NACA 5-H-15 AIRFOIL (n5h15-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 5-H-15 AIRFOIL (n5h15-il) Reynolds number: 200,000 Max Cl/Cd: 69.98 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n5h15-il-200000.txt Download as CSV file: xf-n5h15-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 5-H-15 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3427 0.09204 0.08854 -0.0471 0.7864 0.0697
-10.250 -0.3754 0.08444 0.08090 -0.0538 0.7849 0.0698
-10.000 -0.4029 0.07959 0.07598 -0.0558 0.7828 0.0699
-9.750 -0.4294 0.07588 0.07216 -0.0553 0.7806 0.0700
-9.500 -0.3583 0.07141 0.06789 -0.0536 0.7785 0.0730
-9.250 -0.3715 0.06686 0.06330 -0.0550 0.7769 0.0738
-9.000 -0.3874 0.06255 0.05895 -0.0557 0.7747 0.0745
-8.750 -0.5062 0.06566 0.06148 -0.0506 0.7773 0.0723
-8.500 -0.4967 0.06330 0.05913 -0.0498 0.7748 0.0737
-8.250 -0.4926 0.06095 0.05673 -0.0486 0.7715 0.0752
-8.000 -0.4918 0.05857 0.05423 -0.0467 0.7682 0.0775
-7.750 -0.5138 0.05940 0.05437 -0.0400 0.7648 0.0836
-7.500 -0.5150 0.05358 0.04844 -0.0382 0.7624 0.0855
-7.250 -0.4958 0.05075 0.04572 -0.0383 0.7596 0.0875
-7.000 -0.4807 0.04890 0.04384 -0.0376 0.7554 0.0908
-6.500 -0.4672 0.04471 0.03916 -0.0325 0.7485 0.1021
-6.250 -0.4516 0.04306 0.03742 -0.0309 0.7459 0.1063
-6.000 -0.4429 0.04142 0.03551 -0.0287 0.7416 0.1164
-5.750 -0.4231 0.03977 0.03385 -0.0279 0.7372 0.1213
-5.500 -0.4109 0.03820 0.03207 -0.0258 0.7339 0.1328
-5.250 -0.3975 0.03703 0.03071 -0.0236 0.7313 0.1470
-5.000 -0.3629 0.03153 0.02347 -0.0185 0.7296 0.0703
-4.750 -0.3332 0.02837 0.02025 -0.0196 0.7253 0.0673
-4.500 -0.3055 0.02684 0.01853 -0.0196 0.7217 0.0661
-4.250 -0.2783 0.02577 0.01728 -0.0193 0.7188 0.0668
-4.000 -0.2501 0.02474 0.01609 -0.0191 0.7163 0.0673
-3.750 -0.2204 0.02365 0.01484 -0.0191 0.7143 0.0673
-3.500 -0.1897 0.02294 0.01411 -0.0200 0.7095 0.0676
-3.250 -0.1600 0.02224 0.01336 -0.0204 0.7057 0.0684
-3.000 -0.1315 0.02157 0.01263 -0.0205 0.7028 0.0693
-2.750 -0.1037 0.02075 0.01178 -0.0203 0.7004 0.0709
-2.500 -0.0793 0.01985 0.01092 -0.0196 0.6985 0.0744
-2.250 -0.0564 0.01962 0.01078 -0.0193 0.6927 0.0773
-2.000 -0.0343 0.01922 0.01037 -0.0182 0.6890 0.0805
-1.750 -0.0122 0.01880 0.00989 -0.0170 0.6861 0.0844
-1.500 0.0086 0.01824 0.00930 -0.0154 0.6838 0.0928
-1.250 0.0283 0.01798 0.00922 -0.0142 0.6786 0.1178
-1.000 0.0709 0.01719 0.01137 -0.0136 0.6749 0.8889
-0.750 0.2336 0.01955 0.01341 -0.0357 0.6722 0.9377
-0.500 0.3772 0.01897 0.01258 -0.0569 0.6694 0.9829
-0.250 0.4240 0.01827 0.01179 -0.0611 0.6657 0.9904
0.000 0.4651 0.01781 0.01131 -0.0645 0.6597 0.9968
0.250 0.4981 0.01735 0.01078 -0.0660 0.6558 1.0000
0.500 0.5202 0.01713 0.01047 -0.0651 0.6528 1.0000
0.750 0.5427 0.01716 0.01052 -0.0648 0.6465 1.0000
1.000 0.5651 0.01702 0.01036 -0.0642 0.6416 1.0000
1.250 0.5877 0.01683 0.01009 -0.0635 0.6382 1.0000
1.500 0.6102 0.01684 0.01011 -0.0630 0.6326 1.0000
1.750 0.6329 0.01678 0.01006 -0.0625 0.6270 1.0000
2.000 0.6558 0.01663 0.00984 -0.0618 0.6232 1.0000
2.250 0.6786 0.01664 0.00986 -0.0613 0.6181 1.0000
2.500 0.7014 0.01667 0.00992 -0.0608 0.6121 1.0000
2.750 0.7246 0.01657 0.00978 -0.0602 0.6083 1.0000
3.000 0.7476 0.01658 0.00979 -0.0597 0.6039 1.0000
3.250 0.7702 0.01671 0.00998 -0.0593 0.5976 1.0000
3.500 0.7935 0.01667 0.00994 -0.0587 0.5937 1.0000
3.750 0.8173 0.01663 0.00985 -0.0581 0.5909 1.0000
4.000 0.8392 0.01696 0.01032 -0.0578 0.5849 1.0000
4.250 0.8622 0.01708 0.01049 -0.0573 0.5808 1.0000
4.500 0.8856 0.01713 0.01055 -0.0568 0.5779 1.0000
4.750 0.9096 0.01716 0.01056 -0.0563 0.5755 1.0000
5.000 0.9305 0.01759 0.01117 -0.0559 0.5698 1.0000
5.250 0.9534 0.01760 0.01124 -0.0553 0.5652 1.0000
5.500 0.9783 0.01715 0.01069 -0.0544 0.5602 1.0000
5.750 0.9991 0.01705 0.01072 -0.0535 0.5503 1.0000
6.000 1.0218 0.01672 0.01041 -0.0525 0.5413 1.0000
6.250 1.0446 0.01638 0.01005 -0.0515 0.5318 1.0000
6.500 1.0655 0.01640 0.01019 -0.0506 0.5222 1.0000
6.750 1.0878 0.01629 0.01009 -0.0497 0.5139 1.0000
7.000 1.1085 0.01625 0.01011 -0.0486 0.5023 1.0000
7.250 1.1277 0.01622 0.01007 -0.0472 0.4848 1.0000
7.500 1.1455 0.01637 0.01027 -0.0458 0.4665 1.0000
7.750 1.1615 0.01665 0.01052 -0.0441 0.4456 1.0000
8.000 1.1737 0.01714 0.01097 -0.0419 0.4183 1.0000
8.250 1.1798 0.01789 0.01163 -0.0389 0.3807 1.0000
8.500 1.1664 0.01935 0.01275 -0.0335 0.2876 1.0000
8.750 1.1351 0.02110 0.01424 -0.0255 0.2540 1.0000
9.000 1.1055 0.02239 0.01551 -0.0177 0.2427 1.0000
9.250 1.0780 0.02398 0.01702 -0.0107 0.2252 1.0000
9.500 1.0519 0.02570 0.01865 -0.0043 0.2047 1.0000
9.750 1.0240 0.02765 0.02046 0.0020 0.1772 1.0000
10.000 1.0003 0.02959 0.02225 0.0075 0.1500 1.0000
10.250 0.9758 0.03186 0.02430 0.0126 0.1183 1.0000
10.500 0.9559 0.03420 0.02643 0.0168 0.0873 1.0000
10.750 0.9356 0.03692 0.02890 0.0205 0.0608 1.0000
11.000 0.9265 0.03917 0.03106 0.0231 0.0490 1.0000
11.250 0.9236 0.04116 0.03306 0.0251 0.0431 1.0000
11.500 0.9222 0.04315 0.03506 0.0267 0.0399 1.0000
11.750 0.9208 0.04526 0.03721 0.0283 0.0378 1.0000
12.000 0.9218 0.04726 0.03928 0.0296 0.0356 1.0000
12.250 0.9240 0.04919 0.04129 0.0306 0.0350 1.0000
12.500 0.9251 0.05129 0.04343 0.0317 0.0337 1.0000
12.750 0.9245 0.05357 0.04571 0.0328 0.0323 1.0000
13.000 0.9259 0.05566 0.04781 0.0338 0.0312 1.0000
13.250 0.9318 0.05735 0.04956 0.0347 0.0304 1.0000
13.500 0.9390 0.05888 0.05113 0.0357 0.0298 1.0000
13.750 0.9466 0.06041 0.05270 0.0366 0.0284 1.0000
14.000 0.9569 0.06158 0.05391 0.0377 0.0280 1.0000
14.250 0.9685 0.06262 0.05496 0.0388 0.0274 1.0000
14.500 0.9826 0.06340 0.05573 0.0400 0.0268 1.0000
14.750 1.0003 0.06386 0.05620 0.0414 0.0266 1.0000
15.000 1.0267 0.06367 0.05601 0.0434 0.0260 1.0000
15.250 1.0586 0.06377 0.05618 0.0453 0.0256 1.0000
15.500 1.0590 0.06619 0.05882 0.0457 0.0252 1.0000
15.750 1.0715 0.06801 0.06082 0.0466 0.0251 1.0000
16.000 1.0745 0.07051 0.06352 0.0471 0.0248 1.0000
16.250 1.0804 0.07309 0.06631 0.0478 0.0249 1.0000
16.500 1.0817 0.07622 0.06965 0.0483 0.0249 1.0000
16.750 1.0785 0.07975 0.07341 0.0485 0.0250 1.0000
17.000 1.0774 0.08349 0.07734 0.0487 0.0253 1.0000
17.250 1.0705 0.08771 0.08176 0.0486 0.0254 1.0000
17.500 1.0729 0.09086 0.08504 0.0485 0.0258 1.0000
17.750 1.0564 0.09535 0.08978 0.0474 0.0261 1.0000
18.000 1.0222 0.10275 0.09756 0.0450 0.0267 1.0000
18.250 0.9619 0.11558 0.11091 0.0396 0.0282 1.0000
18.500 0.9310 0.12461 0.12016 0.0354 0.0288 1.0000
18.750 0.9008 0.13421 0.12995 0.0305 0.0294 1.0000
19.000 0.8737 0.14399 0.13986 0.0253 0.0301 1.0000
19.250 0.8477 0.15447 0.15044 0.0196 0.0308 1.0000
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