FX 67-K-150/17 AIRFOIL (fx67k150-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 67-K-150/17 AIRFOIL (fx67k150-il) Reynolds number: 500,000 Max Cl/Cd: 126.26 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx67k150-il-500000.txt Download as CSV file: xf-fx67k150-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.1266 0.03100 0.02748 -0.1079 0.7330 0.0135
-6.750 -0.1249 0.02723 0.02355 -0.1071 0.7311 0.0138
-6.500 -0.1166 0.02427 0.02046 -0.1066 0.7294 0.0142
-6.250 -0.1051 0.02171 0.01775 -0.1061 0.7278 0.0147
-6.000 -0.0916 0.01929 0.01513 -0.1055 0.7264 0.0154
-5.750 -0.0760 0.01700 0.01265 -0.1049 0.7245 0.0164
-5.500 -0.0579 0.01488 0.01031 -0.1042 0.7225 0.0178
-5.250 -0.0289 0.01545 0.01066 -0.1033 0.7203 0.0210
-4.750 0.0032 0.00902 0.00351 -0.1022 0.7171 0.0237
-4.500 0.0272 0.00819 0.00261 -0.1024 0.7155 0.0265
-4.250 0.0605 0.01774 0.01133 -0.1056 0.7170 0.0159
-4.000 0.0879 0.01606 0.00936 -0.1048 0.7155 0.0138
-3.750 0.1139 0.01491 0.00809 -0.1044 0.7141 0.0138
-3.500 0.1385 0.01387 0.00694 -0.1039 0.7127 0.0146
-3.250 0.1634 0.01329 0.00637 -0.1036 0.7107 0.0168
-3.000 0.1894 0.01288 0.00592 -0.1035 0.7086 0.0203
-2.750 0.2148 0.01229 0.00529 -0.1033 0.7065 0.0291
-2.500 0.2418 0.01195 0.00488 -0.1034 0.7046 0.0360
-2.250 0.2694 0.01167 0.00456 -0.1035 0.7030 0.0478
-2.000 0.2892 0.01005 0.00418 -0.1033 0.7015 0.4111
-1.750 0.3102 0.00919 0.00416 -0.1025 0.7001 0.6694
-1.500 0.3355 0.00920 0.00433 -0.1019 0.6984 0.7445
-1.250 0.3608 0.00934 0.00453 -0.1014 0.6960 0.7882
-1.000 0.3860 0.00949 0.00470 -0.1006 0.6938 0.8150
-0.750 0.4123 0.00960 0.00478 -0.1003 0.6919 0.8300
-0.500 0.4376 0.00969 0.00487 -0.0996 0.6902 0.8450
-0.250 0.4647 0.00971 0.00485 -0.0994 0.6887 0.8526
0.000 0.4931 0.00974 0.00480 -0.0997 0.6872 0.8592
0.250 0.5201 0.00980 0.00484 -0.0997 0.6855 0.8647
0.500 0.5467 0.00987 0.00492 -0.0997 0.6832 0.8710
0.750 0.5728 0.00990 0.00496 -0.0996 0.6809 0.8759
1.000 0.5999 0.00992 0.00497 -0.0997 0.6787 0.8813
1.250 0.6280 0.00993 0.00496 -0.1000 0.6769 0.8864
1.500 0.6553 0.00992 0.00493 -0.1001 0.6753 0.8908
1.750 0.6837 0.00993 0.00492 -0.1004 0.6738 0.8955
2.000 0.7115 0.01001 0.00498 -0.1007 0.6719 0.9000
2.250 0.7364 0.01005 0.00509 -0.1005 0.6693 0.9041
2.500 0.7628 0.01009 0.00516 -0.1005 0.6668 0.9087
2.750 0.7906 0.01011 0.00518 -0.1009 0.6646 0.9132
3.000 0.8178 0.01007 0.00517 -0.1009 0.6626 0.9171
3.250 0.8460 0.01006 0.00515 -0.1013 0.6608 0.9215
3.500 0.8737 0.01013 0.00522 -0.1016 0.6587 0.9262
3.750 0.8975 0.01017 0.00535 -0.1012 0.6556 0.9310
4.000 0.9232 0.01018 0.00544 -0.1011 0.6527 0.9363
4.250 0.9507 0.01016 0.00545 -0.1013 0.6502 0.9415
4.500 0.9799 0.01001 0.00527 -0.1017 0.6469 0.9463
4.750 1.0037 0.00997 0.00533 -0.1013 0.6418 0.9536
5.000 1.0319 0.00988 0.00531 -0.1016 0.6374 0.9599
5.250 1.0631 0.00981 0.00525 -0.1026 0.6340 0.9665
5.500 1.0950 0.00985 0.00538 -0.1040 0.6295 0.9737
5.750 1.1290 0.00970 0.00528 -0.1057 0.6219 0.9817
6.250 1.1865 0.00950 0.00518 -0.1070 0.5960 1.0000
6.500 1.2058 0.00955 0.00517 -0.1058 0.5681 1.0000
6.750 1.2202 0.00992 0.00539 -0.1039 0.5286 1.0000
7.000 1.2125 0.01103 0.00612 -0.0982 0.4594 1.0000
7.250 1.1876 0.01255 0.00733 -0.0899 0.4065 1.0000
7.500 1.1667 0.01464 0.00918 -0.0838 0.3608 1.0000
7.750 1.1431 0.01726 0.01147 -0.0780 0.3035 1.0000
8.000 1.1221 0.01992 0.01379 -0.0728 0.2435 1.0000
8.250 1.1089 0.02229 0.01585 -0.0687 0.1906 1.0000
8.500 1.0804 0.02571 0.01874 -0.0634 0.1032 1.0000
8.750 1.0618 0.02872 0.02132 -0.0593 0.0326 1.0000
9.000 1.0636 0.03052 0.02301 -0.0573 0.0095 1.0000
9.250 1.0743 0.03175 0.02430 -0.0561 0.0079 1.0000
9.500 1.0851 0.03301 0.02566 -0.0550 0.0072 1.0000
9.750 1.0938 0.03447 0.02721 -0.0537 0.0065 1.0000
10.000 1.1032 0.03590 0.02873 -0.0525 0.0063 1.0000
10.250 1.1110 0.03750 0.03042 -0.0513 0.0062 1.0000
10.500 1.1153 0.03944 0.03247 -0.0499 0.0060 1.0000
10.750 1.1215 0.04126 0.03437 -0.0487 0.0061 1.0000
11.000 1.1246 0.04339 0.03660 -0.0474 0.0060 1.0000
11.250 1.1279 0.04557 0.03888 -0.0461 0.0060 1.0000
11.500 1.1331 0.04760 0.04099 -0.0451 0.0060 1.0000
11.750 1.1351 0.04996 0.04344 -0.0438 0.0060 1.0000
12.000 1.1360 0.05241 0.04599 -0.0424 0.0058 1.0000
12.250 1.1417 0.05441 0.04806 -0.0411 0.0057 1.0000
12.500 1.1544 0.05590 0.04964 -0.0409 0.0053 1.0000
12.750 1.1635 0.05765 0.05150 -0.0400 0.0052 1.0000
13.000 1.1739 0.05929 0.05324 -0.0390 0.0051 1.0000
13.250 1.1877 0.06066 0.05471 -0.0378 0.0053 1.0000
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Polar data table (+)
Polar graphs
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