FX 67-K-150/17 AIRFOIL (fx67k150-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 67-K-150/17 AIRFOIL (fx67k150-il) Reynolds number: 1,000,000 Max Cl/Cd: 157.21 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx67k150-il-1000000.txt Download as CSV file: xf-fx67k150-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0948 0.08410 0.08126 -0.1002 0.7311 0.0065
-9.500 -0.0933 0.08036 0.07753 -0.1019 0.7296 0.0069
-9.250 -0.0923 0.07624 0.07342 -0.1040 0.7280 0.0074
-9.000 -0.0920 0.07263 0.06980 -0.1058 0.7261 0.0073
-8.750 -0.0887 0.06875 0.06597 -0.1081 0.7247 0.0077
-8.500 -0.0929 0.06441 0.06166 -0.1108 0.7228 0.0076
-5.500 -0.0646 0.01888 0.01390 -0.1054 0.7009 0.0066
-5.250 -0.0411 0.01695 0.01165 -0.1046 0.6991 0.0070
-5.000 -0.0164 0.01534 0.00983 -0.1041 0.6977 0.0072
-4.750 0.0093 0.01416 0.00850 -0.1039 0.6960 0.0073
-4.500 0.0356 0.01325 0.00747 -0.1037 0.6941 0.0075
-4.250 0.0630 0.01287 0.00701 -0.1038 0.6923 0.0080
-4.000 0.0877 0.01166 0.00569 -0.1033 0.6907 0.0081
-3.750 0.1124 0.01074 0.00467 -0.1029 0.6891 0.0082
-3.500 0.1371 0.00993 0.00373 -0.1025 0.6874 0.0087
-3.250 0.1642 0.00960 0.00334 -0.1026 0.6856 0.0103
-3.000 0.1923 0.00944 0.00318 -0.1028 0.6840 0.0128
-2.750 0.2195 0.00909 0.00282 -0.1029 0.6821 0.0200
-2.500 0.2476 0.00894 0.00264 -0.1032 0.6803 0.0230
-2.250 0.2756 0.00874 0.00243 -0.1035 0.6785 0.0300
-2.000 0.3037 0.00856 0.00225 -0.1038 0.6768 0.0442
-1.750 0.3272 0.00758 0.00203 -0.1039 0.6751 0.2975
-1.500 0.3512 0.00681 0.00193 -0.1040 0.6731 0.5240
-1.250 0.3768 0.00639 0.00192 -0.1039 0.6714 0.6573
-1.000 0.4035 0.00625 0.00199 -0.1038 0.6697 0.7353
-0.750 0.4313 0.00627 0.00206 -0.1039 0.6678 0.7709
-0.500 0.4595 0.00631 0.00210 -0.1041 0.6658 0.7902
-0.250 0.4875 0.00637 0.00216 -0.1042 0.6639 0.8052
0.000 0.5160 0.00642 0.00218 -0.1045 0.6622 0.8134
0.250 0.5446 0.00648 0.00220 -0.1049 0.6602 0.8190
0.500 0.5730 0.00652 0.00224 -0.1053 0.6583 0.8239
0.750 0.6017 0.00655 0.00227 -0.1057 0.6565 0.8289
1.000 0.6301 0.00657 0.00229 -0.1060 0.6545 0.8331
1.250 0.6586 0.00659 0.00232 -0.1064 0.6524 0.8373
1.500 0.6872 0.00662 0.00234 -0.1068 0.6504 0.8416
1.750 0.7158 0.00666 0.00236 -0.1073 0.6485 0.8453
2.000 0.7442 0.00673 0.00241 -0.1077 0.6462 0.8488
2.250 0.7723 0.00675 0.00247 -0.1080 0.6442 0.8525
2.500 0.8007 0.00678 0.00252 -0.1085 0.6419 0.8560
2.750 0.8291 0.00680 0.00256 -0.1089 0.6394 0.8591
3.000 0.8571 0.00681 0.00259 -0.1092 0.6370 0.8621
3.250 0.8852 0.00685 0.00262 -0.1096 0.6340 0.8653
3.500 0.9129 0.00687 0.00267 -0.1099 0.6297 0.8686
3.750 0.9408 0.00687 0.00271 -0.1102 0.6249 0.8717
4.000 0.9683 0.00689 0.00275 -0.1105 0.6217 0.8748
4.250 0.9958 0.00695 0.00282 -0.1107 0.6183 0.8780
4.500 1.0232 0.00697 0.00290 -0.1110 0.6142 0.8814
4.750 1.0507 0.00701 0.00298 -0.1113 0.6097 0.8847
5.000 1.0773 0.00706 0.00305 -0.1114 0.6044 0.8880
5.250 1.1027 0.00708 0.00310 -0.1112 0.5936 0.8917
5.500 1.1272 0.00717 0.00318 -0.1109 0.5783 0.8956
5.750 1.1497 0.00736 0.00332 -0.1103 0.5540 0.8999
6.000 1.1670 0.00773 0.00359 -0.1086 0.5176 0.9049
6.250 1.1646 0.00887 0.00434 -0.1036 0.4366 0.9138
6.500 1.1521 0.01004 0.00522 -0.0966 0.3706 0.9289
6.750 1.1321 0.01163 0.00655 -0.0894 0.3019 1.0000
7.000 1.1073 0.01400 0.00858 -0.0829 0.2380 1.0000
7.250 1.0881 0.01639 0.01063 -0.0776 0.1738 1.0000
7.500 1.0749 0.01860 0.01253 -0.0731 0.1176 1.0000
7.750 1.0506 0.02156 0.01505 -0.0676 0.0346 1.0000
8.000 1.0503 0.02324 0.01660 -0.0650 0.0055 1.0000
8.250 1.0639 0.02411 0.01750 -0.0639 0.0048 1.0000
8.500 1.0752 0.02515 0.01859 -0.0625 0.0040 1.0000
8.750 1.0875 0.02613 0.01962 -0.0613 0.0038 1.0000
9.000 1.0990 0.02718 0.02073 -0.0601 0.0037 1.0000
9.250 1.1098 0.02832 0.02194 -0.0588 0.0036 1.0000
9.500 1.1204 0.02950 0.02318 -0.0576 0.0036 1.0000
9.750 1.1285 0.03091 0.02466 -0.0562 0.0035 1.0000
10.000 1.1379 0.03226 0.02607 -0.0549 0.0035 1.0000
10.250 1.1381 0.03436 0.02829 -0.0530 0.0032 1.0000
10.500 1.1446 0.03602 0.03002 -0.0516 0.0033 1.0000
10.750 1.1530 0.03756 0.03161 -0.0506 0.0031 1.0000
11.000 1.1568 0.03952 0.03366 -0.0491 0.0031 1.0000
11.250 1.1599 0.04159 0.03581 -0.0477 0.0031 1.0000
11.500 1.1692 0.04314 0.03741 -0.0469 0.0030 1.0000
11.750 1.1733 0.04520 0.03955 -0.0456 0.0030 1.0000
12.000 1.1807 0.04698 0.04139 -0.0447 0.0030 1.0000
12.250 1.1849 0.04905 0.04357 -0.0435 0.0030 1.0000
12.500 1.1958 0.05059 0.04517 -0.0430 0.0028 1.0000
12.750 1.2046 0.05232 0.04696 -0.0423 0.0026 1.0000
13.000 1.2124 0.05416 0.04888 -0.0415 0.0025 1.0000
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Polar data table (+)
Polar graphs
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