NREL's S816 Airfoil (s816-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S816 Airfoil (s816-nr) Reynolds number: 500,000 Max Cl/Cd: 91.03 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s816-nr-500000-n5.txt Download as CSV file: xf-s816-nr-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.3958 0.11637 0.11402 -0.0712 0.9771 0.0040
-14.500 -0.4679 0.09525 0.09277 -0.0799 0.9780 0.0035
-14.250 -0.4969 0.08545 0.08283 -0.0858 0.9702 0.0035
-13.750 -0.5412 0.06693 0.06378 -0.0991 0.9183 0.0035
-13.500 -0.6159 0.04800 0.04361 -0.0939 0.9236 0.0035
-13.250 -0.5880 0.04491 0.03986 -0.0978 0.8364 0.0038
-13.000 -0.5767 0.04373 0.03829 -0.0963 0.7979 0.0039
-12.750 -0.5614 0.04287 0.03714 -0.0950 0.7739 0.0038
-12.500 -0.5463 0.04209 0.03616 -0.0940 0.7560 0.0039
-12.250 -0.5318 0.04129 0.03523 -0.0935 0.7407 0.0041
-12.000 -0.5147 0.04070 0.03448 -0.0927 0.7284 0.0042
-11.500 -0.4795 0.03969 0.03321 -0.0910 0.7078 0.0044
-11.250 -0.4622 0.03923 0.03262 -0.0902 0.6991 0.0047
-11.000 -0.4453 0.03874 0.03204 -0.0894 0.6913 0.0048
-10.750 -0.4293 0.03823 0.03143 -0.0886 0.6841 0.0048
-10.500 -0.4142 0.03767 0.03078 -0.0877 0.6770 0.0050
-10.000 -0.3843 0.03637 0.02933 -0.0864 0.6652 0.0054
-9.750 -0.3742 0.03552 0.02844 -0.0852 0.6598 0.0056
-9.500 -0.3601 0.03478 0.02766 -0.0847 0.6551 0.0059
-9.250 -0.3462 0.03399 0.02685 -0.0841 0.6509 0.0066
-9.000 -0.3351 0.03308 0.02589 -0.0834 0.6467 0.0067
-8.750 -0.3257 0.03209 0.02483 -0.0824 0.6427 0.0073
-8.500 -0.3174 0.03103 0.02372 -0.0814 0.6395 0.0076
-8.250 -0.3125 0.02975 0.02243 -0.0802 0.6361 0.0082
-8.000 -0.3073 0.02848 0.02112 -0.0790 0.6328 0.0086
-7.750 -0.3016 0.02722 0.01982 -0.0778 0.6298 0.0087
-7.500 -0.2974 0.02588 0.01843 -0.0765 0.6269 0.0100
-7.250 -0.2953 0.02438 0.01689 -0.0751 0.6244 0.0110
-7.000 -0.2930 0.02286 0.01532 -0.0736 0.6219 0.0113
-6.750 -0.2894 0.02144 0.01386 -0.0723 0.6194 0.0131
-6.500 -0.2867 0.01997 0.01233 -0.0708 0.6169 0.0144
-6.250 -0.2857 0.01848 0.01080 -0.0691 0.6146 0.0161
-6.000 -0.2842 0.01730 0.00954 -0.0670 0.6124 0.0182
-5.500 -0.2702 0.01558 0.00770 -0.0639 0.6085 0.0236
-5.250 -0.2537 0.01500 0.00711 -0.0631 0.6063 0.0288
-5.000 -0.2344 0.01452 0.00662 -0.0627 0.6043 0.0359
-4.750 -0.2135 0.01409 0.00618 -0.0624 0.6023 0.0475
-4.500 -0.1911 0.01371 0.00580 -0.0623 0.6006 0.0632
-4.250 -0.1681 0.01333 0.00543 -0.0623 0.5989 0.0824
-4.000 -0.1482 0.01257 0.00483 -0.0621 0.5975 0.1518
-3.750 -0.1367 0.01056 0.00351 -0.0617 0.5961 0.4051
-3.500 -0.1086 0.01049 0.00342 -0.0622 0.5947 0.4206
-3.250 -0.0800 0.01046 0.00339 -0.0628 0.5935 0.4353
-3.000 -0.0515 0.01044 0.00338 -0.0634 0.5921 0.4443
-2.750 -0.0224 0.01046 0.00333 -0.0640 0.5908 0.4492
-2.500 0.0062 0.01043 0.00330 -0.0645 0.5895 0.4528
-2.250 0.0350 0.01043 0.00328 -0.0651 0.5883 0.4564
-2.000 0.0638 0.01045 0.00326 -0.0657 0.5870 0.4596
-1.750 0.0928 0.01046 0.00322 -0.0663 0.5859 0.4622
-1.500 0.1216 0.01047 0.00318 -0.0668 0.5848 0.4634
-1.250 0.1505 0.01047 0.00314 -0.0674 0.5837 0.4643
-1.000 0.1792 0.01045 0.00311 -0.0680 0.5826 0.4655
-0.750 0.2080 0.01046 0.00309 -0.0686 0.5815 0.4667
-0.250 0.2658 0.01047 0.00310 -0.0698 0.5794 0.4694
0.000 0.2946 0.01048 0.00312 -0.0704 0.5785 0.4709
0.250 0.3236 0.01049 0.00315 -0.0710 0.5775 0.4724
0.500 0.3525 0.01051 0.00317 -0.0716 0.5766 0.4740
0.750 0.3814 0.01053 0.00321 -0.0722 0.5757 0.4756
1.000 0.4103 0.01056 0.00324 -0.0728 0.5748 0.4771
1.250 0.4393 0.01060 0.00329 -0.0734 0.5739 0.4784
1.500 0.4681 0.01062 0.00334 -0.0741 0.5730 0.4799
1.750 0.4969 0.01064 0.00340 -0.0747 0.5721 0.4815
2.000 0.5257 0.01067 0.00348 -0.0753 0.5713 0.4831
2.250 0.5546 0.01072 0.00356 -0.0759 0.5704 0.4849
2.500 0.5835 0.01076 0.00364 -0.0765 0.5696 0.4867
2.750 0.6123 0.01082 0.00373 -0.0771 0.5687 0.4886
3.000 0.6412 0.01088 0.00382 -0.0777 0.5678 0.4905
3.250 0.6702 0.01095 0.00392 -0.0783 0.5669 0.4923
3.500 0.6993 0.01104 0.00404 -0.0790 0.5661 0.4940
3.750 0.7285 0.01112 0.00418 -0.0797 0.5654 0.4959
4.000 0.7570 0.01119 0.00433 -0.0803 0.5647 0.4979
4.250 0.7854 0.01125 0.00449 -0.0808 0.5640 0.5000
4.500 0.8137 0.01133 0.00466 -0.0813 0.5632 0.5022
4.750 0.8419 0.01141 0.00482 -0.0818 0.5622 0.5045
5.000 0.8695 0.01147 0.00498 -0.0822 0.5604 0.5067
5.500 0.9211 0.01139 0.00498 -0.0820 0.5488 0.5109
5.750 0.9433 0.01126 0.00494 -0.0811 0.5385 0.5134
6.000 0.9656 0.01120 0.00496 -0.0803 0.5261 0.5161
6.250 0.9883 0.01119 0.00501 -0.0797 0.5132 0.5189
6.500 1.0115 0.01124 0.00511 -0.0791 0.5008 0.5217
6.750 1.0314 0.01133 0.00521 -0.0779 0.4779 0.5242
7.000 1.0330 0.01185 0.00548 -0.0733 0.4168 0.5265
7.250 1.0169 0.01294 0.00625 -0.0658 0.3551 0.5285
7.500 1.0054 0.01423 0.00729 -0.0596 0.3007 0.5306
7.750 0.9930 0.01567 0.00848 -0.0538 0.2485 0.5328
8.000 0.9866 0.01701 0.00967 -0.0493 0.2106 0.5351
8.250 0.9787 0.01859 0.01109 -0.0452 0.1739 0.5372
8.500 0.9750 0.02017 0.01256 -0.0420 0.1455 0.5395
8.750 0.9753 0.02169 0.01404 -0.0395 0.1238 0.5420
9.000 0.9770 0.02326 0.01557 -0.0375 0.1053 0.5448
9.250 0.9807 0.02480 0.01708 -0.0359 0.0909 0.5477
9.500 0.9846 0.02639 0.01864 -0.0343 0.0773 0.5507
10.000 0.9994 0.02922 0.02151 -0.0321 0.0602 0.5571
10.250 1.0062 0.03072 0.02302 -0.0311 0.0529 0.5606
10.500 1.0153 0.03208 0.02442 -0.0302 0.0471 0.5646
10.750 1.0225 0.03361 0.02595 -0.0293 0.0411 0.5684
11.000 1.0322 0.03498 0.02738 -0.0286 0.0372 0.5720
11.250 1.0399 0.03651 0.02894 -0.0279 0.0330 0.5759
11.500 1.0501 0.03788 0.03038 -0.0273 0.0303 0.5805
12.000 1.0682 0.04092 0.03351 -0.0262 0.0251 0.5890
12.250 1.0785 0.04236 0.03503 -0.0258 0.0232 0.5944
12.500 1.0881 0.04390 0.03661 -0.0253 0.0214 0.5989
12.750 1.0965 0.04556 0.03834 -0.0249 0.0195 0.6039
13.000 1.1072 0.04706 0.03993 -0.0247 0.0182 0.6092
13.250 1.1171 0.04866 0.04159 -0.0244 0.0168 0.6145
13.500 1.1253 0.05042 0.04341 -0.0241 0.0153 0.6198
13.750 1.1354 0.05204 0.04511 -0.0239 0.0141 0.6261
14.000 1.1452 0.05372 0.04686 -0.0239 0.0128 0.6323
14.250 1.1539 0.05552 0.04873 -0.0237 0.0116 0.6390
14.750 1.1726 0.05910 0.05247 -0.0237 0.0092 0.6520
15.000 1.1805 0.06107 0.05450 -0.0237 0.0083 0.6589
15.250 1.1888 0.06304 0.05658 -0.0238 0.0079 0.6661
15.500 1.1971 0.06504 0.05868 -0.0240 0.0070 0.6743
15.750 1.2045 0.06715 0.06085 -0.0241 0.0059 0.6826
16.250 1.2186 0.07160 0.06553 -0.0246 0.0052 0.7006
16.500 1.2251 0.07391 0.06795 -0.0250 0.0047 0.7101
16.750 1.2305 0.07643 0.07058 -0.0254 0.0044 0.7202
17.000 1.2348 0.07910 0.07335 -0.0258 0.0040 0.7303
17.250 1.2400 0.08172 0.07614 -0.0264 0.0038 0.7416
17.500 1.2439 0.08454 0.07910 -0.0270 0.0035 0.7539
17.750 1.2476 0.08740 0.08210 -0.0277 0.0032 0.7685
18.000 1.2497 0.09051 0.08537 -0.0284 0.0030 0.7846
18.250 1.2503 0.09386 0.08888 -0.0293 0.0027 0.8050
18.500 1.2506 0.09720 0.09241 -0.0301 0.0026 0.8313
18.750 1.2467 0.10019 0.09571 -0.0298 0.0025 0.9214
19.000 1.2453 0.10380 0.09946 -0.0311 0.0024 1.0000
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