NREL's S811 Airfoil (s811-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S811 Airfoil (s811-nr) Reynolds number: 500,000 Max Cl/Cd: 79.07 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s811-nr-500000.txt Download as CSV file: xf-s811-nr-500000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S811 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0240 0.09571 0.09114 -0.0600 0.6931 0.2725
-9.500 -0.0201 0.09399 0.08919 -0.0598 0.6500 0.2765
-9.250 -0.0204 0.09148 0.08654 -0.0600 0.6228 0.2817
-9.000 -0.0443 0.09043 0.08548 -0.0677 0.6983 0.2829
-8.750 -0.0257 0.09062 0.08537 -0.0664 0.6381 0.2841
-8.500 -0.0054 0.09059 0.08517 -0.0658 0.6016 0.2863
-8.250 -0.0855 0.08047 0.07502 -0.0682 0.6120 0.2937
-8.000 -0.0619 0.08021 0.07462 -0.0677 0.5831 0.2941
-7.750 -0.0322 0.08057 0.07487 -0.0672 0.5593 0.2945
-7.500 -0.0031 0.08073 0.07493 -0.0668 0.5411 0.2950
-7.250 0.0299 0.08136 0.07549 -0.0664 0.5260 0.2958
-7.000 0.0662 0.08250 0.07655 -0.0659 0.5119 0.2975
-6.750 0.0826 0.08140 0.07543 -0.0660 0.5044 0.2984
-6.500 0.1011 0.08073 0.07471 -0.0659 0.4968 0.3004
-6.250 0.0951 0.07837 0.07230 -0.0662 0.4920 0.3048
-6.000 -0.4857 0.02313 0.01688 -0.0678 0.5474 0.3346
-5.750 -0.4742 0.02197 0.01553 -0.0681 0.5354 0.3356
-5.500 -0.4586 0.02065 0.01406 -0.0684 0.5253 0.3370
-5.250 -0.4352 0.02015 0.01349 -0.0684 0.5151 0.3379
-5.000 -0.4095 0.01986 0.01317 -0.0686 0.5066 0.3385
-4.750 -0.3835 0.01964 0.01290 -0.0687 0.4984 0.3391
-4.500 -0.3573 0.01949 0.01268 -0.0689 0.4913 0.3397
-4.250 -0.3302 0.01926 0.01245 -0.0692 0.4857 0.3403
-4.000 -0.3033 0.01909 0.01224 -0.0694 0.4802 0.3409
-3.750 -0.2765 0.01893 0.01202 -0.0697 0.4749 0.3416
-3.500 -0.2493 0.01875 0.01179 -0.0700 0.4705 0.3423
-3.250 -0.2217 0.01850 0.01153 -0.0704 0.4667 0.3431
-3.000 -0.1940 0.01828 0.01127 -0.0708 0.4628 0.3439
-2.750 -0.1663 0.01807 0.01100 -0.0713 0.4591 0.3447
-2.500 -0.1386 0.01787 0.01074 -0.0717 0.4555 0.3456
-2.250 -0.1106 0.01771 0.01050 -0.0722 0.4519 0.3465
-2.000 -0.0820 0.01747 0.01025 -0.0727 0.4497 0.3474
-1.750 -0.0532 0.01726 0.01001 -0.0732 0.4471 0.3483
-1.500 -0.0243 0.01708 0.00979 -0.0737 0.4444 0.3492
-1.250 0.0047 0.01692 0.00958 -0.0742 0.4416 0.3499
-1.000 0.0338 0.01682 0.00943 -0.0747 0.4389 0.3506
-0.750 0.0631 0.01680 0.00935 -0.0751 0.4364 0.3511
-0.500 0.0917 0.01638 0.00887 -0.0758 0.4337 0.3527
-0.250 0.1208 0.01623 0.00873 -0.0763 0.4318 0.3538
0.000 0.1501 0.01613 0.00868 -0.0766 0.4303 0.3546
0.250 0.1796 0.01608 0.00866 -0.0770 0.4286 0.3554
0.500 0.2090 0.01605 0.00866 -0.0773 0.4268 0.3562
0.750 0.2386 0.01602 0.00866 -0.0777 0.4250 0.3570
1.000 0.2682 0.01601 0.00866 -0.0780 0.4232 0.3579
1.250 0.2978 0.01600 0.00866 -0.0784 0.4215 0.3588
1.500 0.3275 0.01599 0.00865 -0.0788 0.4199 0.3598
1.750 0.3573 0.01600 0.00864 -0.0792 0.4183 0.3608
2.000 0.3872 0.01603 0.00866 -0.0797 0.4164 0.3618
2.250 0.4176 0.01615 0.00874 -0.0802 0.4140 0.3629
2.500 0.4477 0.01620 0.00880 -0.0807 0.4126 0.3639
2.750 0.4775 0.01618 0.00881 -0.0811 0.4116 0.3649
3.000 0.5073 0.01619 0.00884 -0.0815 0.4104 0.3658
3.250 0.5371 0.01622 0.00889 -0.0818 0.4092 0.3666
3.500 0.5670 0.01629 0.00898 -0.0822 0.4078 0.3672
3.750 0.5968 0.01606 0.00877 -0.0827 0.4064 0.3690
4.000 0.6263 0.01602 0.00878 -0.0830 0.4048 0.3704
4.250 0.6556 0.01606 0.00887 -0.0832 0.4031 0.3715
4.500 0.6852 0.01614 0.00899 -0.0835 0.4017 0.3726
4.750 0.7147 0.01622 0.00911 -0.0837 0.4002 0.3737
5.000 0.7443 0.01631 0.00923 -0.0840 0.3986 0.3748
5.250 0.7741 0.01647 0.00939 -0.0843 0.3967 0.3759
5.500 0.8045 0.01684 0.00977 -0.0848 0.3941 0.3772
5.750 0.8328 0.01680 0.00981 -0.0848 0.3927 0.3784
6.000 0.8609 0.01678 0.00985 -0.0847 0.3908 0.3797
6.250 0.8892 0.01679 0.00991 -0.0847 0.3885 0.3809
6.500 0.9175 0.01678 0.00994 -0.0847 0.3858 0.3820
6.750 0.9457 0.01673 0.00990 -0.0846 0.3825 0.3830
7.000 0.9737 0.01671 0.00985 -0.0844 0.3785 0.3838
7.250 1.0014 0.01670 0.00984 -0.0844 0.3740 0.3852
7.500 1.0269 0.01641 0.00966 -0.0839 0.3698 0.3871
7.750 1.0530 0.01629 0.00960 -0.0834 0.3654 0.3887
8.000 1.0793 0.01624 0.00958 -0.0829 0.3613 0.3901
8.250 1.1062 0.01638 0.00972 -0.0827 0.3567 0.3915
8.500 1.1308 0.01627 0.00974 -0.0819 0.3525 0.3929
8.750 1.1558 0.01620 0.00974 -0.0812 0.3472 0.3943
9.000 1.1804 0.01620 0.00975 -0.0805 0.3420 0.3958
9.250 1.2053 0.01626 0.00986 -0.0798 0.3370 0.3973
9.500 1.2302 0.01625 0.00993 -0.0792 0.3304 0.3987
9.750 1.2525 0.01633 0.00999 -0.0781 0.3231 0.3999
10.000 1.2767 0.01639 0.01014 -0.0773 0.3141 0.4010
10.250 1.2971 0.01654 0.01027 -0.0759 0.3027 0.4019
10.500 1.3141 0.01662 0.01035 -0.0741 0.2857 0.4042
10.750 1.3219 0.01708 0.01071 -0.0710 0.2598 0.4058
11.000 1.3241 0.01799 0.01148 -0.0673 0.2318 0.4071
11.250 1.3239 0.01913 0.01250 -0.0635 0.2075 0.4083
11.500 1.3235 0.02032 0.01361 -0.0600 0.1859 0.4096
11.750 1.3212 0.02165 0.01487 -0.0565 0.1674 0.4109
12.000 1.3173 0.02315 0.01631 -0.0533 0.1515 0.4121
12.250 1.3121 0.02486 0.01799 -0.0505 0.1377 0.4132
12.500 1.3054 0.02688 0.02000 -0.0481 0.1258 0.4143
12.750 1.2976 0.02927 0.02240 -0.0463 0.1157 0.4154
13.000 1.2878 0.03218 0.02533 -0.0452 0.1071 0.4163
13.250 1.2757 0.03568 0.02885 -0.0448 0.0994 0.4171
13.500 1.2662 0.03924 0.03246 -0.0448 0.0925 0.4180
13.750 1.2523 0.04342 0.03668 -0.0451 0.0866 0.4187
14.000 1.2391 0.04766 0.04096 -0.0456 0.0805 0.4192
14.250 1.2263 0.05194 0.04529 -0.0463 0.0754 0.4198
14.500 1.2127 0.05638 0.04975 -0.0471 0.0704 0.4205
14.750 1.2026 0.06053 0.05395 -0.0480 0.0652 0.4219
15.000 1.1916 0.06492 0.05838 -0.0490 0.0602 0.4232
15.250 1.1815 0.06933 0.06282 -0.0502 0.0552 0.4243
15.500 1.1756 0.07336 0.06688 -0.0513 0.0504 0.4255
15.750 1.1689 0.07760 0.07116 -0.0526 0.0466 0.4266
16.000 1.1645 0.08159 0.07517 -0.0539 0.0434 0.4279
16.250 1.1612 0.08558 0.07920 -0.0552 0.0406 0.4291
16.500 1.1593 0.08939 0.08304 -0.0565 0.0384 0.4306
16.750 1.1566 0.09341 0.08710 -0.0579 0.0367 0.4320
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