HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il) Reynolds number: 500,000 Max Cl/Cd: 92.75 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3010-il-500000-n5.txt Download as CSV file: xf-hq3010-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/10 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3635 0.10840 0.10605 -0.0337 1.0000 0.0085
-10.000 -0.3606 0.10497 0.10264 -0.0348 1.0000 0.0092
-9.750 -0.3573 0.10100 0.09870 -0.0375 1.0000 0.0106
-9.500 -0.2746 0.08482 0.08274 -0.0434 0.9930 0.0114
-9.250 -0.2682 0.08054 0.07847 -0.0458 0.9886 0.0116
-9.000 -0.2614 0.07602 0.07395 -0.0486 0.9842 0.0118
-8.750 -0.2562 0.07122 0.06916 -0.0516 0.9783 0.0119
-8.500 -0.2500 0.06624 0.06416 -0.0551 0.9728 0.0121
-8.250 -0.2444 0.06110 0.05902 -0.0590 0.9654 0.0122
-8.000 -0.2389 0.05544 0.05335 -0.0640 0.9576 0.0123
-7.750 -0.2359 0.04980 0.04770 -0.0691 0.9453 0.0124
-7.500 -0.2421 0.04397 0.04185 -0.0748 0.9280 0.0124
-7.250 -0.2536 0.03772 0.03548 -0.0819 0.9122 0.0123
-7.000 -0.2549 0.03266 0.03025 -0.0848 0.9019 0.0123
-6.750 -0.2509 0.02813 0.02555 -0.0865 0.8928 0.0125
-6.500 -0.2439 0.02316 0.02032 -0.0878 0.8850 0.0124
-6.250 -0.2438 0.02625 0.02242 -0.0945 0.8935 0.0062
-6.000 -0.2255 0.02243 0.01813 -0.0942 0.8868 0.0059
-5.750 -0.2041 0.01941 0.01464 -0.0937 0.8803 0.0056
-5.500 -0.1804 0.01712 0.01190 -0.0932 0.8749 0.0053
-5.250 -0.1556 0.01538 0.00983 -0.0927 0.8687 0.0051
-5.000 -0.1299 0.01414 0.00834 -0.0922 0.8632 0.0050
-4.750 -0.1040 0.01313 0.00715 -0.0918 0.8575 0.0048
-4.500 -0.0778 0.01233 0.00621 -0.0915 0.8516 0.0048
-4.250 -0.0514 0.01167 0.00543 -0.0912 0.8461 0.0047
-4.000 -0.0248 0.01111 0.00479 -0.0910 0.8398 0.0047
-3.500 0.0292 0.01022 0.00371 -0.0906 0.8277 0.0047
-3.250 0.0565 0.00989 0.00329 -0.0904 0.8215 0.0047
-3.000 0.0840 0.00960 0.00293 -0.0903 0.8149 0.0048
-2.750 0.1116 0.00937 0.00261 -0.0902 0.8081 0.0050
-2.500 0.1392 0.00918 0.00233 -0.0901 0.8005 0.0053
-2.250 0.1668 0.00903 0.00209 -0.0899 0.7923 0.0056
-2.000 0.1944 0.00888 0.00189 -0.0898 0.7829 0.0068
-1.750 0.2218 0.00862 0.00171 -0.0897 0.7744 0.0410
-1.500 0.2490 0.00834 0.00158 -0.0897 0.7666 0.0962
-1.250 0.2737 0.00710 0.00143 -0.0901 0.7592 0.4369
-1.000 0.2997 0.00678 0.00148 -0.0899 0.7518 0.5692
-0.750 0.3270 0.00673 0.00148 -0.0897 0.7420 0.6067
-0.500 0.3537 0.00670 0.00150 -0.0893 0.7302 0.6470
-0.250 0.3805 0.00671 0.00151 -0.0890 0.7175 0.6759
0.000 0.4078 0.00674 0.00151 -0.0888 0.7071 0.6898
0.250 0.4353 0.00677 0.00151 -0.0886 0.6975 0.6992
0.750 0.4902 0.00685 0.00153 -0.0884 0.6761 0.7156
1.000 0.5173 0.00692 0.00156 -0.0882 0.6626 0.7237
1.250 0.5441 0.00699 0.00159 -0.0879 0.6459 0.7325
1.500 0.5706 0.00708 0.00163 -0.0876 0.6282 0.7412
1.750 0.5973 0.00717 0.00168 -0.0874 0.6115 0.7506
2.000 0.6237 0.00727 0.00175 -0.0871 0.5927 0.7603
2.250 0.6495 0.00740 0.00182 -0.0866 0.5706 0.7701
2.500 0.6751 0.00756 0.00192 -0.0862 0.5452 0.7808
2.750 0.6999 0.00776 0.00204 -0.0856 0.5155 0.7923
3.000 0.7244 0.00799 0.00217 -0.0850 0.4838 0.8051
3.500 0.7721 0.00847 0.00253 -0.0836 0.4224 0.8364
3.750 0.7951 0.00870 0.00272 -0.0827 0.3930 0.8596
4.000 0.8174 0.00883 0.00289 -0.0815 0.3663 0.9116
4.250 0.8487 0.00915 0.00311 -0.0826 0.3337 1.0000
4.500 0.8732 0.00950 0.00336 -0.0822 0.3070 1.0000
4.750 0.8977 0.00985 0.00361 -0.0817 0.2832 1.0000
5.000 0.9219 0.01021 0.00387 -0.0813 0.2599 1.0000
5.250 0.9459 0.01060 0.00416 -0.0808 0.2366 1.0000
5.500 0.9693 0.01102 0.00448 -0.0802 0.2099 1.0000
5.750 0.9922 0.01149 0.00481 -0.0795 0.1817 1.0000
6.000 1.0158 0.01189 0.00513 -0.0790 0.1630 1.0000
6.250 1.0391 0.01230 0.00547 -0.0784 0.1453 1.0000
6.500 1.0626 0.01268 0.00582 -0.0778 0.1317 1.0000
6.750 1.0849 0.01316 0.00621 -0.0771 0.1117 1.0000
7.000 1.1057 0.01377 0.00669 -0.0762 0.0865 1.0000
7.250 1.1261 0.01439 0.00719 -0.0752 0.0655 1.0000
7.500 1.1473 0.01493 0.00768 -0.0743 0.0528 1.0000
8.000 1.1886 0.01605 0.00873 -0.0724 0.0334 1.0000
8.250 1.2094 0.01656 0.00926 -0.0714 0.0277 1.0000
8.500 1.2294 0.01712 0.00982 -0.0703 0.0230 1.0000
8.750 1.2487 0.01770 0.01043 -0.0692 0.0176 1.0000
9.000 1.2665 0.01838 0.01109 -0.0678 0.0113 1.0000
9.250 1.2785 0.01950 0.01214 -0.0657 0.0030 1.0000
9.500 1.2939 0.02017 0.01289 -0.0638 0.0025 1.0000
9.750 1.3076 0.02092 0.01374 -0.0617 0.0021 1.0000
10.000 1.3204 0.02172 0.01464 -0.0596 0.0019 1.0000
10.250 1.3317 0.02265 0.01567 -0.0574 0.0017 1.0000
10.500 1.3422 0.02365 0.01680 -0.0551 0.0015 1.0000
10.750 1.3532 0.02461 0.01788 -0.0531 0.0015 1.0000
11.000 1.3627 0.02570 0.01913 -0.0510 0.0014 1.0000
11.250 1.3714 0.02689 0.02044 -0.0489 0.0013 1.0000
11.500 1.3784 0.02824 0.02193 -0.0468 0.0013 1.0000
11.750 1.3854 0.02961 0.02342 -0.0449 0.0013 1.0000
12.000 1.3905 0.03119 0.02514 -0.0430 0.0012 1.0000
12.250 1.3938 0.03297 0.02706 -0.0412 0.0012 1.0000
12.500 1.3961 0.03493 0.02916 -0.0395 0.0012 1.0000
12.750 1.3982 0.03695 0.03131 -0.0380 0.0012 1.0000
13.000 1.3966 0.03945 0.03397 -0.0367 0.0011 1.0000
13.250 1.3936 0.04223 0.03690 -0.0356 0.0011 1.0000
13.500 1.3912 0.04507 0.03989 -0.0348 0.0011 1.0000
13.750 1.3879 0.04815 0.04312 -0.0344 0.0011 1.0000
14.000 1.3807 0.05190 0.04703 -0.0344 0.0011 1.0000
14.250 1.3725 0.05601 0.05130 -0.0348 0.0010 1.0000
14.500 1.3647 0.06032 0.05576 -0.0356 0.0011 1.0000
14.750 1.3542 0.06532 0.06094 -0.0370 0.0010 1.0000
15.000 1.3438 0.07067 0.06645 -0.0389 0.0010 1.0000
15.250 1.3311 0.07673 0.07267 -0.0414 0.0010 1.0000
15.500 1.3186 0.08314 0.07925 -0.0444 0.0010 1.0000
15.750 1.3024 0.09060 0.08688 -0.0481 0.0010 1.0000
16.000 1.2878 0.09806 0.09450 -0.0519 0.0010 1.0000
16.250 1.2715 0.10616 0.10275 -0.0563 0.0010 1.0000
16.500 1.2552 0.11447 0.11121 -0.0608 0.0011 1.0000
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