NACA 8-H-12 AIRFOIL (n8h12-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 8-H-12 AIRFOIL (n8h12-il) Reynolds number: 50,000 Max Cl/Cd: 18.6 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n8h12-il-50000-n5.txt Download as CSV file: xf-n8h12-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 8-H-12 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4366 0.08620 0.08035 -0.0312 0.8937 0.0603
-8.500 -0.4323 0.08294 0.07704 -0.0313 0.8792 0.0598
-8.250 -0.4326 0.07922 0.07325 -0.0326 0.8658 0.0596
-8.000 -0.4335 0.07532 0.06925 -0.0340 0.8535 0.0594
-7.750 -0.4329 0.07148 0.06527 -0.0351 0.8422 0.0593
-7.500 -0.4315 0.06762 0.06123 -0.0358 0.8318 0.0592
-7.250 -0.4278 0.06395 0.05733 -0.0360 0.8217 0.0590
-7.000 -0.4211 0.06025 0.05340 -0.0362 0.8116 0.0587
-6.750 -0.4140 0.05674 0.04959 -0.0357 0.8029 0.0584
-6.500 -0.4039 0.05324 0.04575 -0.0353 0.7934 0.0581
-6.250 -0.3930 0.04996 0.04203 -0.0344 0.7851 0.0585
-6.000 -0.3804 0.04684 0.03831 -0.0333 0.7765 0.0597
-5.750 -0.3650 0.04418 0.03524 -0.0321 0.7685 0.0611
-5.500 -0.3464 0.04205 0.03289 -0.0312 0.7601 0.0625
-5.250 -0.3267 0.03984 0.03030 -0.0302 0.7522 0.0635
-5.000 -0.3057 0.03789 0.02799 -0.0292 0.7444 0.0650
-4.750 -0.2834 0.03624 0.02594 -0.0282 0.7371 0.0682
-4.500 -0.2591 0.03460 0.02381 -0.0274 0.7292 0.0712
-4.250 -0.2340 0.03299 0.02178 -0.0263 0.7228 0.0731
-4.000 -0.2073 0.03162 0.02034 -0.0263 0.7145 0.0762
-3.750 -0.1816 0.03057 0.01908 -0.0254 0.7088 0.0817
-3.500 -0.1512 0.02956 0.01780 -0.0256 0.7006 0.0870
-3.250 -0.1227 0.02851 0.01672 -0.0254 0.6945 0.0930
-3.000 -0.0931 0.02776 0.01581 -0.0256 0.6875 0.1037
-2.750 -0.0656 0.02705 0.01503 -0.0254 0.6808 0.1177
-2.500 -0.0413 0.02624 0.01425 -0.0245 0.6760 0.1406
-2.250 -0.0170 0.02548 0.01382 -0.0246 0.6681 0.1915
-2.000 0.0840 0.02256 0.01353 -0.0344 0.6630 0.9530
-1.750 0.1517 0.02256 0.01299 -0.0420 0.6568 1.0000
-1.500 0.1747 0.02277 0.01293 -0.0417 0.6502 1.0000
-1.250 0.1962 0.02287 0.01276 -0.0406 0.6455 1.0000
-1.000 0.2204 0.02322 0.01292 -0.0407 0.6387 1.0000
-0.750 0.2432 0.02348 0.01297 -0.0402 0.6331 1.0000
-0.500 0.2651 0.02364 0.01291 -0.0391 0.6291 1.0000
-0.250 0.2894 0.02416 0.01331 -0.0394 0.6225 1.0000
0.000 0.3122 0.02450 0.01350 -0.0389 0.6172 1.0000
0.250 0.3343 0.02471 0.01354 -0.0378 0.6135 1.0000
0.500 0.3580 0.02534 0.01410 -0.0381 0.6073 1.0000
0.750 0.3808 0.02584 0.01451 -0.0378 0.6023 1.0000
1.000 0.4031 0.02616 0.01471 -0.0369 0.5985 1.0000
1.250 0.4256 0.02674 0.01521 -0.0366 0.5938 1.0000
1.500 0.4477 0.02750 0.01595 -0.0367 0.5879 1.0000
1.750 0.4698 0.02796 0.01634 -0.0360 0.5839 1.0000
2.000 0.4922 0.02831 0.01661 -0.0350 0.5811 1.0000
2.250 0.5122 0.02952 0.01787 -0.0355 0.5747 1.0000
2.500 0.5330 0.03024 0.01857 -0.0350 0.5700 1.0000
2.750 0.5549 0.03070 0.01900 -0.0341 0.5666 1.0000
3.000 0.5750 0.03155 0.01985 -0.0337 0.5625 1.0000
3.250 0.5911 0.03300 0.02137 -0.0338 0.5563 1.0000
3.500 0.6115 0.03367 0.02204 -0.0330 0.5524 1.0000
3.750 0.6338 0.03408 0.02246 -0.0320 0.5496 1.0000
4.000 0.6435 0.03615 0.02462 -0.0321 0.5424 1.0000
4.250 0.6604 0.03721 0.02572 -0.0314 0.5377 1.0000
4.500 0.6822 0.03770 0.02623 -0.0304 0.5346 1.0000
4.750 0.6891 0.03979 0.02842 -0.0300 0.5278 1.0000
5.000 0.7016 0.04122 0.02990 -0.0292 0.5221 1.0000
5.250 0.7237 0.04167 0.03041 -0.0281 0.5189 1.0000
5.500 0.7222 0.04441 0.03322 -0.0275 0.5105 1.0000
5.750 0.7378 0.04546 0.03436 -0.0266 0.5053 1.0000
6.000 0.7628 0.04565 0.03462 -0.0254 0.5024 1.0000
6.500 0.7754 0.04940 0.03853 -0.0237 0.4876 1.0000
7.000 0.7887 0.05279 0.04209 -0.0216 0.4727 1.0000
7.500 0.8019 0.05581 0.04527 -0.0189 0.4574 1.0000
8.000 0.8209 0.05843 0.04808 -0.0164 0.4417 1.0000
8.250 0.8187 0.06071 0.05046 -0.0153 0.4310 1.0000
8.500 0.8472 0.06033 0.05026 -0.0141 0.4253 1.0000
8.750 0.8437 0.06270 0.05271 -0.0131 0.4132 1.0000
9.000 0.8751 0.06173 0.05194 -0.0115 0.4070 1.0000
9.250 0.8813 0.06299 0.05335 -0.0103 0.3949 1.0000
9.500 0.8840 0.06464 0.05511 -0.0093 0.3819 1.0000
10.000 0.9036 0.06608 0.05685 -0.0068 0.3556 1.0000
10.250 0.9173 0.06595 0.05689 -0.0053 0.3403 1.0000
10.500 0.9341 0.06512 0.05626 -0.0035 0.3233 1.0000
10.750 0.9541 0.06364 0.05497 -0.0016 0.3048 1.0000
11.000 0.9513 0.06594 0.05738 -0.0012 0.2826 1.0000
11.250 0.9674 0.06532 0.05687 0.0003 0.2553 1.0000
11.500 0.9912 0.06325 0.05459 0.0029 0.2125 1.0000
11.750 0.9948 0.06443 0.05532 0.0043 0.1763 1.0000
12.000 0.9896 0.06746 0.05809 0.0046 0.1516 1.0000
12.250 0.9843 0.07066 0.06101 0.0047 0.1337 1.0000
12.500 0.9811 0.07385 0.06400 0.0046 0.1196 1.0000
12.750 0.9794 0.07697 0.06703 0.0046 0.1074 1.0000
13.000 0.9808 0.07980 0.06984 0.0047 0.0977 1.0000
13.250 0.9838 0.08240 0.07241 0.0049 0.0905 1.0000
13.500 0.9878 0.08496 0.07500 0.0050 0.0839 1.0000
13.750 0.9943 0.08720 0.07724 0.0054 0.0790 1.0000
14.000 0.9999 0.08978 0.07999 0.0055 0.0741 1.0000
14.250 1.0075 0.09187 0.08205 0.0059 0.0704 1.0000
14.500 1.0142 0.09444 0.08477 0.0061 0.0672 1.0000
14.750 1.0196 0.09744 0.08805 0.0060 0.0649 1.0000
15.000 1.0230 0.10074 0.09156 0.0056 0.0628 1.0000
15.250 1.0261 0.10402 0.09496 0.0051 0.0609 1.0000
15.500 1.0364 0.10593 0.09686 0.0055 0.0587 1.0000
15.750 1.0276 0.11154 0.10273 0.0033 0.0578 1.0000
16.000 1.0135 0.11835 0.10983 0.0002 0.0573 1.0000
16.250 0.9944 0.12650 0.11823 -0.0040 0.0570 1.0000
16.500 0.9713 0.13613 0.12807 -0.0091 0.0571 1.0000
16.750 0.9427 0.14810 0.14019 -0.0158 0.0573 1.0000
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Polar data table (+)
Polar graphs
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