FX 67-K-150/17 AIRFOIL (fx67k150-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 67-K-150/17 AIRFOIL (fx67k150-il) Reynolds number: 1,000,000 Max Cl/Cd: 147.83 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx67k150-il-1000000-n5.txt Download as CSV file: xf-fx67k150-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.1547 0.04517 0.04208 -0.1144 0.6886 0.0022
-7.250 -0.1550 0.04115 0.03790 -0.1137 0.6870 0.0022
-7.000 -0.1521 0.03696 0.03352 -0.1126 0.6853 0.0021
-6.750 -0.1460 0.03271 0.02904 -0.1112 0.6835 0.0020
-6.500 -0.1374 0.02824 0.02425 -0.1094 0.6816 0.0020
-6.250 -0.1291 0.02249 0.01800 -0.1067 0.6798 0.0019
-6.000 -0.1220 0.01471 0.00925 -0.1028 0.6782 0.0018
-5.750 -0.0986 0.01327 0.00754 -0.1022 0.6766 0.0018
-5.500 -0.0740 0.01238 0.00646 -0.1019 0.6750 0.0018
-5.250 -0.0488 0.01164 0.00559 -0.1016 0.6736 0.0019
-5.000 -0.0230 0.01104 0.00489 -0.1015 0.6719 0.0020
-4.750 0.0034 0.01059 0.00435 -0.1014 0.6701 0.0021
-4.500 0.0302 0.01022 0.00392 -0.1015 0.6681 0.0023
-4.250 0.0571 0.00989 0.00352 -0.1016 0.6662 0.0026
-4.000 0.0842 0.00958 0.00316 -0.1017 0.6645 0.0032
-3.750 0.1117 0.00937 0.00290 -0.1019 0.6629 0.0039
-3.250 0.1673 0.00900 0.00249 -0.1023 0.6597 0.0069
-3.000 0.1953 0.00884 0.00239 -0.1027 0.6579 0.0114
-2.750 0.2237 0.00879 0.00235 -0.1031 0.6559 0.0144
-2.500 0.2516 0.00861 0.00214 -0.1034 0.6539 0.0184
-2.250 0.2798 0.00850 0.00200 -0.1037 0.6521 0.0212
-2.000 0.3081 0.00842 0.00188 -0.1040 0.6504 0.0237
-1.750 0.3361 0.00831 0.00178 -0.1043 0.6486 0.0339
-1.500 0.3634 0.00802 0.00168 -0.1046 0.6468 0.1023
-1.250 0.3904 0.00764 0.00159 -0.1050 0.6449 0.2037
-1.000 0.4158 0.00699 0.00150 -0.1053 0.6430 0.3943
-0.750 0.4407 0.00636 0.00144 -0.1054 0.6410 0.5900
-0.500 0.4668 0.00607 0.00148 -0.1053 0.6389 0.7005
-0.250 0.4944 0.00605 0.00154 -0.1055 0.6369 0.7460
0.000 0.5224 0.00608 0.00158 -0.1057 0.6351 0.7669
0.250 0.5512 0.00611 0.00160 -0.1061 0.6333 0.7756
0.500 0.5799 0.00614 0.00163 -0.1065 0.6313 0.7819
0.750 0.6087 0.00617 0.00165 -0.1070 0.6291 0.7880
1.000 0.6372 0.00620 0.00168 -0.1074 0.6270 0.7927
1.250 0.6657 0.00624 0.00171 -0.1078 0.6249 0.7977
1.500 0.6943 0.00630 0.00174 -0.1082 0.6228 0.8023
1.750 0.7225 0.00634 0.00179 -0.1086 0.6208 0.8060
2.000 0.7510 0.00638 0.00185 -0.1091 0.6187 0.8100
2.250 0.7796 0.00642 0.00190 -0.1095 0.6162 0.8138
2.500 0.8080 0.00647 0.00194 -0.1099 0.6130 0.8169
2.750 0.8353 0.00653 0.00200 -0.1101 0.6072 0.8197
3.000 0.8632 0.00657 0.00206 -0.1105 0.6006 0.8227
3.250 0.8908 0.00664 0.00212 -0.1108 0.5962 0.8259
3.500 0.9187 0.00671 0.00220 -0.1111 0.5920 0.8290
3.750 0.9464 0.00676 0.00229 -0.1115 0.5874 0.8317
4.000 0.9734 0.00684 0.00239 -0.1117 0.5824 0.8345
4.250 1.0008 0.00692 0.00249 -0.1119 0.5770 0.8374
4.500 1.0273 0.00702 0.00260 -0.1120 0.5694 0.8404
4.750 1.0540 0.00713 0.00273 -0.1122 0.5613 0.8433
5.000 1.0763 0.00739 0.00291 -0.1115 0.5369 0.8463
5.250 1.0865 0.00819 0.00341 -0.1087 0.4728 0.8501
5.500 1.0760 0.00975 0.00445 -0.1024 0.3726 0.8559
5.750 1.0580 0.01104 0.00541 -0.0946 0.3034 0.8624
6.000 1.0395 0.01235 0.00653 -0.0872 0.2578 0.8712
6.250 1.0211 0.01415 0.00813 -0.0809 0.2068 0.8817
6.500 0.9929 0.01662 0.01027 -0.0738 0.1294 0.8984
6.750 0.9945 0.01777 0.01137 -0.0707 0.1006 0.9182
7.000 0.9980 0.02006 0.01342 -0.0701 0.0274 1.0000
7.250 1.0027 0.02140 0.01467 -0.0679 0.0034 1.0000
7.500 1.0172 0.02219 0.01549 -0.0668 0.0025 1.0000
7.750 1.0309 0.02303 0.01638 -0.0657 0.0020 1.0000
8.000 1.0448 0.02388 0.01727 -0.0646 0.0019 1.0000
8.250 1.0579 0.02479 0.01822 -0.0635 0.0018 1.0000
8.500 1.0706 0.02573 0.01920 -0.0624 0.0017 1.0000
8.750 1.0838 0.02665 0.02016 -0.0613 0.0016 1.0000
9.000 1.0971 0.02758 0.02110 -0.0604 0.0013 1.0000
9.250 1.1086 0.02868 0.02226 -0.0592 0.0013 1.0000
9.500 1.1208 0.02976 0.02337 -0.0582 0.0012 1.0000
9.750 1.1315 0.03097 0.02465 -0.0571 0.0012 1.0000
10.000 1.1423 0.03220 0.02593 -0.0560 0.0011 1.0000
10.250 1.1533 0.03344 0.02722 -0.0551 0.0010 1.0000
10.500 1.1636 0.03475 0.02858 -0.0541 0.0009 1.0000
10.750 1.1731 0.03616 0.03004 -0.0530 0.0009 1.0000
11.000 1.1828 0.03758 0.03150 -0.0521 0.0008 1.0000
11.250 1.1879 0.03942 0.03340 -0.0509 0.0007 1.0000
11.500 1.1897 0.04160 0.03568 -0.0494 0.0007 1.0000
11.750 1.1974 0.04330 0.03744 -0.0485 0.0006 1.0000
12.000 1.2041 0.04513 0.03934 -0.0476 0.0006 1.0000
12.250 1.2115 0.04693 0.04121 -0.0467 0.0006 1.0000
12.500 1.2159 0.04903 0.04339 -0.0458 0.0006 1.0000
12.750 1.2250 0.05073 0.04515 -0.0452 0.0005 1.0000
13.000 1.2290 0.05297 0.04749 -0.0444 0.0005 1.0000
13.250 1.2363 0.05491 0.04951 -0.0438 0.0005 1.0000
13.500 1.2408 0.05717 0.05187 -0.0431 0.0005 1.0000
13.750 1.2449 0.05951 0.05430 -0.0424 0.0004 1.0000
14.000 1.2499 0.06181 0.05669 -0.0418 0.0004 1.0000
14.250 1.2530 0.06435 0.05934 -0.0411 0.0004 1.0000
14.500 1.2570 0.06683 0.06193 -0.0406 0.0004 1.0000
14.750 1.2605 0.06941 0.06464 -0.0401 0.0004 1.0000
15.000 1.2638 0.07212 0.06747 -0.0396 0.0004 1.0000
15.250 1.2654 0.07510 0.07061 -0.0392 0.0004 1.0000
15.500 1.2690 0.07790 0.07351 -0.0393 0.0004 1.0000
15.750 1.2684 0.08134 0.07712 -0.0390 0.0004 1.0000
16.000 1.2664 0.08510 0.08105 -0.0391 0.0003 1.0000
16.250 1.2636 0.08906 0.08518 -0.0394 0.0004 1.0000
16.500 1.2575 0.09364 0.08995 -0.0399 0.0003 1.0000
16.750 1.2485 0.09882 0.09535 -0.0408 0.0003 1.0000
17.000 1.2409 0.10387 0.10057 -0.0420 0.0004 1.0000
17.250 1.2292 0.10978 0.10667 -0.0436 0.0004 1.0000
17.500 1.2185 0.11567 0.11273 -0.0456 0.0004 1.0000
17.750 1.2028 0.12267 0.11993 -0.0482 0.0004 1.0000
18.000 1.1919 0.12894 0.12635 -0.0509 0.0004 1.0000
18.250 1.1768 0.13630 0.13389 -0.0544 0.0004 1.0000
18.500 1.1630 0.14366 0.14140 -0.0581 0.0004 1.0000
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