FX 67-K-170/17 AIRFOIL (fx67k170-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 67-K-170/17 AIRFOIL (fx67k170-il) Reynolds number: 1,000,000 Max Cl/Cd: 141.35 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx67k170-il-1000000-n5.txt Download as CSV file: xf-fx67k170-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4985 0.04529 0.04209 -0.1262 0.7176 0.0038
-13.250 -0.5147 0.04092 0.03759 -0.1283 0.7160 0.0038
-13.000 -0.5345 0.03701 0.03352 -0.1287 0.7141 0.0038
-12.750 -0.5476 0.03416 0.03052 -0.1279 0.7124 0.0039
-12.500 -0.5703 0.03077 0.02691 -0.1257 0.7108 0.0038
-12.250 -0.5860 0.02815 0.02407 -0.1228 0.7090 0.0038
-12.000 -0.5726 0.02772 0.02364 -0.1217 0.7074 0.0040
-11.750 -0.5774 0.02611 0.02187 -0.1185 0.7056 0.0040
-11.500 -0.5799 0.02474 0.02033 -0.1150 0.7038 0.0040
-11.250 -0.5650 0.02413 0.01965 -0.1138 0.7020 0.0041
-11.000 -0.5550 0.02294 0.01830 -0.1121 0.7003 0.0043
-10.500 -0.5272 0.02079 0.01585 -0.1094 0.6972 0.0044
-10.250 -0.5105 0.01982 0.01473 -0.1083 0.6958 0.0045
-10.000 -0.4924 0.01889 0.01367 -0.1074 0.6943 0.0046
-9.750 -0.4728 0.01809 0.01274 -0.1066 0.6926 0.0048
-9.500 -0.4522 0.01735 0.01188 -0.1060 0.6909 0.0049
-9.250 -0.4311 0.01664 0.01104 -0.1053 0.6891 0.0049
-9.000 -0.4091 0.01601 0.01030 -0.1048 0.6874 0.0050
-8.750 -0.3857 0.01554 0.00974 -0.1044 0.6858 0.0051
-8.500 -0.3625 0.01502 0.00912 -0.1040 0.6843 0.0052
-8.250 -0.3393 0.01443 0.00844 -0.1036 0.6830 0.0053
-8.000 -0.3164 0.01380 0.00773 -0.1032 0.6815 0.0055
-7.750 -0.2924 0.01330 0.00717 -0.1029 0.6799 0.0057
-7.500 -0.2675 0.01290 0.00672 -0.1027 0.6781 0.0059
-7.250 -0.2424 0.01253 0.00629 -0.1026 0.6762 0.0061
-7.000 -0.2168 0.01221 0.00592 -0.1025 0.6746 0.0064
-6.750 -0.1910 0.01190 0.00556 -0.1024 0.6730 0.0067
-6.500 -0.1652 0.01161 0.00521 -0.1023 0.6715 0.0070
-6.250 -0.1390 0.01135 0.00490 -0.1023 0.6700 0.0074
-6.000 -0.1127 0.01104 0.00458 -0.1023 0.6686 0.0080
-5.750 -0.0859 0.01081 0.00435 -0.1025 0.6670 0.0087
-5.500 -0.0588 0.01060 0.00412 -0.1026 0.6652 0.0095
-5.250 -0.0317 0.01040 0.00390 -0.1027 0.6633 0.0104
-5.000 -0.0043 0.01026 0.00377 -0.1029 0.6616 0.0116
-4.750 0.0233 0.01014 0.00362 -0.1031 0.6600 0.0132
-4.500 0.0508 0.01000 0.00346 -0.1033 0.6584 0.0143
-4.250 0.0781 0.00985 0.00329 -0.1035 0.6568 0.0155
-4.000 0.1059 0.00971 0.00314 -0.1038 0.6554 0.0166
-3.750 0.1338 0.00959 0.00302 -0.1041 0.6539 0.0178
-3.500 0.1620 0.00950 0.00291 -0.1044 0.6521 0.0185
-3.250 0.1894 0.00931 0.00271 -0.1046 0.6502 0.0199
-3.000 0.2172 0.00917 0.00256 -0.1049 0.6484 0.0212
-2.750 0.2450 0.00906 0.00243 -0.1052 0.6467 0.0226
-2.500 0.2730 0.00896 0.00231 -0.1055 0.6451 0.0238
-2.250 0.3009 0.00889 0.00221 -0.1058 0.6434 0.0248
-2.000 0.3290 0.00880 0.00212 -0.1061 0.6419 0.0286
-1.750 0.3569 0.00865 0.00205 -0.1064 0.6403 0.0464
-1.500 0.3838 0.00838 0.00196 -0.1066 0.6384 0.1091
-1.250 0.4095 0.00796 0.00187 -0.1068 0.6365 0.2184
-1.000 0.4330 0.00726 0.00177 -0.1068 0.6347 0.4134
-0.750 0.4577 0.00677 0.00171 -0.1068 0.6330 0.5554
-0.500 0.4835 0.00650 0.00171 -0.1067 0.6313 0.6476
-0.250 0.5101 0.00640 0.00177 -0.1067 0.6296 0.7130
0.000 0.5381 0.00642 0.00184 -0.1070 0.6279 0.7400
0.250 0.5667 0.00645 0.00189 -0.1074 0.6261 0.7543
0.500 0.5954 0.00649 0.00193 -0.1078 0.6243 0.7656
0.750 0.6240 0.00654 0.00199 -0.1082 0.6225 0.7768
1.000 0.6525 0.00658 0.00203 -0.1086 0.6207 0.7813
1.250 0.6810 0.00663 0.00208 -0.1090 0.6188 0.7858
1.500 0.7095 0.00669 0.00211 -0.1094 0.6169 0.7897
1.750 0.7377 0.00676 0.00215 -0.1098 0.6147 0.7928
2.000 0.7660 0.00678 0.00220 -0.1102 0.6108 0.7957
2.250 0.7938 0.00683 0.00225 -0.1105 0.6057 0.7989
2.500 0.8216 0.00690 0.00230 -0.1109 0.6028 0.8021
2.750 0.8494 0.00697 0.00236 -0.1112 0.6002 0.8049
3.000 0.8778 0.00702 0.00243 -0.1117 0.5975 0.8072
3.250 0.9057 0.00707 0.00250 -0.1120 0.5945 0.8093
3.500 0.9331 0.00713 0.00258 -0.1123 0.5911 0.8114
3.750 0.9598 0.00722 0.00266 -0.1125 0.5872 0.8135
4.000 0.9871 0.00729 0.00275 -0.1127 0.5827 0.8157
4.250 1.0132 0.00739 0.00285 -0.1128 0.5753 0.8181
4.500 1.0390 0.00751 0.00296 -0.1128 0.5683 0.8206
5.000 1.0897 0.00774 0.00320 -0.1127 0.5554 0.8249
5.250 1.1138 0.00788 0.00335 -0.1124 0.5466 0.8269
5.500 1.1369 0.00806 0.00352 -0.1119 0.5365 0.8290
5.750 1.1557 0.00834 0.00376 -0.1106 0.5196 0.8314
6.000 1.1675 0.00880 0.00412 -0.1081 0.4942 0.8341
6.250 1.1663 0.00943 0.00462 -0.1030 0.4640 0.8373
6.500 1.1494 0.01040 0.00549 -0.0954 0.4338 0.8415
6.750 1.1354 0.01178 0.00678 -0.0893 0.4077 0.8464
7.000 1.1220 0.01342 0.00830 -0.0838 0.3779 0.8510
7.250 1.1157 0.01484 0.00964 -0.0795 0.3542 0.8551
7.500 1.1063 0.01646 0.01114 -0.0749 0.3252 0.8603
7.750 1.0951 0.01825 0.01278 -0.0703 0.2909 0.8661
8.000 1.0806 0.02027 0.01462 -0.0655 0.2516 0.8725
8.250 1.0706 0.02216 0.01635 -0.0614 0.2144 0.8797
8.500 1.0757 0.02333 0.01749 -0.0592 0.1984 0.8870
8.750 1.0669 0.02535 0.01936 -0.0557 0.1585 0.8995
9.000 1.0698 0.02690 0.02086 -0.0537 0.1310 0.9239
9.250 1.0841 0.02962 0.02338 -0.0561 0.0794 0.9564
9.500 1.0817 0.03216 0.02567 -0.0546 0.0351 1.0000
9.750 1.0980 0.03301 0.02655 -0.0542 0.0354 1.0000
10.000 1.1122 0.03401 0.02755 -0.0535 0.0337 1.0000
10.250 1.1255 0.03509 0.02866 -0.0528 0.0323 1.0000
10.500 1.1386 0.03620 0.02977 -0.0521 0.0305 1.0000
10.750 1.1531 0.03720 0.03080 -0.0516 0.0302 1.0000
11.000 1.1664 0.03831 0.03194 -0.0510 0.0288 1.0000
11.250 1.1791 0.03950 0.03316 -0.0503 0.0274 1.0000
11.500 1.1938 0.04052 0.03421 -0.0499 0.0265 1.0000
11.750 1.2080 0.04158 0.03531 -0.0494 0.0259 1.0000
12.000 1.2203 0.04282 0.03657 -0.0488 0.0227 1.0000
12.250 1.2306 0.04422 0.03796 -0.0481 0.0185 1.0000
12.500 1.2342 0.04619 0.03983 -0.0470 0.0079 1.0000
12.750 1.2390 0.04814 0.04178 -0.0459 0.0036 1.0000
13.000 1.2493 0.04961 0.04328 -0.0454 0.0031 1.0000
13.250 1.2585 0.05120 0.04491 -0.0447 0.0026 1.0000
13.500 1.2681 0.05278 0.04654 -0.0442 0.0024 1.0000
13.750 1.2780 0.05434 0.04815 -0.0437 0.0022 1.0000
14.000 1.2871 0.05600 0.04986 -0.0432 0.0021 1.0000
14.250 1.2959 0.05773 0.05163 -0.0427 0.0021 1.0000
14.500 1.3045 0.05946 0.05342 -0.0423 0.0019 1.0000
14.750 1.3105 0.06149 0.05550 -0.0418 0.0018 1.0000
15.000 1.3173 0.06346 0.05754 -0.0413 0.0017 1.0000
15.250 1.3232 0.06557 0.05972 -0.0409 0.0016 1.0000
15.500 1.3292 0.06771 0.06192 -0.0406 0.0016 1.0000
15.750 1.3361 0.06976 0.06403 -0.0403 0.0016 1.0000
16.000 1.3417 0.07198 0.06631 -0.0401 0.0015 1.0000
16.250 1.3483 0.07410 0.06849 -0.0400 0.0015 1.0000
16.500 1.3535 0.07643 0.07088 -0.0398 0.0014 1.0000
16.750 1.3586 0.07882 0.07334 -0.0398 0.0014 1.0000
17.000 1.3625 0.08135 0.07595 -0.0398 0.0014 1.0000
17.250 1.3654 0.08409 0.07877 -0.0398 0.0013 1.0000
17.500 1.3691 0.08670 0.08145 -0.0400 0.0012 1.0000
17.750 1.3738 0.08924 0.08406 -0.0403 0.0012 1.0000
18.000 1.3758 0.09216 0.08706 -0.0405 0.0011 1.0000
18.250 1.3767 0.09531 0.09030 -0.0409 0.0012 1.0000
18.500 1.3771 0.09855 0.09362 -0.0414 0.0011 1.0000
18.750 1.3791 0.10159 0.09673 -0.0420 0.0011 1.0000
19.000 1.3791 0.10495 0.10018 -0.0426 0.0010 1.0000
19.250 1.3807 0.10810 0.10340 -0.0434 0.0010 1.0000
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