HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/9 AIRFOIL (hq309-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.22 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq309-il-1000000-n5.txt Download as CSV file: xf-hq309-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/9 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3875 0.10802 0.10635 -0.0290 1.0000 0.0023
-10.000 -0.3912 0.10218 0.10053 -0.0308 1.0000 0.0021
-9.750 -0.3913 0.09778 0.09615 -0.0322 1.0000 0.0020
-9.500 -0.3889 0.09461 0.09300 -0.0333 1.0000 0.0021
-9.250 -0.3919 0.08990 0.08831 -0.0347 1.0000 0.0020
-9.000 -0.3900 0.08714 0.08557 -0.0356 1.0000 0.0021
-8.500 -0.3829 0.07901 0.07749 -0.0409 0.9913 0.0022
-8.250 -0.3712 0.07418 0.07266 -0.0467 0.9842 0.0023
-8.000 -0.3573 0.06758 0.06607 -0.0560 0.9753 0.0024
-7.750 -0.3333 0.05784 0.05628 -0.0745 0.9620 0.0024
-7.500 -0.3175 0.04980 0.04808 -0.0855 0.9427 0.0026
-7.250 -0.3102 0.04317 0.04121 -0.0900 0.9227 0.0027
-7.000 -0.3046 0.03567 0.03336 -0.0923 0.9070 0.0029
-6.500 -0.2899 0.01555 0.01148 -0.0923 0.8844 0.0032
-6.000 -0.2392 0.01350 0.00901 -0.0919 0.8717 0.0036
-5.750 -0.2129 0.01283 0.00816 -0.0917 0.8655 0.0038
-5.500 -0.1865 0.01210 0.00728 -0.0916 0.8595 0.0039
-5.250 -0.1608 0.01100 0.00596 -0.0913 0.8532 0.0041
-5.000 -0.1352 0.00992 0.00469 -0.0911 0.8474 0.0046
-4.750 -0.1082 0.00952 0.00424 -0.0910 0.8413 0.0050
-4.500 -0.0810 0.00918 0.00382 -0.0909 0.8356 0.0054
-4.250 -0.0536 0.00883 0.00340 -0.0908 0.8294 0.0059
-4.000 -0.0263 0.00852 0.00299 -0.0907 0.8231 0.0063
-3.750 0.0013 0.00828 0.00269 -0.0907 0.8168 0.0067
-3.500 0.0289 0.00808 0.00243 -0.0907 0.8100 0.0070
-3.250 0.0566 0.00782 0.00210 -0.0906 0.8029 0.0073
-3.000 0.0842 0.00758 0.00175 -0.0905 0.7940 0.0080
-2.750 0.1118 0.00741 0.00150 -0.0904 0.7835 0.0098
-2.500 0.1395 0.00729 0.00134 -0.0903 0.7732 0.0135
-2.250 0.1670 0.00713 0.00122 -0.0903 0.7646 0.0297
-2.000 0.1949 0.00705 0.00112 -0.0903 0.7563 0.0370
-1.750 0.2227 0.00694 0.00103 -0.0903 0.7487 0.0544
-1.500 0.2503 0.00682 0.00096 -0.0903 0.7392 0.0823
-1.250 0.2774 0.00657 0.00088 -0.0903 0.7263 0.1561
-1.000 0.3045 0.00634 0.00081 -0.0903 0.7112 0.2398
-0.750 0.3313 0.00602 0.00074 -0.0904 0.6966 0.3538
-0.500 0.3581 0.00574 0.00073 -0.0904 0.6841 0.4718
-0.250 0.3853 0.00563 0.00074 -0.0903 0.6724 0.5316
0.000 0.4123 0.00554 0.00079 -0.0902 0.6596 0.6000
0.250 0.4389 0.00552 0.00084 -0.0900 0.6408 0.6538
0.500 0.4656 0.00558 0.00089 -0.0897 0.6191 0.6811
0.750 0.4927 0.00567 0.00092 -0.0896 0.6001 0.6902
1.000 0.5198 0.00578 0.00096 -0.0894 0.5799 0.6986
1.250 0.5465 0.00591 0.00102 -0.0892 0.5565 0.7072
1.500 0.5731 0.00606 0.00109 -0.0890 0.5310 0.7155
2.000 0.6252 0.00646 0.00128 -0.0884 0.4676 0.7344
2.250 0.6510 0.00669 0.00141 -0.0881 0.4357 0.7441
2.500 0.6769 0.00692 0.00154 -0.0878 0.4051 0.7543
2.750 0.7028 0.00713 0.00167 -0.0876 0.3783 0.7655
3.000 0.7286 0.00735 0.00181 -0.0873 0.3504 0.7770
3.250 0.7540 0.00759 0.00198 -0.0869 0.3201 0.7894
3.500 0.7794 0.00782 0.00215 -0.0865 0.2945 0.8029
3.750 0.8046 0.00805 0.00233 -0.0861 0.2709 0.8189
4.000 0.8298 0.00823 0.00250 -0.0857 0.2516 0.8387
4.250 0.8533 0.00843 0.00269 -0.0850 0.2257 0.8705
4.500 0.8790 0.00875 0.00296 -0.0848 0.1781 1.0000
4.750 0.9027 0.00923 0.00324 -0.0843 0.1398 1.0000
5.000 0.9260 0.00975 0.00356 -0.0837 0.1024 1.0000
5.250 0.9494 0.01025 0.00389 -0.0831 0.0724 1.0000
5.500 0.9712 0.01094 0.00435 -0.0823 0.0343 1.0000
5.750 0.9942 0.01149 0.00479 -0.0816 0.0138 1.0000
6.000 1.0177 0.01198 0.00521 -0.0809 0.0038 1.0000
6.250 1.0427 0.01229 0.00554 -0.0805 0.0032 1.0000
6.500 1.0673 0.01261 0.00591 -0.0801 0.0029 1.0000
6.750 1.0915 0.01300 0.00634 -0.0795 0.0025 1.0000
7.000 1.1151 0.01342 0.00682 -0.0789 0.0022 1.0000
7.250 1.1379 0.01394 0.00743 -0.0781 0.0020 1.0000
7.500 1.1600 0.01452 0.00809 -0.0773 0.0018 1.0000
7.750 1.1803 0.01531 0.00898 -0.0761 0.0017 1.0000
8.000 1.2020 0.01588 0.00960 -0.0752 0.0016 1.0000
8.250 1.2242 0.01636 0.01012 -0.0745 0.0016 1.0000
8.500 1.2454 0.01694 0.01076 -0.0735 0.0015 1.0000
8.750 1.2660 0.01754 0.01142 -0.0725 0.0014 1.0000
9.000 1.2854 0.01824 0.01220 -0.0714 0.0013 1.0000
9.250 1.3040 0.01896 0.01300 -0.0701 0.0013 1.0000
9.500 1.3210 0.01981 0.01396 -0.0686 0.0012 1.0000
9.750 1.3369 0.02069 0.01494 -0.0669 0.0012 1.0000
10.000 1.3520 0.02157 0.01591 -0.0651 0.0011 1.0000
10.250 1.3641 0.02248 0.01692 -0.0629 0.0011 1.0000
10.500 1.3742 0.02340 0.01793 -0.0603 0.0011 1.0000
10.750 1.3832 0.02439 0.01902 -0.0577 0.0010 1.0000
11.000 1.3920 0.02541 0.02013 -0.0553 0.0010 1.0000
11.250 1.3979 0.02667 0.02151 -0.0527 0.0009 1.0000
11.500 1.4027 0.02806 0.02303 -0.0501 0.0009 1.0000
11.750 1.4087 0.02940 0.02447 -0.0479 0.0009 1.0000
12.000 1.4109 0.03111 0.02631 -0.0455 0.0009 1.0000
12.250 1.4163 0.03261 0.02791 -0.0438 0.0008 1.0000
12.500 1.4164 0.03465 0.03011 -0.0418 0.0008 1.0000
12.750 1.4190 0.03655 0.03212 -0.0403 0.0008 1.0000
13.000 1.4183 0.03889 0.03458 -0.0389 0.0008 1.0000
13.250 1.4161 0.04148 0.03730 -0.0378 0.0007 1.0000
13.500 1.4113 0.04457 0.04054 -0.0370 0.0007 1.0000
13.750 1.4039 0.04813 0.04425 -0.0366 0.0007 1.0000
14.000 1.3950 0.05215 0.04842 -0.0367 0.0007 1.0000
14.250 1.3844 0.05669 0.05311 -0.0375 0.0007 1.0000
14.500 1.3707 0.06205 0.05863 -0.0390 0.0007 1.0000
14.750 1.3537 0.06845 0.06522 -0.0414 0.0007 1.0000
15.000 1.3408 0.07466 0.07158 -0.0442 0.0007 1.0000
15.250 1.3179 0.08330 0.08041 -0.0486 0.0006 1.0000
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