ONERA HOR20 AIRFOIL (hor20-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA HOR20 AIRFOIL (hor20-il) Reynolds number: 200,000 Max Cl/Cd: 61.64 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hor20-il-200000.txt Download as CSV file: xf-hor20-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -1.0092 0.05586 0.05017 -0.0680 1.0000 0.1041
-14.250 -1.0492 0.04806 0.04202 -0.0747 1.0000 0.1052
-14.000 -1.0434 0.04570 0.03965 -0.0758 1.0000 0.1068
-13.750 -1.0210 0.04533 0.03942 -0.0753 1.0000 0.1087
-13.500 -1.0204 0.04251 0.03653 -0.0775 1.0000 0.1104
-13.250 -1.0312 0.03903 0.03287 -0.0801 1.0000 0.1119
-13.000 -1.0410 0.03648 0.03007 -0.0804 1.0000 0.1134
-12.750 -1.0334 0.03474 0.02822 -0.0802 1.0000 0.1152
-12.500 -1.0113 0.03408 0.02770 -0.0798 1.0000 0.1170
-12.250 -0.9949 0.03315 0.02678 -0.0795 1.0000 0.1190
-12.000 -0.9827 0.03192 0.02544 -0.0791 1.0000 0.1213
-11.750 -0.9741 0.03057 0.02384 -0.0784 1.0000 0.1235
-11.500 -0.9560 0.02981 0.02323 -0.0774 1.0000 0.1256
-11.250 -0.9435 0.02939 0.02290 -0.0757 1.0000 0.1277
-11.000 -0.9415 0.02897 0.02248 -0.0727 0.9996 0.1297
-10.750 -0.9017 0.02773 0.02092 -0.0770 0.9919 0.1337
-10.500 -0.8600 0.02695 0.02034 -0.0800 0.9848 0.1370
-10.250 -0.8177 0.02619 0.01954 -0.0835 0.9774 0.1410
-10.000 -0.7803 0.02513 0.01826 -0.0865 0.9667 0.1450
-9.750 -0.7411 0.02447 0.01774 -0.0889 0.9568 0.1485
-9.500 -0.7076 0.02387 0.01708 -0.0903 0.9429 0.1523
-9.250 -0.6817 0.02321 0.01617 -0.0903 0.9254 0.1560
-9.000 -0.6569 0.02262 0.01569 -0.0897 0.9085 0.1592
-8.750 -0.6325 0.02226 0.01532 -0.0889 0.8924 0.1628
-8.500 -0.6089 0.02183 0.01469 -0.0882 0.8775 0.1672
-8.250 -0.5849 0.02133 0.01418 -0.0874 0.8630 0.1711
-8.000 -0.5591 0.02107 0.01392 -0.0869 0.8485 0.1754
-7.750 -0.5340 0.02074 0.01339 -0.0862 0.8360 0.1803
-7.500 -0.5077 0.02030 0.01297 -0.0859 0.8218 0.1847
-7.250 -0.4812 0.02012 0.01274 -0.0854 0.8098 0.1895
-7.000 -0.4539 0.01985 0.01228 -0.0853 0.7967 0.1951
-6.750 -0.4270 0.01955 0.01201 -0.0849 0.7856 0.1999
-6.500 -0.3989 0.01939 0.01183 -0.0848 0.7728 0.2054
-6.250 -0.3714 0.01919 0.01141 -0.0845 0.7619 0.2115
-6.000 -0.3430 0.01898 0.01130 -0.0845 0.7495 0.2168
-5.750 -0.3148 0.01892 0.01110 -0.0843 0.7394 0.2232
-5.500 -0.2861 0.01862 0.01076 -0.0844 0.7276 0.2293
-5.250 -0.2577 0.01851 0.01064 -0.0842 0.7172 0.2350
-5.000 -0.2285 0.01841 0.01042 -0.0843 0.7067 0.2417
-4.750 -0.1997 0.01809 0.01008 -0.0843 0.6964 0.2477
-4.500 -0.1709 0.01802 0.00996 -0.0842 0.6874 0.2537
-4.250 -0.1412 0.01789 0.00974 -0.0844 0.6768 0.2606
-4.000 -0.1124 0.01760 0.00942 -0.0844 0.6681 0.2668
-3.750 -0.0830 0.01753 0.00935 -0.0844 0.6595 0.2733
-3.500 -0.0531 0.01743 0.00914 -0.0846 0.6502 0.2803
-3.250 -0.0241 0.01721 0.00890 -0.0846 0.6424 0.2868
-3.000 0.0055 0.01715 0.00887 -0.0847 0.6339 0.2935
-2.750 0.0356 0.01711 0.00870 -0.0849 0.6256 0.3008
-2.500 0.0648 0.01695 0.00856 -0.0849 0.6187 0.3074
-2.250 0.0946 0.01695 0.00858 -0.0850 0.6109 0.3147
-2.000 0.1247 0.01692 0.00844 -0.0852 0.6029 0.3220
-1.750 0.1540 0.01681 0.00837 -0.0852 0.5961 0.3288
-1.500 0.1839 0.01687 0.00841 -0.0853 0.5893 0.3363
-1.250 0.2139 0.01682 0.00832 -0.0855 0.5817 0.3440
-1.000 0.2434 0.01677 0.00830 -0.0855 0.5749 0.3509
-0.750 0.2732 0.01688 0.00833 -0.0856 0.5685 0.3591
-0.500 0.3030 0.01682 0.00830 -0.0858 0.5612 0.3669
-0.250 0.3326 0.01682 0.00833 -0.0858 0.5544 0.3743
0.000 0.3625 0.01694 0.00832 -0.0859 0.5484 0.3832
0.250 0.3920 0.01693 0.00840 -0.0860 0.5418 0.3913
0.500 0.4216 0.01700 0.00850 -0.0861 0.5350 0.4002
0.750 0.4515 0.01706 0.00847 -0.0862 0.5291 0.4102
1.000 0.4807 0.01721 0.00864 -0.0862 0.5233 0.4189
1.250 0.5103 0.01731 0.00876 -0.0863 0.5167 0.4300
1.500 0.5395 0.01735 0.00885 -0.0862 0.5107 0.4392
1.750 0.5691 0.01752 0.00894 -0.0863 0.5052 0.4502
2.000 0.5982 0.01765 0.00911 -0.0863 0.4993 0.4601
2.250 0.6270 0.01776 0.00929 -0.0862 0.4929 0.4703
2.500 0.6564 0.01786 0.00934 -0.0863 0.4872 0.4808
2.750 0.6857 0.01807 0.00950 -0.0863 0.4819 0.4900
3.000 0.7143 0.01822 0.00969 -0.0863 0.4758 0.5007
3.250 0.7426 0.01823 0.00981 -0.0861 0.4696 0.5096
3.500 0.7718 0.01835 0.00987 -0.0861 0.4643 0.5198
3.750 0.8008 0.01853 0.01000 -0.0862 0.4592 0.5286
4.000 0.8284 0.01860 0.01020 -0.0860 0.4529 0.5381
4.250 0.8570 0.01867 0.01026 -0.0859 0.4468 0.5480
4.500 0.8856 0.01872 0.01030 -0.0858 0.4416 0.5573
4.750 0.9137 0.01892 0.01052 -0.0857 0.4359 0.5672
5.000 0.9409 0.01896 0.01067 -0.0855 0.4295 0.5762
5.250 0.9690 0.01903 0.01074 -0.0854 0.4238 0.5870
5.500 0.9977 0.01923 0.01088 -0.0853 0.4185 0.5979
5.750 1.0236 0.01934 0.01116 -0.0849 0.4122 0.6097
6.000 1.0507 0.01942 0.01130 -0.0846 0.4062 0.6218
6.250 1.0786 0.01955 0.01140 -0.0845 0.4010 0.6364
6.500 1.1044 0.01976 0.01175 -0.0841 0.3954 0.6538
6.750 1.1296 0.01986 0.01203 -0.0835 0.3893 0.6781
7.000 1.1549 0.01988 0.01218 -0.0828 0.3838 0.7150
7.250 1.1768 0.01979 0.01236 -0.0812 0.3786 0.8245
7.500 1.2023 0.01986 0.01263 -0.0808 0.3722 1.0000
7.750 1.2289 0.02014 0.01283 -0.0805 0.3663 1.0000
8.000 1.2569 0.02050 0.01303 -0.0805 0.3611 1.0000
8.250 1.2800 0.02090 0.01351 -0.0798 0.3552 1.0000
8.500 1.3043 0.02124 0.01385 -0.0793 0.3494 1.0000
8.750 1.3301 0.02158 0.01409 -0.0789 0.3443 1.0000
9.000 1.3537 0.02207 0.01457 -0.0782 0.3389 1.0000
9.250 1.3750 0.02246 0.01502 -0.0773 0.3329 1.0000
9.500 1.3983 0.02282 0.01532 -0.0765 0.3275 1.0000
9.750 1.4222 0.02333 0.01575 -0.0760 0.3222 1.0000
10.000 1.4400 0.02383 0.01636 -0.0745 0.3165 1.0000
10.250 1.4603 0.02426 0.01679 -0.0734 0.3112 1.0000
10.500 1.4859 0.02478 0.01714 -0.0731 0.3062 1.0000
10.750 1.4986 0.02541 0.01793 -0.0710 0.3010 1.0000
11.000 1.5143 0.02596 0.01853 -0.0694 0.2958 1.0000
11.250 1.5337 0.02648 0.01897 -0.0682 0.2910 1.0000
11.500 1.5469 0.02721 0.01973 -0.0663 0.2862 1.0000
11.750 1.5532 0.02799 0.02061 -0.0634 0.2812 1.0000
12.000 1.5648 0.02871 0.02133 -0.0615 0.2765 1.0000
12.250 1.5848 0.02939 0.02189 -0.0606 0.2717 1.0000
12.500 1.5856 0.03061 0.02328 -0.0579 0.2671 1.0000
12.750 1.5933 0.03168 0.02440 -0.0560 0.2623 1.0000
13.000 1.6084 0.03252 0.02516 -0.0549 0.2579 1.0000
13.250 1.6166 0.03381 0.02651 -0.0534 0.2535 1.0000
13.500 1.6183 0.03541 0.02824 -0.0516 0.2489 1.0000
13.750 1.6261 0.03674 0.02958 -0.0504 0.2445 1.0000
14.000 1.6461 0.03746 0.03015 -0.0497 0.2400 1.0000
14.250 1.6396 0.03984 0.03276 -0.0481 0.2361 1.0000
14.500 1.6412 0.04179 0.03479 -0.0471 0.2317 1.0000
14.750 1.6497 0.04323 0.03620 -0.0462 0.2276 1.0000
15.000 1.6576 0.04483 0.03779 -0.0453 0.2234 1.0000
15.250 1.6493 0.04779 0.04094 -0.0446 0.2191 1.0000
15.500 1.6502 0.05000 0.04319 -0.0440 0.2149 1.0000
15.750 1.6668 0.05080 0.04383 -0.0432 0.2106 1.0000
16.000 1.6524 0.05463 0.04789 -0.0429 0.2069 1.0000
16.250 1.6469 0.05775 0.05112 -0.0428 0.2030 1.0000
16.500 1.6505 0.05994 0.05332 -0.0425 0.1993 1.0000
16.750 1.6611 0.06138 0.05469 -0.0419 0.1956 1.0000
17.000 1.6441 0.06609 0.05962 -0.0425 0.1919 1.0000
17.250 1.6394 0.06948 0.06309 -0.0429 0.1880 1.0000
17.500 1.6473 0.07129 0.06484 -0.0427 0.1846 1.0000
17.750 1.6458 0.07435 0.06796 -0.0429 0.1813 1.0000
18.000 1.6303 0.07935 0.07315 -0.0439 0.1779 1.0000
18.250 1.6271 0.08277 0.07663 -0.0445 0.1745 1.0000
18.500 1.6393 0.08404 0.07782 -0.0443 0.1714 1.0000
18.750 1.6314 0.08814 0.08203 -0.0451 0.1684 1.0000
19.000 1.6120 0.09400 0.08808 -0.0469 0.1650 1.0000
19.250 1.6092 0.09750 0.09163 -0.0478 0.1618 1.0000
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