HT12 (ht12-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT12 (ht12-il) Reynolds number: 50,000 Max Cl/Cd: 20.29 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht12-il-50000-n5.txt Download as CSV file: xf-ht12-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HT12
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.7379 0.10393 0.09710 0.0348 1.0000 0.0496
-8.500 -0.7382 0.09898 0.09220 0.0317 1.0000 0.0494
-8.250 -0.7388 0.09383 0.08710 0.0279 1.0000 0.0493
-8.000 -0.7377 0.08808 0.08139 0.0227 1.0000 0.0492
-7.750 -0.7342 0.08169 0.07499 0.0169 1.0000 0.0490
-7.500 -0.7288 0.07496 0.06818 0.0112 1.0000 0.0489
-7.250 -0.7218 0.06810 0.06116 0.0060 1.0000 0.0488
-7.000 -0.7126 0.06136 0.05415 0.0015 1.0000 0.0487
-6.750 -0.7003 0.05488 0.04726 -0.0020 1.0000 0.0485
-6.500 -0.6843 0.04899 0.04087 -0.0045 1.0000 0.0487
-6.250 -0.6651 0.04380 0.03503 -0.0060 1.0000 0.0494
-6.000 -0.6431 0.03936 0.02994 -0.0069 1.0000 0.0511
-5.750 -0.6185 0.03557 0.02526 -0.0074 1.0000 0.0551
-5.500 -0.5946 0.03273 0.02217 -0.0074 1.0000 0.0586
-5.250 -0.5688 0.03015 0.01919 -0.0071 1.0000 0.0620
-5.000 -0.5416 0.02791 0.01638 -0.0067 1.0000 0.0682
-4.750 -0.5163 0.02616 0.01456 -0.0064 1.0000 0.0765
-4.500 -0.4898 0.02430 0.01246 -0.0058 1.0000 0.0841
-4.250 -0.4637 0.02294 0.01104 -0.0054 1.0000 0.0994
-4.000 -0.4369 0.02154 0.00956 -0.0050 1.0000 0.1176
-3.750 -0.4101 0.02031 0.00839 -0.0048 1.0000 0.1512
-3.500 -0.3836 0.01910 0.00737 -0.0046 1.0000 0.2047
-3.250 -0.3579 0.01806 0.00669 -0.0044 1.0000 0.2833
-3.000 -0.3327 0.01718 0.00613 -0.0039 1.0000 0.3735
-2.750 -0.3087 0.01630 0.00564 -0.0029 1.0000 0.4677
-2.500 -0.2874 0.01533 0.00522 -0.0010 1.0000 0.5817
-2.250 -0.2673 0.01433 0.00492 0.0025 1.0000 0.7674
-2.000 -0.2112 0.01380 0.00432 -0.0020 1.0000 1.0000
-1.750 -0.1849 0.01370 0.00393 -0.0018 1.0000 1.0000
-1.500 -0.1586 0.01361 0.00358 -0.0016 1.0000 1.0000
-1.250 -0.1322 0.01355 0.00332 -0.0014 1.0000 1.0000
-1.000 -0.1058 0.01350 0.00312 -0.0011 1.0000 1.0000
-0.750 -0.0794 0.01346 0.00297 -0.0008 1.0000 1.0000
-0.500 -0.0529 0.01343 0.00286 -0.0006 1.0000 1.0000
-0.250 -0.0264 0.01342 0.00278 -0.0003 1.0000 1.0000
0.000 0.0001 0.01341 0.00276 0.0000 1.0000 1.0000
0.250 0.0266 0.01342 0.00278 0.0003 1.0000 1.0000
0.500 0.0531 0.01343 0.00285 0.0006 1.0000 1.0000
0.750 0.0795 0.01346 0.00297 0.0008 1.0000 1.0000
1.000 0.1060 0.01350 0.00312 0.0011 1.0000 1.0000
1.250 0.1324 0.01355 0.00332 0.0014 1.0000 1.0000
1.500 0.1587 0.01361 0.00358 0.0016 1.0000 1.0000
1.750 0.1851 0.01370 0.00393 0.0018 1.0000 1.0000
2.000 0.2114 0.01380 0.00433 0.0020 1.0000 1.0000
2.250 0.2675 0.01433 0.00492 -0.0025 0.7656 1.0000
2.500 0.2875 0.01533 0.00523 0.0010 0.5809 1.0000
2.750 0.3089 0.01631 0.00564 0.0029 0.4671 1.0000
3.000 0.3329 0.01718 0.00614 0.0039 0.3729 1.0000
3.250 0.3580 0.01806 0.00669 0.0044 0.2827 1.0000
3.500 0.3838 0.01911 0.00738 0.0046 0.2043 1.0000
3.750 0.4103 0.02031 0.00839 0.0047 0.1510 1.0000
4.000 0.4371 0.02154 0.00957 0.0049 0.1175 1.0000
4.250 0.4639 0.02295 0.01105 0.0054 0.0994 1.0000
4.500 0.4900 0.02431 0.01247 0.0058 0.0841 1.0000
4.750 0.5165 0.02618 0.01457 0.0064 0.0764 1.0000
5.000 0.5418 0.02793 0.01639 0.0067 0.0682 1.0000
5.250 0.5690 0.03016 0.01921 0.0071 0.0619 1.0000
5.500 0.5948 0.03275 0.02219 0.0074 0.0586 1.0000
5.750 0.6187 0.03559 0.02528 0.0073 0.0550 1.0000
6.000 0.6433 0.03939 0.02997 0.0069 0.0510 1.0000
6.250 0.6653 0.04384 0.03507 0.0060 0.0493 1.0000
6.500 0.6845 0.04904 0.04091 0.0044 0.0486 1.0000
6.750 0.7005 0.05493 0.04732 0.0019 0.0485 1.0000
7.000 0.7128 0.06143 0.05422 -0.0016 0.0487 1.0000
7.250 0.7220 0.06820 0.06126 -0.0061 0.0489 1.0000
7.500 0.7290 0.07506 0.06829 -0.0113 0.0490 1.0000
7.750 0.7344 0.08180 0.07510 -0.0170 0.0491 1.0000
8.000 0.7380 0.08818 0.08149 -0.0229 0.0492 1.0000
8.250 0.7392 0.09393 0.08720 -0.0280 0.0494 1.0000
8.500 0.7387 0.09908 0.09230 -0.0318 0.0495 1.0000
8.750 0.7384 0.10403 0.09719 -0.0349 0.0497 1.0000
9.000 0.7386 0.10885 0.10197 -0.0376 0.0500 1.0000
9.250 0.7393 0.11361 0.10668 -0.0400 0.0508 1.0000
9.500 0.7412 0.11825 0.11129 -0.0419 0.0521 1.0000
9.750 0.7449 0.12273 0.11575 -0.0430 0.0537 1.0000
10.500 0.6054 0.12654 0.11979 -0.0329 0.0616 1.0000
10.750 0.6066 0.13082 0.12406 -0.0338 0.0652 1.0000
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Polar data table (+)
Polar graphs
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