ONERA HOR20 AIRFOIL (hor20-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: ONERA HOR20 AIRFOIL (hor20-il) Reynolds number: 50,000 Max Cl/Cd: 21.66 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hor20-il-50000-n5.txt Download as CSV file: xf-hor20-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3290 0.12042 0.11192 -0.0304 1.0000 0.1517
-10.750 -0.3330 0.11578 0.10730 -0.0329 1.0000 0.1537
-10.500 -0.3435 0.11032 0.10186 -0.0359 1.0000 0.1564
-10.250 -0.3265 0.10889 0.10049 -0.0358 1.0000 0.1586
-10.000 -0.3193 0.10610 0.09774 -0.0368 1.0000 0.1611
-9.750 -0.3209 0.10216 0.09384 -0.0387 1.0000 0.1637
-9.500 -0.3476 0.09497 0.08667 -0.0428 1.0000 0.1678
-9.250 -0.3371 0.09332 0.08511 -0.0428 1.0000 0.1701
-9.000 -0.3296 0.09175 0.08365 -0.0426 1.0000 0.1726
-8.000 -0.4119 0.06242 0.05419 -0.0675 0.9369 0.1960
-7.750 -0.3610 0.06450 0.05630 -0.0665 0.9237 0.1982
-7.500 -0.4113 0.05167 0.04301 -0.0789 0.9006 0.2093
-7.250 -0.3873 0.05042 0.04172 -0.0799 0.8857 0.2135
-7.000 -0.3639 0.04975 0.04102 -0.0800 0.8704 0.2180
-6.750 -0.3693 0.04388 0.03462 -0.0846 0.8559 0.2277
-6.500 -0.3403 0.04417 0.03498 -0.0835 0.8422 0.2313
-6.250 -0.3197 0.04306 0.03375 -0.0837 0.8291 0.2373
-6.000 -0.3047 0.04034 0.03067 -0.0854 0.8170 0.2456
-5.750 -0.2788 0.04045 0.03084 -0.0844 0.8045 0.2499
-5.500 -0.2567 0.03931 0.02952 -0.0846 0.7929 0.2573
-5.250 -0.2354 0.03794 0.02793 -0.0852 0.7815 0.2647
-5.000 -0.2098 0.03796 0.02800 -0.0842 0.7701 0.2697
-4.750 -0.1859 0.03689 0.02669 -0.0846 0.7604 0.2781
-4.500 -0.1624 0.03631 0.02603 -0.0845 0.7484 0.2847
-4.250 -0.1356 0.03620 0.02591 -0.0836 0.7398 0.2905
-4.000 -0.1121 0.03526 0.02474 -0.0844 0.7284 0.2999
-3.750 -0.0861 0.03512 0.02461 -0.0837 0.7190 0.3056
-3.500 -0.0597 0.03498 0.02444 -0.0832 0.7102 0.3121
-3.250 -0.0340 0.03418 0.02340 -0.0841 0.6996 0.3221
-3.000 -0.0070 0.03423 0.02351 -0.0832 0.6918 0.3274
-2.750 0.0190 0.03410 0.02333 -0.0831 0.6826 0.3349
-2.500 0.0458 0.03360 0.02266 -0.0836 0.6732 0.3441
-2.250 0.0733 0.03355 0.02262 -0.0828 0.6663 0.3500
-2.000 0.0991 0.03345 0.02246 -0.0829 0.6571 0.3585
-1.750 0.1261 0.03321 0.02212 -0.0831 0.6485 0.3668
-1.500 0.1540 0.03311 0.02200 -0.0825 0.6421 0.3736
-1.250 0.1801 0.03305 0.02185 -0.0828 0.6333 0.3834
-1.000 0.2063 0.03306 0.02186 -0.0825 0.6251 0.3906
-0.750 0.2345 0.03295 0.02170 -0.0821 0.6190 0.3988
-0.500 0.2615 0.03292 0.02154 -0.0826 0.6110 0.4095
-0.250 0.2861 0.03312 0.02184 -0.0819 0.6028 0.4162
0.000 0.3149 0.03301 0.02163 -0.0819 0.5967 0.4263
0.250 0.3421 0.03303 0.02159 -0.0818 0.5902 0.4357
0.500 0.3654 0.03336 0.02200 -0.0814 0.5814 0.4442
0.750 0.3945 0.03328 0.02177 -0.0816 0.5750 0.4560
1.000 0.4235 0.03315 0.02162 -0.0810 0.5703 0.4649
1.250 0.4446 0.03374 0.02225 -0.0809 0.5606 0.4759
1.500 0.4707 0.03382 0.02235 -0.0804 0.5539 0.4851
1.750 0.5010 0.03370 0.02210 -0.0803 0.5489 0.4977
2.000 0.5219 0.03428 0.02278 -0.0798 0.5406 0.5072
2.250 0.5468 0.03458 0.02307 -0.0795 0.5333 0.5189
2.500 0.5761 0.03450 0.02293 -0.0793 0.5280 0.5302
2.750 0.6008 0.03488 0.02330 -0.0790 0.5216 0.5425
3.000 0.6204 0.03555 0.02408 -0.0783 0.5134 0.5529
3.250 0.6488 0.03560 0.02408 -0.0780 0.5077 0.5660
3.500 0.6801 0.03538 0.02382 -0.0778 0.5036 0.5788
3.750 0.6919 0.03678 0.02537 -0.0768 0.4941 0.5906
4.000 0.7156 0.03707 0.02574 -0.0761 0.4878 0.6030
4.250 0.7466 0.03694 0.02556 -0.0759 0.4833 0.6188
4.500 0.7603 0.03807 0.02686 -0.0748 0.4758 0.6325
4.750 0.7757 0.03900 0.02794 -0.0736 0.4682 0.6475
5.000 0.8040 0.03893 0.02790 -0.0731 0.4633 0.6674
5.250 0.8296 0.03908 0.02812 -0.0724 0.4585 0.6895
5.500 0.8262 0.04134 0.03069 -0.0701 0.4488 0.7076
5.750 0.8497 0.04138 0.03087 -0.0690 0.4438 0.7390
6.000 0.8807 0.04066 0.03030 -0.0679 0.4402 0.7950
6.250 0.8561 0.04415 0.03425 -0.0645 0.4292 1.0000
6.500 0.8827 0.04472 0.03468 -0.0648 0.4238 1.0000
6.750 0.9244 0.04415 0.03390 -0.0656 0.4204 1.0000
7.000 0.8679 0.05059 0.04056 -0.0616 0.4072 1.0000
7.250 0.8973 0.05070 0.04055 -0.0614 0.4030 1.0000
7.500 0.9424 0.04958 0.03927 -0.0617 0.4003 1.0000
8.000 0.9009 0.05871 0.04852 -0.0595 0.3815 1.0000
8.250 0.9365 0.05792 0.04761 -0.0588 0.3790 1.0000
8.750 0.8991 0.06846 0.05826 -0.0592 0.3597 1.0000
9.250 0.8650 0.07998 0.06988 -0.0610 0.3402 1.0000
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