AIRFOIL (fx67k170-il) Reynolds number: 200,000 Max Cl/Cd: 48.24 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx67k170-il-200000-n5.txt Download as CSV file: xf-fx67k170-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 67-K-170/17 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1032 0.09548 0.09074 -0.1043 0.7540 0.0138
-11.000 -0.1028 0.09149 0.08679 -0.1060 0.7522 0.0137
-10.750 -0.1018 0.08783 0.08317 -0.1076 0.7505 0.0136
-10.500 -0.1021 0.08402 0.07939 -0.1094 0.7488 0.0134
-10.250 -0.1029 0.08020 0.07560 -0.1112 0.7471 0.0133
-10.000 -0.1076 0.07549 0.07092 -0.1136 0.7454 0.0131
-9.750 -0.1166 0.06974 0.06520 -0.1170 0.7438 0.0130
-9.500 -0.1307 0.06276 0.05819 -0.1223 0.7422 0.0127
-9.250 -0.1506 0.05738 0.05275 -0.1251 0.7404 0.0125
-9.000 -0.1707 0.05339 0.04871 -0.1254 0.7376 0.0123
-8.750 -0.1931 0.05025 0.04545 -0.1232 0.7349 0.0124
-8.500 -0.2064 0.04701 0.04202 -0.1211 0.7327 0.0123
-8.250 -0.2154 0.04341 0.03814 -0.1189 0.7308 0.0124
-8.000 -0.2207 0.03948 0.03378 -0.1163 0.7291 0.0132
-7.750 -0.2197 0.03593 0.02969 -0.1139 0.7276 0.0136
-7.500 -0.2126 0.03316 0.02645 -0.1119 0.7258 0.0141
-7.250 -0.1993 0.03125 0.02431 -0.1107 0.7232 0.0143
-7.000 -0.1826 0.02962 0.02245 -0.1097 0.7210 0.0145
-6.750 -0.1636 0.02821 0.02082 -0.1089 0.7191 0.0149
-6.500 -0.1429 0.02682 0.01920 -0.1082 0.7174 0.0154
-6.250 -0.1207 0.02547 0.01759 -0.1076 0.7159 0.0161
-6.000 -0.0972 0.02417 0.01603 -0.1070 0.7145 0.0169
-5.750 -0.0725 0.02305 0.01464 -0.1065 0.7133 0.0179
-5.500 -0.0493 0.02214 0.01363 -0.1061 0.7115 0.0194
-5.250 -0.0272 0.02167 0.01318 -0.1057 0.7089 0.0212
-5.000 -0.0042 0.02104 0.01249 -0.1052 0.7067 0.0227
-4.750 0.0191 0.02042 0.01178 -0.1046 0.7048 0.0243
-4.500 0.0411 0.01967 0.01100 -0.1040 0.7031 0.0265
-4.250 0.0654 0.01925 0.01055 -0.1037 0.7016 0.0297
-4.000 0.0904 0.01886 0.01006 -0.1034 0.7003 0.0326
-3.750 0.1143 0.01827 0.00942 -0.1031 0.6991 0.0358
-3.500 0.1374 0.01806 0.00916 -0.1026 0.6970 0.0387
-3.250 0.1595 0.01802 0.00908 -0.1020 0.6942 0.0423
-3.000 0.1826 0.01779 0.00885 -0.1016 0.6919 0.0482
-2.750 0.2068 0.01753 0.00861 -0.1013 0.6901 0.0632
-2.500 0.2289 0.01686 0.00831 -0.1009 0.6884 0.1638
-2.250 0.2485 0.01587 0.00804 -0.1003 0.6870 0.3600
-2.000 0.2649 0.01490 0.00800 -0.0985 0.6857 0.5979
-1.750 0.2841 0.01493 0.00847 -0.0958 0.6847 0.7376
-1.500 0.3010 0.01549 0.00907 -0.0939 0.6812 0.7759
-1.250 0.3217 0.01584 0.00938 -0.0927 0.6785 0.7940
-1.000 0.3439 0.01606 0.00957 -0.0915 0.6764 0.8105
-0.750 0.3671 0.01619 0.00964 -0.0904 0.6747 0.8252
-0.500 0.3922 0.01624 0.00961 -0.0899 0.6733 0.8361
-0.250 0.4187 0.01623 0.00952 -0.0896 0.6721 0.8424
0.000 0.4461 0.01622 0.00943 -0.0896 0.6711 0.8491
0.250 0.4641 0.01659 0.00980 -0.0884 0.6681 0.8553
0.500 0.4795 0.01701 0.01024 -0.0867 0.6643 0.8614
0.750 0.5030 0.01714 0.01032 -0.0863 0.6621 0.8676
1.000 0.5278 0.01715 0.01030 -0.0859 0.6604 0.8721
1.250 0.5544 0.01714 0.01025 -0.0859 0.6591 0.8771
1.750 0.6104 0.01709 0.01011 -0.0864 0.6571 0.8855
2.250 0.6288 0.01828 0.01140 -0.0814 0.6482 0.8977
2.500 0.6528 0.01834 0.01147 -0.0811 0.6465 0.9019
2.750 0.6796 0.01835 0.01146 -0.0812 0.6452 0.9064
3.000 0.7088 0.01829 0.01139 -0.0817 0.6442 0.9108
3.250 0.7392 0.01818 0.01127 -0.0824 0.6433 0.9143
3.750 0.7357 0.02004 0.01330 -0.0744 0.6320 0.9330
4.000 0.7670 0.01995 0.01322 -0.0754 0.6310 0.9379
4.250 0.8006 0.01983 0.01311 -0.0767 0.6301 0.9424
4.500 0.8364 0.01970 0.01301 -0.0784 0.6294 0.9466
4.750 0.8739 0.01953 0.01286 -0.0805 0.6287 0.9509
5.250 0.8926 0.02192 0.01542 -0.0787 0.6162 1.0000
5.500 0.9298 0.02139 0.01491 -0.0801 0.6154 1.0000
5.750 0.9774 0.02026 0.01380 -0.0828 0.6143 1.0000
6.000 0.9437 0.02317 0.01675 -0.0763 0.6022 1.0000
6.250 0.9940 0.02157 0.01517 -0.0788 0.6010 1.0000
6.750 1.0108 0.02333 0.01700 -0.0753 0.5876 1.0000
7.000 1.0482 0.02267 0.01639 -0.0766 0.5864 1.0000
7.500 1.0436 0.02595 0.01979 -0.0711 0.5694 1.0000
8.000 1.0855 0.02638 0.02033 -0.0702 0.5591 1.0000
8.250 1.0785 0.02847 0.02248 -0.0672 0.5479 1.0000
8.500 1.1135 0.02771 0.02179 -0.0680 0.5448 1.0000
9.000 1.1254 0.03021 0.02443 -0.0645 0.5247 1.0000
9.250 1.1575 0.02944 0.02369 -0.0649 0.5150 1.0000
9.500 1.1663 0.03047 0.02477 -0.0633 0.5018 1.0000
9.750 1.1822 0.03095 0.02530 -0.0624 0.4874 1.0000
10.000 1.1974 0.03145 0.02579 -0.0614 0.4670 1.0000
10.250 1.2210 0.03123 0.02547 -0.0608 0.4403 1.0000
10.500 1.2312 0.03185 0.02579 -0.0590 0.3977 1.0000
10.750 1.2277 0.03372 0.02740 -0.0564 0.3594 1.0000
11.000 1.2250 0.03575 0.02929 -0.0541 0.3300 1.0000
11.250 1.2210 0.03801 0.03141 -0.0520 0.3005 1.0000
11.500 1.2178 0.04034 0.03362 -0.0501 0.2728 1.0000
11.750 1.2138 0.04282 0.03597 -0.0483 0.2445 1.0000
12.000 1.2099 0.04541 0.03842 -0.0466 0.2162 1.0000
12.250 1.2032 0.04833 0.04116 -0.0449 0.1839 1.0000
12.500 1.1977 0.05123 0.04389 -0.0435 0.1519 1.0000
12.750 1.1929 0.05416 0.04664 -0.0422 0.1204 1.0000
13.250 1.1873 0.05987 0.05204 -0.0402 0.0702 1.0000
13.500 1.1886 0.06242 0.05454 -0.0395 0.0578 1.0000
13.750 1.1926 0.06476 0.05690 -0.0390 0.0501 1.0000
14.000 1.1962 0.06717 0.05931 -0.0386 0.0439 1.0000
14.250 1.2005 0.06956 0.06172 -0.0383 0.0387 1.0000
14.500 1.2044 0.07202 0.06422 -0.0380 0.0346 1.0000
14.750 1.2106 0.07426 0.06655 -0.0378 0.0312 1.0000
15.000 1.2145 0.07683 0.06919 -0.0377 0.0287 1.0000
15.250 1.2204 0.07918 0.07164 -0.0377 0.0257 1.0000
15.500 1.2281 0.08133 0.07391 -0.0377 0.0200 1.0000
15.750 1.2334 0.08380 0.07642 -0.0378 0.0147 1.0000
16.000 1.2352 0.08673 0.07938 -0.0379 0.0117 1.0000
16.250 1.2364 0.08981 0.08251 -0.0380 0.0102 1.0000
16.500 1.2370 0.09302 0.08583 -0.0383 0.0091 1.0000
16.750 1.2369 0.09637 0.08926 -0.0386 0.0083 1.0000
17.000 1.2365 0.09979 0.09277 -0.0391 0.0077 1.0000
17.250 1.2370 0.10314 0.09627 -0.0396 0.0070 1.0000
17.500 1.2377 0.10648 0.09972 -0.0403 0.0065 1.0000
17.750 1.2378 0.10996 0.10334 -0.0411 0.0062 1.0000
18.000 1.2364 0.11370 0.10717 -0.0420 0.0058 1.0000
18.250 1.2349 0.11751 0.11111 -0.0431 0.0057 1.0000
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