FX 67-K-150/17 AIRFOIL (fx67k150-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 67-K-150/17 AIRFOIL (fx67k150-il) Reynolds number: 200,000 Max Cl/Cd: 61.62 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx67k150-il-200000.txt Download as CSV file: xf-fx67k150-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.0540 0.09937 0.09566 -0.0945 0.8145 0.0316
-10.500 -0.0549 0.09615 0.09246 -0.0969 0.8125 0.0321
-10.250 -0.0542 0.09280 0.08912 -0.0988 0.8107 0.0323
-10.000 -0.0541 0.08929 0.08561 -0.1008 0.8091 0.0324
-9.750 -0.0527 0.08578 0.08211 -0.1023 0.8076 0.0325
-9.500 -0.0533 0.08194 0.07829 -0.1044 0.8059 0.0326
-9.250 -0.0487 0.07625 0.07265 -0.1030 0.8039 0.0344
-9.000 -0.0426 0.07332 0.06974 -0.1035 0.8012 0.0355
-8.750 -0.0400 0.07012 0.06653 -0.1043 0.7989 0.0369
-8.500 -0.0407 0.06660 0.06302 -0.1056 0.7968 0.0378
-8.250 -0.0437 0.06287 0.05930 -0.1072 0.7951 0.0390
-8.000 -0.1311 0.06793 0.06400 -0.1218 0.7966 0.0330
-7.750 -0.1282 0.06355 0.05967 -0.1216 0.7948 0.0341
-7.500 -0.1248 0.06120 0.05730 -0.1211 0.7929 0.0350
-7.250 -0.1212 0.05912 0.05524 -0.1211 0.7894 0.0367
-7.000 -0.1197 0.05664 0.05268 -0.1210 0.7862 0.0381
-6.750 -0.1162 0.05403 0.04992 -0.1206 0.7835 0.0396
-6.500 -0.1105 0.05355 0.04884 -0.1190 0.7812 0.0449
-6.250 -0.1105 0.04851 0.04365 -0.1185 0.7788 0.0467
-6.000 -0.0970 0.04686 0.04219 -0.1186 0.7751 0.0515
-5.500 -0.0740 0.04246 0.03730 -0.1168 0.7696 0.0627
-5.250 -0.0592 0.04133 0.03562 -0.1153 0.7678 0.0734
-5.000 -0.0393 0.03853 0.03294 -0.1152 0.7666 0.0784
-4.750 -0.0311 0.03786 0.03211 -0.1140 0.7607 0.0895
-4.500 -0.0145 0.03655 0.03064 -0.1132 0.7579 0.1032
-4.250 0.0213 0.03166 0.02474 -0.1098 0.7562 0.0406
-4.000 0.0508 0.02992 0.02250 -0.1083 0.7547 0.0317
-3.750 0.0776 0.02783 0.02015 -0.1076 0.7536 0.0308
-3.500 0.0872 0.02790 0.02015 -0.1057 0.7475 0.0309
-3.250 0.1094 0.02755 0.01963 -0.1047 0.7446 0.0326
-3.000 0.1319 0.02594 0.01806 -0.1039 0.7428 0.0384
-2.750 0.1576 0.02508 0.01713 -0.1032 0.7413 0.0436
-2.500 0.1831 0.02421 0.01624 -0.1027 0.7402 0.0552
-2.250 0.1803 0.02555 0.01760 -0.0996 0.7322 0.0596
-2.000 0.2039 0.02499 0.01711 -0.0991 0.7300 0.0911
-1.750 0.2055 0.02263 0.01733 -0.0942 0.7283 0.7380
-1.500 0.2246 0.02287 0.01753 -0.0911 0.7271 0.8153
-1.250 0.2063 0.02485 0.01961 -0.0851 0.7178 0.8350
-1.000 0.2121 0.02504 0.01984 -0.0791 0.7156 0.8816
-0.750 0.2189 0.02497 0.01976 -0.0729 0.7142 0.9208
-0.500 0.1930 0.02680 0.02166 -0.0662 0.7046 0.9422
-0.250 0.2743 0.02711 0.02176 -0.0753 0.7048 0.9716
0.000 0.3303 0.02727 0.02174 -0.0809 0.7037 0.9764
0.250 0.3764 0.02737 0.02171 -0.0848 0.7027 0.9817
0.500 0.4274 0.02733 0.02155 -0.0895 0.7019 0.9847
0.750 0.4751 0.02721 0.02132 -0.0935 0.7012 0.9882
1.000 0.5204 0.02699 0.02102 -0.0969 0.7005 0.9920
1.250 0.5645 0.02680 0.02075 -0.1001 0.6999 0.9955
1.500 0.6085 0.02661 0.02050 -0.1034 0.6994 0.9988
1.750 0.5130 0.02948 0.02346 -0.0862 0.6849 1.0000
2.000 0.5619 0.02884 0.02275 -0.0892 0.6859 1.0000
2.250 0.5135 0.03095 0.02485 -0.0795 0.6741 1.0000
2.500 0.5498 0.03078 0.02462 -0.0809 0.6734 1.0000
2.750 0.5873 0.03055 0.02438 -0.0824 0.6728 1.0000
3.000 0.5652 0.03286 0.02667 -0.0775 0.6612 1.0000
3.250 0.5593 0.03470 0.02849 -0.0746 0.6521 1.0000
3.500 0.5883 0.03483 0.02860 -0.0751 0.6497 1.0000
3.750 0.6217 0.03472 0.02848 -0.0761 0.6483 1.0000
4.000 0.6350 0.03569 0.02943 -0.0750 0.6429 1.0000
4.250 0.6873 0.03457 0.02835 -0.0777 0.6454 1.0000
4.500 0.6821 0.03636 0.03013 -0.0748 0.6354 1.0000
4.750 0.7169 0.03611 0.02991 -0.0758 0.6343 1.0000
5.000 0.7528 0.03576 0.02958 -0.0768 0.6334 1.0000
5.250 0.7891 0.03540 0.02929 -0.0779 0.6327 1.0000
5.500 0.6843 0.02472 0.01902 -0.0633 0.5965 1.0000
5.750 0.7177 0.02433 0.01870 -0.0641 0.5950 1.0000
6.000 0.7523 0.02381 0.01822 -0.0649 0.5939 1.0000
6.250 0.7887 0.02316 0.01764 -0.0658 0.5931 1.0000
6.500 0.8259 0.02241 0.01699 -0.0668 0.5925 1.0000
6.750 0.8815 0.03945 0.03366 -0.0722 0.5962 1.0000
7.000 0.9178 0.03874 0.03304 -0.0729 0.5949 1.0000
7.250 0.9261 0.03984 0.03421 -0.0714 0.5863 1.0000
7.500 0.9625 0.03879 0.03327 -0.0719 0.5836 1.0000
7.750 1.0175 0.03592 0.03058 -0.0735 0.5832 1.0000
8.000 1.0720 0.03299 0.02783 -0.0752 0.5833 1.0000
8.250 1.2244 0.01987 0.01486 -0.0830 0.5594 1.0000
8.500 1.2236 0.02000 0.01467 -0.0785 0.4936 1.0000
8.750 1.2096 0.02160 0.01566 -0.0731 0.4101 1.0000
9.000 1.1869 0.02425 0.01788 -0.0679 0.3494 1.0000
9.250 1.1635 0.02727 0.02050 -0.0631 0.2918 1.0000
9.500 1.1410 0.03050 0.02334 -0.0589 0.2304 1.0000
9.750 1.1152 0.03426 0.02657 -0.0548 0.1549 1.0000
10.000 1.0959 0.03786 0.02965 -0.0517 0.0808 1.0000
10.250 1.0801 0.04142 0.03281 -0.0489 0.0296 1.0000
10.500 1.0809 0.04379 0.03522 -0.0472 0.0195 1.0000
10.750 1.0843 0.04598 0.03751 -0.0459 0.0171 1.0000
11.000 1.0858 0.04841 0.04009 -0.0446 0.0157 1.0000
11.250 1.0892 0.05073 0.04255 -0.0435 0.0150 1.0000
11.500 1.0920 0.05314 0.04508 -0.0424 0.0146 1.0000
11.750 1.0939 0.05569 0.04774 -0.0414 0.0142 1.0000
12.000 1.0974 0.05808 0.05022 -0.0403 0.0139 1.0000
12.250 1.1030 0.06025 0.05248 -0.0393 0.0137 1.0000
12.500 1.1123 0.06203 0.05434 -0.0380 0.0136 1.0000
12.750 1.1278 0.06322 0.05559 -0.0367 0.0136 1.0000
13.000 1.1524 0.06378 0.05629 -0.0352 0.0137 1.0000
13.250 1.1855 0.06434 0.05703 -0.0339 0.0141 1.0000
13.500 1.2231 0.06610 0.05907 -0.0328 0.0148 1.0000
13.750 1.2321 0.06872 0.06195 -0.0320 0.0142 1.0000
14.000 1.2377 0.07167 0.06515 -0.0313 0.0137 1.0000
14.250 1.2416 0.07529 0.06907 -0.0304 0.0138 1.0000
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