ONERA HOR20 AIRFOIL (hor20-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA HOR20 AIRFOIL (hor20-il) Reynolds number: 100,000 Max Cl/Cd: 34.35 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hor20-il-100000.txt Download as CSV file: xf-hor20-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: ONERA HOR20 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2009 0.10512 0.09995 -0.0329 0.9874 0.2496
-8.250 -0.1726 0.10143 0.09622 -0.0382 0.9746 0.2565
-8.000 -0.5071 0.04043 0.03372 -0.0906 0.9372 0.2097
-7.750 -0.4649 0.04011 0.03352 -0.0923 0.9264 0.2140
-7.500 -0.4279 0.04065 0.03419 -0.0923 0.9123 0.2182
-7.250 -0.4224 0.03578 0.02858 -0.0956 0.8974 0.2271
-7.000 -0.3891 0.03607 0.02910 -0.0947 0.8851 0.2309
-6.750 -0.3634 0.03612 0.02921 -0.0937 0.8698 0.2358
-6.500 -0.3482 0.03337 0.02587 -0.0947 0.8577 0.2445
-6.250 -0.3219 0.03346 0.02616 -0.0933 0.8435 0.2486
-6.000 -0.2965 0.03336 0.02608 -0.0923 0.8313 0.2543
-5.750 -0.2768 0.03146 0.02370 -0.0929 0.8187 0.2631
-5.500 -0.2507 0.03153 0.02394 -0.0916 0.8070 0.2677
-5.250 -0.2252 0.03133 0.02372 -0.0908 0.7948 0.2742
-5.000 -0.2016 0.03004 0.02207 -0.0911 0.7849 0.2829
-4.750 -0.1752 0.03018 0.02237 -0.0901 0.7725 0.2881
-4.500 -0.1490 0.02989 0.02194 -0.0893 0.7640 0.2955
-4.250 -0.1232 0.02914 0.02104 -0.0899 0.7516 0.3037
-4.000 -0.0963 0.02925 0.02123 -0.0888 0.7425 0.3094
-3.750 -0.0693 0.02893 0.02076 -0.0889 0.7329 0.3180
-3.500 -0.0425 0.02855 0.02033 -0.0887 0.7226 0.3252
-3.250 -0.0150 0.02860 0.02037 -0.0878 0.7152 0.3318
-3.000 0.0129 0.02821 0.01977 -0.0886 0.7051 0.3419
-2.750 0.0398 0.02816 0.01983 -0.0879 0.6962 0.3476
-2.500 0.0678 0.02815 0.01974 -0.0871 0.6896 0.3550
-2.250 0.0959 0.02783 0.01927 -0.0880 0.6795 0.3649
-2.000 0.1230 0.02790 0.01945 -0.0873 0.6715 0.3707
-1.750 0.1517 0.02783 0.01927 -0.0868 0.6654 0.3791
-1.500 0.1795 0.02767 0.01905 -0.0874 0.6559 0.3881
-1.250 0.2068 0.02776 0.01922 -0.0868 0.6480 0.3946
-1.000 0.2361 0.02760 0.01891 -0.0866 0.6421 0.4039
-0.750 0.2636 0.02761 0.01891 -0.0869 0.6337 0.4120
-0.500 0.2907 0.02771 0.01908 -0.0865 0.6255 0.4192
-0.250 0.3209 0.02750 0.01867 -0.0866 0.6194 0.4298
0.000 0.3479 0.02760 0.01883 -0.0864 0.6122 0.4372
0.250 0.3747 0.02777 0.01905 -0.0862 0.6037 0.4461
0.500 0.4047 0.02756 0.01868 -0.0863 0.5974 0.4569
0.750 0.4327 0.02763 0.01876 -0.0858 0.5918 0.4654
1.000 0.4593 0.02792 0.01906 -0.0862 0.5828 0.4772
1.250 0.4868 0.02782 0.01901 -0.0857 0.5762 0.4859
1.500 0.5177 0.02773 0.01875 -0.0857 0.5712 0.4989
1.750 0.5415 0.02809 0.01928 -0.0853 0.5630 0.5084
2.000 0.5694 0.02820 0.01936 -0.0853 0.5557 0.5216
2.250 0.5984 0.02801 0.01915 -0.0849 0.5504 0.5328
2.500 0.6259 0.02833 0.01942 -0.0850 0.5441 0.5468
2.750 0.6493 0.02860 0.01989 -0.0844 0.5360 0.5576
3.000 0.6789 0.02852 0.01973 -0.0843 0.5301 0.5715
3.250 0.7093 0.02841 0.01954 -0.0840 0.5255 0.5848
3.500 0.7295 0.02913 0.02047 -0.0836 0.5169 0.5969
3.750 0.7564 0.02923 0.02060 -0.0832 0.5103 0.6106
4.000 0.7870 0.02905 0.02035 -0.0830 0.5054 0.6239
4.250 0.8098 0.02974 0.02113 -0.0826 0.4984 0.6379
4.500 0.8321 0.03015 0.02171 -0.0818 0.4909 0.6510
4.750 0.8619 0.03006 0.02157 -0.0817 0.4855 0.6668
5.000 0.8927 0.03007 0.02150 -0.0815 0.4807 0.6839
5.250 0.9066 0.03113 0.02287 -0.0802 0.4718 0.6985
5.500 0.9339 0.03117 0.02295 -0.0798 0.4658 0.7184
5.750 0.9660 0.03086 0.02259 -0.0795 0.4613 0.7439
6.000 0.9785 0.03196 0.02401 -0.0779 0.4534 0.7729
6.250 0.9973 0.03208 0.02440 -0.0761 0.4470 0.8278
6.500 1.0353 0.03156 0.02388 -0.0771 0.4420 1.0000
6.750 1.0597 0.03255 0.02481 -0.0775 0.4356 1.0000
7.000 1.0778 0.03367 0.02597 -0.0769 0.4280 1.0000
7.250 1.1109 0.03365 0.02578 -0.0773 0.4229 1.0000
7.500 1.1501 0.03348 0.02532 -0.0782 0.4189 1.0000
7.750 1.1465 0.03585 0.02802 -0.0755 0.4102 1.0000
8.000 1.1744 0.03603 0.02812 -0.0753 0.4045 1.0000
8.250 1.2148 0.03550 0.02735 -0.0760 0.4002 1.0000
8.500 1.2131 0.03776 0.02985 -0.0734 0.3928 1.0000
8.750 1.2306 0.03858 0.03069 -0.0723 0.3865 1.0000
9.000 1.2702 0.03801 0.02993 -0.0729 0.3821 1.0000
9.250 1.2848 0.03923 0.03120 -0.0716 0.3765 1.0000
9.500 1.2750 0.04171 0.03390 -0.0682 0.3693 1.0000
9.750 1.3108 0.04131 0.03338 -0.0685 0.3645 1.0000
10.000 1.3662 0.04012 0.03190 -0.0705 0.3606 1.0000
10.250 1.2966 0.04587 0.03819 -0.0623 0.3531 1.0000
10.500 1.3106 0.04663 0.03894 -0.0608 0.3477 1.0000
10.750 1.3923 0.04375 0.03575 -0.0646 0.3435 1.0000
11.000 1.0640 0.07826 0.07116 -0.0589 0.3235 1.0000
11.250 1.1265 0.07263 0.06546 -0.0563 0.3233 1.0000
11.500 1.2009 0.06615 0.05888 -0.0540 0.3228 1.0000
11.750 1.3147 0.05684 0.04935 -0.0527 0.3220 1.0000
12.750 0.8359 0.14334 0.13665 -0.0792 0.2703 1.0000
13.000 0.8170 0.15103 0.14440 -0.0827 0.2694 1.0000
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Polar data table (+)
Polar graphs
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