HQ 3.0/13 AIRFOIL (hq3013-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 3.0/13 AIRFOIL (hq3013-il) Reynolds number: 100,000 Max Cl/Cd: 55.08 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq3013-il-100000-n5.txt Download as CSV file: xf-hq3013-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 3.0/13 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4152 0.08581 0.08086 -0.0564 1.0000 0.0275
-10.250 -0.4296 0.07931 0.07444 -0.0591 1.0000 0.0274
-10.000 -0.4513 0.07178 0.06697 -0.0629 1.0000 0.0271
-9.750 -0.4754 0.06662 0.06186 -0.0648 1.0000 0.0268
-9.500 -0.5030 0.06337 0.05866 -0.0641 1.0000 0.0265
-9.250 -0.5361 0.06164 0.05699 -0.0608 1.0000 0.0262
-9.000 -0.5493 0.05427 0.04927 -0.0685 0.9867 0.0262
-8.750 -0.5521 0.04727 0.04167 -0.0737 0.9750 0.0267
-8.500 -0.5449 0.04178 0.03550 -0.0764 0.9659 0.0272
-8.250 -0.5277 0.03771 0.03091 -0.0783 0.9591 0.0280
-8.000 -0.5053 0.03554 0.02853 -0.0795 0.9530 0.0289
-7.750 -0.4814 0.03346 0.02614 -0.0804 0.9468 0.0303
-7.500 -0.4521 0.03103 0.02329 -0.0821 0.9430 0.0325
-7.250 -0.4296 0.02911 0.02095 -0.0820 0.9361 0.0356
-7.000 -0.4004 0.02814 0.01996 -0.0833 0.9313 0.0390
-6.750 -0.3680 0.02662 0.01807 -0.0845 0.9280 0.0439
-6.500 -0.3455 0.02570 0.01716 -0.0843 0.9208 0.0483
-6.250 -0.3149 0.02491 0.01606 -0.0851 0.9162 0.0552
-6.000 -0.2829 0.02388 0.01506 -0.0865 0.9129 0.0617
-5.750 -0.2598 0.02326 0.01424 -0.0858 0.9055 0.0677
-5.500 -0.2306 0.02235 0.01336 -0.0864 0.9011 0.0737
-5.250 -0.1983 0.02154 0.01243 -0.0874 0.8979 0.0796
-5.000 -0.1775 0.02096 0.01184 -0.0863 0.8900 0.0853
-4.750 -0.1482 0.02036 0.01119 -0.0868 0.8856 0.0937
-4.500 -0.1205 0.01973 0.01056 -0.0870 0.8809 0.1023
-4.250 -0.0969 0.01927 0.01007 -0.0864 0.8741 0.1139
-4.000 -0.0676 0.01866 0.00953 -0.0869 0.8699 0.1359
-3.750 -0.0433 0.01809 0.00914 -0.0867 0.8639 0.1753
-3.500 -0.0194 0.01730 0.00873 -0.0866 0.8580 0.2653
-3.250 0.0056 0.01639 0.00864 -0.0864 0.8539 0.4470
-3.000 0.0274 0.01639 0.00879 -0.0850 0.8469 0.5287
-2.750 0.0547 0.01642 0.00880 -0.0845 0.8417 0.5730
-2.500 0.0854 0.01641 0.00872 -0.0846 0.8380 0.6077
-2.250 0.1059 0.01659 0.00891 -0.0829 0.8301 0.6352
-2.000 0.1329 0.01667 0.00899 -0.0820 0.8253 0.6658
-1.750 0.1572 0.01679 0.00907 -0.0808 0.8193 0.6896
-1.500 0.1817 0.01684 0.00909 -0.0798 0.8127 0.7056
-1.250 0.2116 0.01678 0.00896 -0.0797 0.8083 0.7204
-1.000 0.2336 0.01687 0.00900 -0.0785 0.8002 0.7334
-0.750 0.2627 0.01677 0.00886 -0.0784 0.7949 0.7425
-0.500 0.2888 0.01677 0.00879 -0.0780 0.7880 0.7503
-0.250 0.3163 0.01671 0.00868 -0.0778 0.7817 0.7578
0.000 0.3453 0.01663 0.00855 -0.0779 0.7762 0.7659
0.250 0.3698 0.01666 0.00856 -0.0772 0.7684 0.7741
0.500 0.4004 0.01654 0.00839 -0.0775 0.7635 0.7823
0.750 0.4236 0.01662 0.00848 -0.0766 0.7550 0.7922
1.000 0.4529 0.01652 0.00836 -0.0766 0.7494 0.8010
1.250 0.4770 0.01656 0.00841 -0.0759 0.7407 0.8113
1.500 0.5071 0.01636 0.00818 -0.0759 0.7333 0.8222
1.750 0.5302 0.01631 0.00817 -0.0748 0.7219 0.8340
2.000 0.5555 0.01620 0.00809 -0.0740 0.7116 0.8467
2.250 0.5842 0.01603 0.00792 -0.0737 0.7034 0.8606
2.500 0.6079 0.01602 0.00799 -0.0728 0.6929 0.8780
2.750 0.6365 0.01593 0.00797 -0.0728 0.6833 0.8990
3.000 0.6729 0.01577 0.00784 -0.0742 0.6736 0.9248
3.250 0.7118 0.01572 0.00784 -0.0765 0.6605 0.9966
3.500 0.7377 0.01580 0.00790 -0.0763 0.6470 1.0000
3.750 0.7636 0.01586 0.00793 -0.0760 0.6326 1.0000
4.000 0.7892 0.01595 0.00799 -0.0756 0.6174 1.0000
4.250 0.8147 0.01605 0.00807 -0.0752 0.6013 1.0000
4.500 0.8400 0.01617 0.00815 -0.0746 0.5847 1.0000
4.750 0.8638 0.01634 0.00829 -0.0739 0.5662 1.0000
5.000 0.8874 0.01653 0.00847 -0.0731 0.5461 1.0000
5.250 0.9111 0.01674 0.00861 -0.0723 0.5250 1.0000
5.500 0.9332 0.01701 0.00883 -0.0713 0.5014 1.0000
5.750 0.9550 0.01734 0.00906 -0.0702 0.4775 1.0000
6.000 0.9756 0.01773 0.00937 -0.0690 0.4523 1.0000
6.250 0.9955 0.01818 0.00973 -0.0677 0.4279 1.0000
6.500 1.0145 0.01869 0.01013 -0.0663 0.4041 1.0000
6.750 1.0328 0.01922 0.01063 -0.0649 0.3807 1.0000
7.000 1.0504 0.01981 0.01113 -0.0634 0.3592 1.0000
7.250 1.0675 0.02041 0.01169 -0.0618 0.3379 1.0000
7.500 1.0838 0.02106 0.01227 -0.0602 0.3189 1.0000
7.750 1.0994 0.02175 0.01289 -0.0585 0.3017 1.0000
8.000 1.1139 0.02245 0.01356 -0.0566 0.2859 1.0000
8.500 1.1417 0.02391 0.01499 -0.0529 0.2573 1.0000
8.750 1.1553 0.02468 0.01577 -0.0510 0.2438 1.0000
9.000 1.1687 0.02548 0.01660 -0.0493 0.2309 1.0000
9.250 1.1816 0.02632 0.01749 -0.0475 0.2186 1.0000
9.500 1.1938 0.02721 0.01840 -0.0458 0.2072 1.0000
9.750 1.2046 0.02817 0.01937 -0.0439 0.1964 1.0000
10.000 1.2157 0.02916 0.02041 -0.0423 0.1856 1.0000
10.250 1.2269 0.03019 0.02151 -0.0407 0.1752 1.0000
10.500 1.2365 0.03133 0.02268 -0.0390 0.1657 1.0000
10.750 1.2452 0.03256 0.02397 -0.0374 0.1565 1.0000
11.000 1.2552 0.03378 0.02529 -0.0360 0.1473 1.0000
11.250 1.2626 0.03518 0.02672 -0.0345 0.1393 1.0000
11.500 1.2708 0.03658 0.02824 -0.0332 0.1310 1.0000
11.750 1.2778 0.03812 0.02986 -0.0319 0.1233 1.0000
12.000 1.2830 0.03982 0.03162 -0.0306 0.1160 1.0000
12.250 1.2890 0.04155 0.03346 -0.0295 0.1087 1.0000
12.500 1.2918 0.04354 0.03550 -0.0284 0.1024 1.0000
12.750 1.2965 0.04551 0.03763 -0.0274 0.0958 1.0000
13.000 1.2977 0.04779 0.03997 -0.0266 0.0900 1.0000
13.250 1.2999 0.05009 0.04239 -0.0260 0.0841 1.0000
13.500 1.2998 0.05266 0.04506 -0.0255 0.0787 1.0000
13.750 1.2987 0.05545 0.04792 -0.0252 0.0743 1.0000
14.000 1.2993 0.05821 0.05085 -0.0251 0.0696 1.0000
14.250 1.2963 0.06141 0.05414 -0.0252 0.0662 1.0000
14.500 1.2926 0.06486 0.05768 -0.0255 0.0631 1.0000
14.750 1.2913 0.06820 0.06122 -0.0259 0.0598 1.0000
15.000 1.2869 0.07202 0.06520 -0.0266 0.0569 1.0000
15.250 1.2803 0.07627 0.06955 -0.0277 0.0547 1.0000
15.500 1.2734 0.08071 0.07406 -0.0290 0.0529 1.0000
15.750 1.2680 0.08521 0.07881 -0.0305 0.0502 1.0000
16.000 1.2599 0.09025 0.08403 -0.0324 0.0478 1.0000
16.250 1.2503 0.09573 0.08968 -0.0348 0.0458 1.0000
16.500 1.2386 0.10170 0.09575 -0.0376 0.0441 1.0000
16.750 1.2268 0.10790 0.10207 -0.0406 0.0422 1.0000
17.000 1.2156 0.11425 0.10864 -0.0438 0.0403 1.0000
17.250 1.2032 0.12101 0.11556 -0.0474 0.0385 1.0000
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