NREL's S816 Airfoil (s816-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S816 Airfoil (s816-nr) Reynolds number: 1,000,000 Max Cl/Cd: 121.37 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s816-nr-1000000.txt Download as CSV file: xf-s816-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S816 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.2978 0.09036 0.08799 -0.0898 0.7841 0.0081
-13.750 -0.3266 0.08202 0.07955 -0.0934 0.7794 0.0081
-13.500 -0.3533 0.07483 0.07223 -0.0958 0.7714 0.0081
-13.250 -0.3769 0.06898 0.06625 -0.0974 0.7621 0.0081
-13.000 -0.3998 0.06329 0.06042 -0.0984 0.7532 0.0081
-11.750 -0.5271 0.03551 0.03037 -0.0959 0.7519 0.0044
-11.500 -0.5044 0.03536 0.02999 -0.0941 0.7361 0.0043
-11.250 -0.4872 0.03489 0.02939 -0.0932 0.7224 0.0047
-11.000 -0.4697 0.03449 0.02888 -0.0922 0.7114 0.0048
-10.750 -0.4527 0.03420 0.02846 -0.0909 0.7009 0.0047
-10.500 -0.4369 0.03376 0.02794 -0.0898 0.6917 0.0049
-10.250 -0.4216 0.03320 0.02729 -0.0890 0.6837 0.0051
-10.000 -0.4040 0.03252 0.02654 -0.0889 0.6762 0.0054
-9.750 -0.3932 0.03193 0.02587 -0.0873 0.6697 0.0054
-9.500 -0.3874 0.03095 0.02485 -0.0856 0.6638 0.0058
-9.250 -0.3774 0.03004 0.02391 -0.0846 0.6583 0.0062
-9.000 -0.3691 0.02904 0.02285 -0.0835 0.6536 0.0062
-8.750 -0.3618 0.02794 0.02172 -0.0824 0.6490 0.0065
-8.500 -0.3545 0.02685 0.02058 -0.0812 0.6447 0.0067
-8.250 -0.3493 0.02565 0.01932 -0.0799 0.6405 0.0071
-8.000 -0.3467 0.02422 0.01785 -0.0784 0.6374 0.0071
-7.750 -0.3391 0.02307 0.01667 -0.0773 0.6341 0.0073
-7.500 -0.3388 0.02150 0.01504 -0.0756 0.6308 0.0076
-7.250 -0.3455 0.01950 0.01297 -0.0733 0.6278 0.0081
-7.000 -0.3396 0.01826 0.01167 -0.0720 0.6247 0.0080
-6.750 -0.3416 0.01655 0.00992 -0.0700 0.6222 0.0090
-6.500 -0.3367 0.01547 0.00880 -0.0683 0.6197 0.0101
-6.250 -0.3408 0.01425 0.00749 -0.0654 0.6173 0.0111
-6.000 -0.3239 0.01378 0.00699 -0.0647 0.6149 0.0139
-5.750 -0.3078 0.01322 0.00639 -0.0638 0.6126 0.0177
-5.500 -0.2882 0.01278 0.00592 -0.0633 0.6102 0.0217
-5.250 -0.2654 0.01242 0.00553 -0.0632 0.6088 0.0258
-5.000 -0.2415 0.01210 0.00521 -0.0632 0.6072 0.0311
-4.750 -0.2181 0.01170 0.00486 -0.0632 0.6055 0.0445
-4.500 -0.1940 0.01132 0.00455 -0.0633 0.6039 0.0692
-4.250 -0.1695 0.01093 0.00423 -0.0635 0.6023 0.1020
-4.000 -0.1596 0.00850 0.00276 -0.0630 0.6008 0.3993
-3.750 -0.1312 0.00841 0.00269 -0.0636 0.5993 0.4212
-3.500 -0.1025 0.00838 0.00265 -0.0642 0.5976 0.4325
-3.250 -0.0734 0.00840 0.00263 -0.0648 0.5959 0.4395
-3.000 -0.0441 0.00842 0.00264 -0.0655 0.5947 0.4454
-2.750 -0.0144 0.00847 0.00265 -0.0661 0.5938 0.4509
-2.500 0.0147 0.00845 0.00264 -0.0668 0.5928 0.4558
-2.250 0.0441 0.00845 0.00263 -0.0674 0.5917 0.4584
-2.000 0.0736 0.00849 0.00264 -0.0681 0.5904 0.4612
-1.750 0.1030 0.00851 0.00262 -0.0688 0.5892 0.4629
-1.500 0.1325 0.00854 0.00262 -0.0695 0.5881 0.4644
-1.250 0.1614 0.00848 0.00258 -0.0701 0.5871 0.4673
-1.000 0.1906 0.00847 0.00256 -0.0707 0.5861 0.4689
-0.750 0.2199 0.00847 0.00256 -0.0714 0.5851 0.4702
-0.500 0.2492 0.00849 0.00256 -0.0721 0.5841 0.4716
-0.250 0.2786 0.00852 0.00258 -0.0728 0.5830 0.4729
0.000 0.3081 0.00856 0.00261 -0.0735 0.5819 0.4743
0.250 0.3377 0.00863 0.00266 -0.0742 0.5807 0.4757
0.500 0.3673 0.00867 0.00270 -0.0750 0.5800 0.4770
0.750 0.3967 0.00870 0.00273 -0.0757 0.5794 0.4782
1.000 0.4260 0.00871 0.00276 -0.0763 0.5788 0.4794
1.250 0.4552 0.00869 0.00278 -0.0770 0.5782 0.4818
1.500 0.4845 0.00870 0.00283 -0.0777 0.5775 0.4837
1.750 0.5138 0.00872 0.00288 -0.0784 0.5767 0.4855
2.000 0.5430 0.00875 0.00294 -0.0791 0.5758 0.4874
2.250 0.5723 0.00878 0.00301 -0.0797 0.5749 0.4892
2.500 0.6017 0.00883 0.00308 -0.0804 0.5741 0.4911
2.750 0.6310 0.00889 0.00316 -0.0811 0.5734 0.4927
3.000 0.6604 0.00894 0.00323 -0.0818 0.5726 0.4942
3.250 0.6897 0.00896 0.00331 -0.0825 0.5719 0.4970
3.500 0.7190 0.00900 0.00340 -0.0832 0.5712 0.4993
3.750 0.7483 0.00906 0.00351 -0.0839 0.5704 0.5014
4.000 0.7776 0.00912 0.00361 -0.0846 0.5696 0.5036
4.250 0.8069 0.00919 0.00372 -0.0853 0.5686 0.5057
4.500 0.8363 0.00934 0.00387 -0.0861 0.5659 0.5075
4.750 0.8623 0.00921 0.00382 -0.0860 0.5617 0.5094
5.000 0.8876 0.00901 0.00365 -0.0857 0.5540 0.5123
5.250 0.9130 0.00894 0.00363 -0.0855 0.5463 0.5148
5.500 0.9388 0.00886 0.00360 -0.0854 0.5396 0.5173
5.750 0.9658 0.00893 0.00368 -0.0856 0.5349 0.5197
6.000 0.9926 0.00890 0.00374 -0.0857 0.5302 0.5220
6.250 1.0188 0.00890 0.00379 -0.0857 0.5238 0.5242
6.500 1.0448 0.00890 0.00386 -0.0857 0.5154 0.5274
6.750 1.0697 0.00893 0.00394 -0.0855 0.5047 0.5303
7.000 1.0935 0.00901 0.00404 -0.0851 0.4845 0.5333
7.250 1.0957 0.00981 0.00447 -0.0807 0.4070 0.5357
7.500 1.0839 0.01098 0.00526 -0.0738 0.3339 0.5376
7.750 1.0732 0.01214 0.00612 -0.0674 0.2747 0.5396
8.000 1.0638 0.01334 0.00708 -0.0616 0.2219 0.5424
8.250 1.0575 0.01451 0.00808 -0.0566 0.1812 0.5453
8.500 1.0531 0.01573 0.00915 -0.0523 0.1480 0.5481
8.750 1.0510 0.01699 0.01031 -0.0487 0.1219 0.5511
9.000 1.0494 0.01838 0.01160 -0.0456 0.0994 0.5535
9.250 1.0511 0.01975 0.01293 -0.0431 0.0823 0.5570
9.500 1.0564 0.02104 0.01421 -0.0413 0.0709 0.5607
9.750 1.0617 0.02240 0.01556 -0.0396 0.0603 0.5643
10.000 1.0675 0.02381 0.01695 -0.0381 0.0518 0.5677
10.250 1.0733 0.02526 0.01839 -0.0367 0.0438 0.5713
10.500 1.0826 0.02651 0.01969 -0.0356 0.0390 0.5755
10.750 1.0889 0.02800 0.02118 -0.0344 0.0340 0.5798
11.000 1.0982 0.02933 0.02252 -0.0336 0.0297 0.5837
11.250 1.1059 0.03077 0.02399 -0.0326 0.0268 0.5882
11.500 1.1162 0.03205 0.02533 -0.0319 0.0245 0.5934
11.750 1.1259 0.03342 0.02673 -0.0312 0.0226 0.5982
12.000 1.1333 0.03497 0.02831 -0.0303 0.0201 0.6034
12.250 1.1442 0.03627 0.02969 -0.0298 0.0187 0.6092
12.500 1.1544 0.03767 0.03112 -0.0293 0.0171 0.6151
12.750 1.1630 0.03921 0.03271 -0.0287 0.0156 0.6212
13.000 1.1730 0.04066 0.03422 -0.0283 0.0144 0.6277
13.250 1.1834 0.04211 0.03573 -0.0279 0.0133 0.6339
13.500 1.1926 0.04368 0.03735 -0.0275 0.0122 0.6414
13.750 1.2003 0.04543 0.03915 -0.0271 0.0111 0.6482
14.000 1.2121 0.04683 0.04063 -0.0269 0.0104 0.6562
14.250 1.2220 0.04843 0.04231 -0.0267 0.0096 0.6638
14.500 1.2300 0.05021 0.04413 -0.0264 0.0086 0.6719
14.750 1.2392 0.05192 0.04592 -0.0263 0.0080 0.6808
15.000 1.2489 0.05362 0.04770 -0.0262 0.0073 0.6900
15.250 1.2576 0.05543 0.04959 -0.0261 0.0068 0.7004
15.500 1.2638 0.05751 0.05174 -0.0260 0.0059 0.7106
15.750 1.2735 0.05928 0.05359 -0.0261 0.0054 0.7219
16.000 1.2817 0.06122 0.05562 -0.0261 0.0049 0.7340
16.250 1.2877 0.06344 0.05793 -0.0262 0.0044 0.7467
16.500 1.2929 0.06579 0.06040 -0.0263 0.0037 0.7609
16.750 1.2998 0.06796 0.06270 -0.0265 0.0036 0.7783
17.000 1.3054 0.07030 0.06516 -0.0267 0.0031 0.7994
17.250 1.3063 0.07319 0.06820 -0.0269 0.0027 0.8257
17.500 1.3082 0.07578 0.07103 -0.0268 0.0025 0.8743
17.750 1.3112 0.07787 0.07337 -0.0265 0.0022 1.0000
18.000 1.3144 0.08076 0.07634 -0.0271 0.0022 1.0000
18.250 1.3162 0.08388 0.07954 -0.0278 0.0020 1.0000
18.500 1.3189 0.08690 0.08262 -0.0286 0.0018 1.0000
18.750 1.3163 0.09074 0.08654 -0.0295 0.0016 1.0000
19.000 1.3142 0.09458 0.09049 -0.0306 0.0016 1.0000
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