HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: HQ 3.5/9 AIRFOIL (hq359-il) Reynolds number: 1,000,000 Max Cl/Cd: 140.62 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hq359-il-1000000.txt Download as CSV file: xf-hq359-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.5/9 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2350 0.08096 0.07949 -0.0476 0.9934 0.0070
-8.750 -0.2285 0.07626 0.07479 -0.0503 0.9906 0.0070
-8.500 -0.2320 0.06921 0.06776 -0.0538 0.9877 0.0073
-8.250 -0.2247 0.06458 0.06314 -0.0571 0.9851 0.0075
-8.000 -0.2150 0.05992 0.05848 -0.0611 0.9830 0.0077
-7.750 -0.2037 0.05618 0.05473 -0.0644 0.9785 0.0080
-7.500 -0.1912 0.05189 0.05044 -0.0690 0.9732 0.0083
-7.250 -0.1820 0.04687 0.04541 -0.0747 0.9638 0.0085
-7.000 -0.1780 0.04191 0.04043 -0.0809 0.9493 0.0087
-6.750 -0.1765 0.03622 0.03465 -0.0883 0.9344 0.0087
-6.500 -0.1709 0.03135 0.02966 -0.0922 0.9230 0.0088
-6.250 -0.1611 0.02700 0.02515 -0.0949 0.9139 0.0091
-6.000 -0.1481 0.02274 0.02072 -0.0969 0.9053 0.0093
-5.750 -0.1315 0.01877 0.01654 -0.0985 0.8985 0.0099
-5.500 -0.1106 0.01546 0.01301 -0.0994 0.8921 0.0108
-5.250 -0.0855 0.01376 0.01113 -0.0994 0.8868 0.0115
-5.000 -0.0631 0.01104 0.00812 -0.1000 0.8808 0.0116
-4.750 -0.0444 0.00598 0.00241 -0.1018 0.8760 0.0127
-4.250 0.0153 0.01111 0.00638 -0.1068 0.8784 0.0076
-4.000 0.0417 0.00986 0.00493 -0.1065 0.8732 0.0079
-3.750 0.0687 0.00924 0.00424 -0.1063 0.8673 0.0089
-3.500 0.0959 0.00879 0.00370 -0.1062 0.8617 0.0097
-3.250 0.1233 0.00832 0.00315 -0.1061 0.8558 0.0102
-3.000 0.1507 0.00798 0.00272 -0.1059 0.8488 0.0109
-2.750 0.1782 0.00771 0.00238 -0.1058 0.8405 0.0114
-2.500 0.2056 0.00740 0.00195 -0.1055 0.8314 0.0116
-2.250 0.2334 0.00707 0.00149 -0.1053 0.8222 0.0142
-2.000 0.2611 0.00681 0.00131 -0.1053 0.8142 0.0436
-1.750 0.2888 0.00668 0.00121 -0.1053 0.8065 0.0670
-1.500 0.3165 0.00642 0.00111 -0.1054 0.7982 0.1281
-1.250 0.3428 0.00555 0.00099 -0.1057 0.7899 0.4064
-1.000 0.3694 0.00516 0.00100 -0.1057 0.7812 0.5630
-0.750 0.3970 0.00509 0.00100 -0.1056 0.7727 0.6079
-0.500 0.4244 0.00508 0.00099 -0.1054 0.7631 0.6378
-0.250 0.4517 0.00508 0.00100 -0.1053 0.7521 0.6666
0.000 0.4790 0.00506 0.00102 -0.1051 0.7420 0.6961
0.250 0.5062 0.00506 0.00106 -0.1049 0.7326 0.7257
0.500 0.5333 0.00509 0.00108 -0.1046 0.7220 0.7465
1.000 0.5879 0.00517 0.00112 -0.1044 0.6983 0.7672
1.250 0.6151 0.00522 0.00115 -0.1042 0.6854 0.7782
1.750 0.6687 0.00535 0.00123 -0.1037 0.6560 0.8027
2.000 0.6952 0.00541 0.00129 -0.1034 0.6389 0.8174
2.250 0.7211 0.00548 0.00136 -0.1030 0.6188 0.8356
2.500 0.7459 0.00555 0.00143 -0.1024 0.5955 0.8621
2.750 0.7734 0.00550 0.00149 -0.1023 0.5649 1.0000
3.000 0.7986 0.00577 0.00161 -0.1019 0.5286 1.0000
3.250 0.8233 0.00611 0.00175 -0.1014 0.4865 1.0000
3.500 0.8476 0.00648 0.00195 -0.1009 0.4433 1.0000
3.750 0.8720 0.00686 0.00214 -0.1004 0.4027 1.0000
4.000 0.8963 0.00724 0.00235 -0.0999 0.3637 1.0000
4.250 0.9202 0.00767 0.00258 -0.0993 0.3199 1.0000
4.500 0.9442 0.00808 0.00284 -0.0988 0.2860 1.0000
4.750 0.9691 0.00840 0.00306 -0.0984 0.2645 1.0000
5.000 0.9935 0.00875 0.00330 -0.0979 0.2421 1.0000
5.250 1.0187 0.00902 0.00351 -0.0976 0.2245 1.0000
5.500 1.0439 0.00930 0.00373 -0.0973 0.2081 1.0000
5.750 1.0676 0.00970 0.00401 -0.0967 0.1789 1.0000
6.000 1.0891 0.01031 0.00437 -0.0959 0.1360 1.0000
6.250 1.1091 0.01108 0.00486 -0.0948 0.0897 1.0000
6.500 1.1266 0.01210 0.00556 -0.0933 0.0384 1.0000
6.750 1.1446 0.01311 0.00636 -0.0917 0.0061 1.0000
7.000 1.1674 0.01360 0.00688 -0.0909 0.0047 1.0000
7.250 1.1899 0.01410 0.00748 -0.0900 0.0042 1.0000
7.500 1.2116 0.01469 0.00816 -0.0890 0.0039 1.0000
7.750 1.2320 0.01539 0.00897 -0.0878 0.0038 1.0000
8.000 1.2513 0.01617 0.00986 -0.0864 0.0038 1.0000
8.250 1.2681 0.01715 0.01097 -0.0846 0.0037 1.0000
8.500 1.2830 0.01825 0.01219 -0.0826 0.0036 1.0000
8.750 1.3018 0.01890 0.01291 -0.0812 0.0035 1.0000
9.000 1.3177 0.01976 0.01386 -0.0795 0.0034 1.0000
9.250 1.3308 0.02081 0.01501 -0.0772 0.0034 1.0000
9.500 1.3397 0.02193 0.01626 -0.0743 0.0034 1.0000
9.750 1.3488 0.02297 0.01740 -0.0714 0.0033 1.0000
10.000 1.3555 0.02424 0.01878 -0.0684 0.0033 1.0000
10.250 1.3619 0.02560 0.02026 -0.0655 0.0032 1.0000
10.500 1.3706 0.02677 0.02153 -0.0631 0.0031 1.0000
10.750 1.3750 0.02844 0.02334 -0.0603 0.0031 1.0000
11.000 1.3807 0.03000 0.02502 -0.0578 0.0029 1.0000
11.250 1.3832 0.03201 0.02718 -0.0552 0.0029 1.0000
11.500 1.3871 0.03378 0.02907 -0.0531 0.0027 1.0000
11.750 1.3899 0.03564 0.03106 -0.0511 0.0026 1.0000
12.000 1.3880 0.03827 0.03385 -0.0489 0.0025 1.0000
12.250 1.3868 0.04076 0.03648 -0.0471 0.0025 1.0000
12.500 1.3780 0.04449 0.04045 -0.0452 0.0025 1.0000
12.750 1.3642 0.04907 0.04530 -0.0435 0.0026 1.0000
13.000 1.3437 0.05480 0.05134 -0.0425 0.0028 1.0000
13.250 1.3215 0.06098 0.05780 -0.0426 0.0029 1.0000
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