NREL's S816 Airfoil (s816-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S816 Airfoil (s816-nr) Reynolds number: 1,000,000 Max Cl/Cd: 108.85 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s816-nr-1000000-n5.txt Download as CSV file: xf-s816-nr-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7940 0.06336 0.06046 -0.0758 0.9908 0.0019
-15.750 -0.7963 0.05902 0.05585 -0.0769 0.9865 0.0019
-15.500 -0.7925 0.05517 0.05175 -0.0788 0.9814 0.0019
-15.250 -0.7712 0.05237 0.04875 -0.0825 0.9730 0.0019
-15.000 -0.7210 0.04902 0.04514 -0.0925 0.9463 0.0020
-14.750 -0.6925 0.04738 0.04282 -0.0961 0.8148 0.0020
-14.500 -0.6853 0.04617 0.04133 -0.0948 0.7807 0.0020
-14.250 -0.6741 0.04514 0.04009 -0.0940 0.7584 0.0020
-14.000 -0.6610 0.04423 0.03904 -0.0935 0.7405 0.0020
-13.750 -0.6508 0.04323 0.03781 -0.0920 0.7270 0.0022
-13.500 -0.6364 0.04246 0.03694 -0.0915 0.7147 0.0023
-13.250 -0.6205 0.04173 0.03616 -0.0913 0.7032 0.0026
-13.000 -0.6058 0.04103 0.03535 -0.0906 0.6939 0.0026
-12.750 -0.5910 0.04033 0.03455 -0.0900 0.6850 0.0025
-12.500 -0.5759 0.03965 0.03379 -0.0894 0.6770 0.0026
-12.250 -0.5600 0.03896 0.03306 -0.0891 0.6695 0.0027
-12.000 -0.5449 0.03828 0.03230 -0.0886 0.6623 0.0028
-11.500 -0.5159 0.03685 0.03074 -0.0874 0.6502 0.0029
-11.250 -0.5011 0.03613 0.02997 -0.0870 0.6444 0.0031
-11.000 -0.4869 0.03537 0.02916 -0.0864 0.6400 0.0031
-10.750 -0.4737 0.03455 0.02830 -0.0858 0.6358 0.0031
-10.500 -0.4616 0.03368 0.02738 -0.0851 0.6314 0.0032
-10.250 -0.4490 0.03282 0.02647 -0.0845 0.6273 0.0033
-10.000 -0.4360 0.03196 0.02557 -0.0839 0.6239 0.0034
-9.750 -0.4273 0.03086 0.02443 -0.0830 0.6206 0.0034
-9.500 -0.4157 0.02993 0.02348 -0.0823 0.6171 0.0035
-9.250 -0.4096 0.02875 0.02225 -0.0811 0.6140 0.0037
-8.750 -0.3977 0.02629 0.01972 -0.0788 0.6085 0.0039
-8.500 -0.3916 0.02504 0.01844 -0.0777 0.6060 0.0040
-8.250 -0.3871 0.02368 0.01705 -0.0764 0.6035 0.0044
-8.000 -0.3824 0.02235 0.01567 -0.0751 0.6009 0.0043
-7.750 -0.3759 0.02111 0.01439 -0.0739 0.5985 0.0045
-7.250 -0.3688 0.01828 0.01146 -0.0711 0.5944 0.0053
-7.000 -0.3623 0.01706 0.01020 -0.0698 0.5925 0.0052
-6.750 -0.3620 0.01564 0.00874 -0.0677 0.5904 0.0060
-6.500 -0.3638 0.01458 0.00764 -0.0650 0.5884 0.0068
-6.250 -0.3500 0.01397 0.00697 -0.0641 0.5864 0.0079
-6.000 -0.3322 0.01350 0.00647 -0.0634 0.5843 0.0103
-5.750 -0.3122 0.01310 0.00605 -0.0629 0.5825 0.0127
-5.250 -0.2670 0.01247 0.00536 -0.0626 0.5795 0.0175
-5.000 -0.2430 0.01216 0.00505 -0.0627 0.5783 0.0213
-4.750 -0.2184 0.01188 0.00477 -0.0628 0.5770 0.0267
-4.500 -0.1935 0.01158 0.00450 -0.0629 0.5757 0.0371
-4.250 -0.1681 0.01131 0.00426 -0.0632 0.5744 0.0510
-4.000 -0.1423 0.01104 0.00403 -0.0634 0.5731 0.0687
-3.750 -0.1159 0.01081 0.00382 -0.0638 0.5718 0.0862
-3.500 -0.0949 0.00984 0.00322 -0.0639 0.5706 0.2215
-3.250 -0.0751 0.00842 0.00235 -0.0641 0.5694 0.3987
-3.000 -0.0466 0.00833 0.00228 -0.0647 0.5683 0.4120
-2.750 -0.0179 0.00828 0.00223 -0.0653 0.5671 0.4238
-2.500 0.0109 0.00825 0.00220 -0.0659 0.5659 0.4316
-2.250 0.0400 0.00825 0.00217 -0.0665 0.5650 0.4346
-2.000 0.0692 0.00822 0.00214 -0.0671 0.5643 0.4386
-1.750 0.0984 0.00820 0.00212 -0.0678 0.5635 0.4413
-1.500 0.1277 0.00819 0.00210 -0.0684 0.5627 0.4444
-1.250 0.1569 0.00818 0.00209 -0.0691 0.5617 0.4468
-1.000 0.1862 0.00818 0.00207 -0.0697 0.5608 0.4481
-0.750 0.2154 0.00818 0.00206 -0.0703 0.5598 0.4489
-0.500 0.2446 0.00819 0.00205 -0.0710 0.5588 0.4497
-0.250 0.2737 0.00818 0.00205 -0.0716 0.5580 0.4511
0.000 0.3028 0.00818 0.00205 -0.0722 0.5571 0.4525
0.250 0.3319 0.00818 0.00206 -0.0729 0.5563 0.4540
0.500 0.3610 0.00819 0.00208 -0.0735 0.5555 0.4554
0.750 0.3900 0.00821 0.00210 -0.0741 0.5547 0.4569
1.000 0.4191 0.00823 0.00213 -0.0747 0.5539 0.4583
1.250 0.4481 0.00825 0.00216 -0.0753 0.5531 0.4598
1.500 0.4771 0.00829 0.00220 -0.0759 0.5523 0.4613
1.750 0.5060 0.00833 0.00224 -0.0765 0.5515 0.4627
2.000 0.5351 0.00838 0.00230 -0.0771 0.5506 0.4639
2.250 0.5642 0.00840 0.00236 -0.0778 0.5500 0.4657
2.500 0.5933 0.00841 0.00241 -0.0784 0.5495 0.4676
2.750 0.6223 0.00843 0.00248 -0.0791 0.5490 0.4695
3.000 0.6514 0.00845 0.00255 -0.0797 0.5483 0.4713
3.250 0.6803 0.00848 0.00262 -0.0803 0.5475 0.4731
3.500 0.7093 0.00852 0.00270 -0.0809 0.5468 0.4749
3.750 0.7382 0.00856 0.00278 -0.0815 0.5461 0.4765
4.000 0.7671 0.00860 0.00287 -0.0821 0.5455 0.4780
4.250 0.7960 0.00865 0.00296 -0.0827 0.5447 0.4795
4.500 0.8245 0.00866 0.00304 -0.0832 0.5431 0.4816
4.750 0.8516 0.00867 0.00307 -0.0834 0.5382 0.4836
5.000 0.8780 0.00863 0.00309 -0.0834 0.5294 0.4857
5.250 0.9036 0.00864 0.00310 -0.0833 0.5174 0.4878
5.500 0.9293 0.00868 0.00315 -0.0833 0.5030 0.4898
5.750 0.9546 0.00877 0.00323 -0.0831 0.4854 0.4916
6.000 0.9682 0.00929 0.00350 -0.0809 0.4260 0.4931
6.250 0.9699 0.01034 0.00418 -0.0766 0.3523 0.4946
6.500 0.9698 0.01123 0.00480 -0.0719 0.2931 0.4965
6.750 0.9659 0.01210 0.00544 -0.0666 0.2425 0.4983
7.000 0.9628 0.01308 0.00621 -0.0617 0.1943 0.5001
7.250 0.9647 0.01394 0.00693 -0.0579 0.1605 0.5021
7.500 0.9696 0.01474 0.00764 -0.0547 0.1352 0.5042
7.750 0.9747 0.01559 0.00841 -0.0518 0.1142 0.5060
8.000 0.9814 0.01644 0.00920 -0.0492 0.0972 0.5078
8.250 0.9880 0.01736 0.01009 -0.0469 0.0827 0.5102
8.500 0.9962 0.01829 0.01101 -0.0449 0.0721 0.5127
8.750 1.0045 0.01929 0.01201 -0.0431 0.0632 0.5156
9.000 1.0141 0.02029 0.01303 -0.0417 0.0561 0.5181
9.250 1.0225 0.02142 0.01416 -0.0402 0.0480 0.5207
9.500 1.0312 0.02260 0.01533 -0.0388 0.0422 0.5231
9.750 1.0402 0.02380 0.01654 -0.0376 0.0363 0.5256
10.000 1.0498 0.02500 0.01777 -0.0365 0.0322 0.5285
10.250 1.0582 0.02631 0.01908 -0.0354 0.0276 0.5314
10.500 1.0686 0.02751 0.02033 -0.0345 0.0249 0.5344
10.750 1.0794 0.02871 0.02156 -0.0337 0.0228 0.5372
11.000 1.0868 0.03017 0.02300 -0.0327 0.0184 0.5397
11.250 1.0980 0.03138 0.02427 -0.0321 0.0175 0.5431
11.500 1.1064 0.03281 0.02572 -0.0312 0.0149 0.5467
11.750 1.1178 0.03405 0.02702 -0.0306 0.0141 0.5504
12.250 1.1370 0.03685 0.02989 -0.0294 0.0111 0.5577
12.500 1.1478 0.03821 0.03130 -0.0289 0.0101 0.5629
12.750 1.1583 0.03961 0.03275 -0.0285 0.0092 0.5669
13.000 1.1676 0.04113 0.03431 -0.0280 0.0079 0.5709
13.250 1.1782 0.04257 0.03581 -0.0277 0.0072 0.5755
13.500 1.1883 0.04407 0.03736 -0.0273 0.0066 0.5809
13.750 1.1976 0.04568 0.03901 -0.0270 0.0059 0.5855
14.000 1.2082 0.04719 0.04059 -0.0267 0.0054 0.5906
14.250 1.2177 0.04882 0.04229 -0.0265 0.0049 0.5960
14.500 1.2266 0.05053 0.04404 -0.0263 0.0043 0.6005
14.750 1.2362 0.05220 0.04579 -0.0262 0.0039 0.6069
15.000 1.2453 0.05397 0.04762 -0.0261 0.0036 0.6122
15.250 1.2548 0.05570 0.04943 -0.0260 0.0034 0.6186
15.500 1.2630 0.05759 0.05139 -0.0260 0.0029 0.6254
15.750 1.2703 0.05961 0.05347 -0.0260 0.0025 0.6310
16.000 1.2792 0.06149 0.05543 -0.0261 0.0023 0.6374
16.250 1.2868 0.06353 0.05755 -0.0262 0.0022 0.6439
16.500 1.2934 0.06574 0.05985 -0.0263 0.0018 0.6505
16.750 1.3015 0.06778 0.06197 -0.0266 0.0018 0.6586
17.000 1.3064 0.07023 0.06452 -0.0268 0.0015 0.6665
17.250 1.3129 0.07253 0.06691 -0.0272 0.0014 0.6750
17.500 1.3188 0.07495 0.06942 -0.0275 0.0013 0.6831
17.750 1.3233 0.07758 0.07214 -0.0280 0.0011 0.6921
18.000 1.3287 0.08012 0.07479 -0.0285 0.0011 0.7014
18.250 1.3310 0.08313 0.07790 -0.0292 0.0010 0.7101
18.500 1.3346 0.08597 0.08085 -0.0299 0.0009 0.7202
18.750 1.3364 0.08915 0.08415 -0.0307 0.0008 0.7305
19.000 1.3383 0.09234 0.08746 -0.0316 0.0008 0.7415
19.250 1.3386 0.09583 0.09109 -0.0327 0.0007 0.7544
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