NACA 5-H-20 AIRFOIL (n5h20-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 5-H-20 AIRFOIL (n5h20-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.41 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n5h20-il-1000000.txt Download as CSV file: xf-n5h20-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 5-H-20 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2190 0.09062 0.08765 -0.0531 0.6215 0.0292
-11.500 -0.5468 0.04836 0.04455 -0.0722 0.6322 0.0276
-11.250 -0.5622 0.04613 0.04223 -0.0684 0.6296 0.0274
-11.000 -0.5816 0.04368 0.03965 -0.0635 0.6273 0.0272
-10.750 -0.6052 0.04079 0.03658 -0.0575 0.6260 0.0269
-10.500 -0.6407 0.03661 0.03208 -0.0490 0.6246 0.0269
-10.250 -0.6667 0.03271 0.02781 -0.0412 0.6232 0.0268
-10.000 -0.6731 0.02956 0.02431 -0.0364 0.6215 0.0269
-9.750 -0.6691 0.02698 0.02140 -0.0329 0.6196 0.0270
-9.500 -0.6566 0.02519 0.01936 -0.0307 0.6176 0.0271
-9.250 -0.6394 0.02390 0.01787 -0.0292 0.6155 0.0273
-9.000 -0.6199 0.02288 0.01667 -0.0280 0.6132 0.0275
-8.750 -0.5996 0.02216 0.01580 -0.0268 0.6104 0.0276
-8.500 -0.5780 0.02149 0.01502 -0.0259 0.6091 0.0277
-8.250 -0.5444 0.01961 0.01295 -0.0275 0.6077 0.0281
-8.000 -0.5061 0.01842 0.01173 -0.0301 0.6061 0.0286
-7.750 -0.4788 0.01793 0.01122 -0.0302 0.6045 0.0289
-7.500 -0.4527 0.01753 0.01079 -0.0302 0.6028 0.0292
-7.250 -0.4227 0.01701 0.01023 -0.0308 0.6012 0.0295
-7.000 -0.3935 0.01658 0.00976 -0.0313 0.5996 0.0298
-6.750 -0.3622 0.01610 0.00923 -0.0322 0.5979 0.0301
-6.500 -0.3310 0.01565 0.00873 -0.0330 0.5960 0.0304
-6.250 -0.3013 0.01529 0.00832 -0.0335 0.5938 0.0307
-6.000 -0.2713 0.01492 0.00792 -0.0341 0.5923 0.0310
-5.750 -0.2422 0.01457 0.00756 -0.0345 0.5914 0.0314
-5.500 -0.2135 0.01423 0.00721 -0.0348 0.5903 0.0316
-5.250 -0.1858 0.01395 0.00692 -0.0350 0.5889 0.0319
-5.000 -0.1588 0.01372 0.00667 -0.0350 0.5872 0.0321
-4.750 -0.1299 0.01312 0.00608 -0.0354 0.5857 0.0329
-4.500 -0.1039 0.01286 0.00583 -0.0352 0.5842 0.0336
-4.250 -0.0780 0.01265 0.00562 -0.0350 0.5827 0.0342
-4.000 -0.0523 0.01247 0.00543 -0.0348 0.5810 0.0347
-3.750 -0.0268 0.01229 0.00524 -0.0345 0.5791 0.0354
-3.500 -0.0015 0.01214 0.00506 -0.0342 0.5772 0.0360
-3.250 0.0239 0.01203 0.00493 -0.0339 0.5754 0.0365
-3.000 0.0496 0.01187 0.00477 -0.0337 0.5747 0.0370
-2.750 0.0745 0.01159 0.00452 -0.0333 0.5739 0.0383
-2.500 0.1000 0.01144 0.00439 -0.0331 0.5729 0.0393
-2.250 0.1255 0.01132 0.00428 -0.0328 0.5719 0.0407
-2.000 0.1509 0.01120 0.00418 -0.0325 0.5708 0.0419
-1.750 0.1758 0.01104 0.00404 -0.0322 0.5697 0.0441
-1.500 0.2010 0.01093 0.00394 -0.0318 0.5681 0.0465
-1.250 0.2257 0.01080 0.00384 -0.0314 0.5667 0.0505
-1.000 0.2502 0.01067 0.00373 -0.0310 0.5649 0.0567
-0.750 0.2736 0.01052 0.00364 -0.0303 0.5629 0.0692
-0.500 0.2915 0.01020 0.00355 -0.0287 0.5611 0.1430
-0.250 0.2942 0.00960 0.00344 -0.0242 0.5594 0.2979
0.000 0.2678 0.00893 0.00332 -0.0137 0.5583 0.4660
0.250 0.2458 0.00837 0.00316 -0.0037 0.5576 0.5796
0.500 0.2172 0.00754 0.00316 0.0081 0.5567 0.8092
0.750 0.2446 0.00784 0.00348 0.0083 0.5555 0.8322
1.000 0.2721 0.00812 0.00376 0.0084 0.5542 0.8425
1.250 0.3074 0.00863 0.00431 0.0070 0.5530 0.8493
1.500 0.3371 0.00902 0.00469 0.0066 0.5519 0.8555
1.750 0.3710 0.00939 0.00507 0.0055 0.5504 0.8600
2.000 0.4238 0.01052 0.00625 0.0011 0.5492 0.8659
2.250 0.4578 0.01127 0.00698 0.0000 0.5476 0.8731
2.500 0.4927 0.01142 0.00712 -0.0013 0.5454 0.8759
2.750 0.5449 0.01199 0.00767 -0.0060 0.5434 0.8771
3.000 0.5798 0.01214 0.00781 -0.0077 0.5417 0.8776
3.250 0.5978 0.01194 0.00762 -0.0062 0.5407 0.8780
3.500 0.6163 0.01174 0.00744 -0.0048 0.5389 0.8784
3.750 0.6358 0.01156 0.00727 -0.0036 0.5367 0.8788
4.000 0.6560 0.01139 0.00710 -0.0025 0.5344 0.8791
4.250 0.6768 0.01125 0.00696 -0.0016 0.5321 0.8794
4.500 0.6982 0.01114 0.00683 -0.0008 0.5301 0.8798
4.750 0.7198 0.01106 0.00673 -0.0001 0.5276 0.8801
5.000 0.7422 0.01100 0.00666 0.0005 0.5254 0.8803
5.250 0.7653 0.01093 0.00663 0.0009 0.5236 0.8807
5.500 0.7889 0.01089 0.00661 0.0013 0.5217 0.8812
5.750 0.8115 0.01083 0.00658 0.0017 0.5190 0.8815
6.000 0.8337 0.01079 0.00654 0.0023 0.5163 0.8819
6.250 0.8548 0.01077 0.00652 0.0030 0.5133 0.8822
6.500 0.8745 0.01079 0.00652 0.0040 0.5103 0.8826
6.750 0.8948 0.01078 0.00655 0.0048 0.5076 0.8830
7.000 0.9136 0.01079 0.00660 0.0059 0.5040 0.8834
7.250 0.9241 0.01082 0.00664 0.0086 0.4998 0.8840
7.500 0.9212 0.01112 0.00693 0.0132 0.4947 0.8850
7.750 0.9307 0.01145 0.00728 0.0156 0.4876 0.8856
8.000 0.9319 0.01200 0.00780 0.0192 0.4784 0.8863
8.250 0.9330 0.01263 0.00840 0.0227 0.4646 0.8869
8.500 0.9276 0.01350 0.00921 0.0271 0.4474 0.8879
8.750 0.8716 0.01606 0.01153 0.0383 0.3941 0.8892
9.000 0.8249 0.01880 0.01408 0.0475 0.3589 0.8900
9.250 0.8019 0.02094 0.01613 0.0530 0.3393 0.8904
9.500 0.7979 0.02224 0.01739 0.0562 0.3296 0.8913
9.750 0.7948 0.02364 0.01875 0.0591 0.3215 0.8920
10.000 0.8030 0.02455 0.01967 0.0606 0.3152 0.8924
10.250 0.8084 0.02567 0.02078 0.0624 0.3096 0.8929
10.500 0.8133 0.02684 0.02194 0.0641 0.3037 0.8934
10.750 0.8255 0.02767 0.02279 0.0650 0.3003 0.8938
11.000 0.8376 0.02851 0.02365 0.0659 0.2947 0.8941
11.250 0.8427 0.02977 0.02489 0.0673 0.2872 0.8946
11.500 0.8540 0.03072 0.02585 0.0682 0.2838 0.8950
11.750 0.8660 0.03163 0.02677 0.0689 0.2748 0.8953
12.000 0.8718 0.03295 0.02805 0.0701 0.2639 0.8957
12.250 0.8757 0.03442 0.02947 0.0714 0.2506 0.8963
12.500 0.8754 0.03616 0.03111 0.0730 0.2301 0.8969
12.750 0.8753 0.03794 0.03281 0.0744 0.2139 0.8975
13.000 0.8801 0.03941 0.03421 0.0754 0.1996 0.8979
13.250 0.8818 0.04112 0.03582 0.0766 0.1790 0.8984
13.500 0.8725 0.04360 0.03806 0.0784 0.1407 0.8988
13.750 0.8787 0.04508 0.03946 0.0791 0.1295 0.8993
14.000 0.8879 0.04639 0.04075 0.0795 0.1237 0.8997
14.250 0.8988 0.04763 0.04201 0.0798 0.1199 0.9001
14.500 0.9115 0.04874 0.04313 0.0798 0.1175 0.9005
14.750 0.9218 0.05003 0.04441 0.0801 0.1135 0.9009
15.000 0.9326 0.05130 0.04568 0.0802 0.1096 0.9013
15.250 0.9458 0.05241 0.04683 0.0801 0.1068 0.9017
15.500 0.9580 0.05362 0.04807 0.0801 0.1034 0.9021
15.750 0.9691 0.05494 0.04939 0.0801 0.0999 0.9025
16.000 0.9802 0.05625 0.05071 0.0801 0.0952 0.9029
16.250 0.9926 0.05747 0.05191 0.0799 0.0861 0.9033
16.500 0.9857 0.06034 0.05454 0.0805 0.0588 0.9037
16.750 0.9909 0.06225 0.05644 0.0806 0.0538 0.9041
17.000 0.9966 0.06414 0.05833 0.0806 0.0497 0.9045
17.250 1.0021 0.06612 0.06035 0.0805 0.0477 0.9048
17.500 1.0068 0.06818 0.06242 0.0804 0.0454 0.9052
17.750 1.0151 0.06990 0.06418 0.0802 0.0439 0.9055
18.000 1.0224 0.07177 0.06609 0.0799 0.0427 0.9059
18.250 1.0281 0.07381 0.06817 0.0796 0.0413 0.9062
18.500 1.0331 0.07594 0.07032 0.0793 0.0401 0.9064
18.750 1.0354 0.07844 0.07286 0.0789 0.0387 0.9068
19.000 1.0435 0.08043 0.07491 0.0781 0.0379 0.9075
19.250 1.0526 0.08233 0.07686 0.0773 0.0371 0.9082
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