NREL's S811 Airfoil (s811-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S811 Airfoil (s811-nr) Reynolds number: 500,000 Max Cl/Cd: 75.97 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s811-nr-500000-n5.txt Download as CSV file: xf-s811-nr-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.9216 0.02770 0.02288 -0.0499 0.9537 0.3071
-10.000 -0.8979 0.02660 0.02177 -0.0517 0.9354 0.3080
-9.750 -0.7515 0.02693 0.02154 -0.0717 0.7888 0.3081
-9.500 -0.7521 0.02599 0.02033 -0.0696 0.7224 0.3091
-9.250 -0.7562 0.02453 0.01868 -0.0681 0.6824 0.3101
-9.000 -0.7648 0.02270 0.01671 -0.0666 0.6536 0.3112
-8.750 -0.7803 0.02077 0.01464 -0.0645 0.6309 0.3123
-8.500 -0.7788 0.01933 0.01305 -0.0644 0.6087 0.3134
-8.250 -0.7641 0.01855 0.01212 -0.0648 0.5875 0.3143
-8.000 -0.7450 0.01807 0.01151 -0.0649 0.5687 0.3151
-7.750 -0.7241 0.01766 0.01099 -0.0649 0.5521 0.3158
-7.500 -0.7014 0.01730 0.01052 -0.0651 0.5382 0.3165
-7.250 -0.6777 0.01697 0.01009 -0.0654 0.5262 0.3172
-7.000 -0.6533 0.01667 0.00969 -0.0656 0.5148 0.3178
-6.750 -0.6280 0.01639 0.00932 -0.0660 0.5053 0.3185
-6.500 -0.6022 0.01613 0.00898 -0.0663 0.4959 0.3191
-6.250 -0.5759 0.01590 0.00866 -0.0667 0.4881 0.3196
-6.000 -0.5490 0.01567 0.00835 -0.0671 0.4804 0.3202
-5.750 -0.5221 0.01548 0.00807 -0.0675 0.4733 0.3207
-5.500 -0.4944 0.01529 0.00781 -0.0679 0.4676 0.3211
-5.250 -0.4668 0.01509 0.00757 -0.0683 0.4618 0.3217
-5.000 -0.4391 0.01492 0.00736 -0.0686 0.4560 0.3225
-4.750 -0.4112 0.01478 0.00719 -0.0690 0.4509 0.3232
-4.500 -0.3827 0.01464 0.00704 -0.0694 0.4464 0.3239
-4.250 -0.3541 0.01453 0.00691 -0.0698 0.4418 0.3245
-4.000 -0.3256 0.01443 0.00678 -0.0702 0.4376 0.3252
-3.750 -0.2970 0.01435 0.00666 -0.0706 0.4338 0.3258
-3.500 -0.2680 0.01426 0.00655 -0.0710 0.4308 0.3265
-3.250 -0.2388 0.01416 0.00644 -0.0715 0.4280 0.3272
-3.000 -0.2096 0.01408 0.00634 -0.0719 0.4250 0.3280
-2.750 -0.1803 0.01401 0.00625 -0.0724 0.4221 0.3288
-2.500 -0.1511 0.01395 0.00617 -0.0728 0.4193 0.3296
-2.250 -0.1220 0.01390 0.00608 -0.0732 0.4167 0.3305
-2.000 -0.0928 0.01386 0.00600 -0.0736 0.4141 0.3314
-1.750 -0.0633 0.01379 0.00592 -0.0740 0.4122 0.3322
-1.500 -0.0336 0.01372 0.00583 -0.0745 0.4104 0.3329
-1.250 -0.0040 0.01365 0.00575 -0.0749 0.4085 0.3336
-1.000 0.0257 0.01359 0.00568 -0.0754 0.4064 0.3343
-0.750 0.0553 0.01355 0.00562 -0.0758 0.4043 0.3350
-0.500 0.0849 0.01351 0.00556 -0.0762 0.4020 0.3355
-0.250 0.1145 0.01349 0.00550 -0.0765 0.4000 0.3360
0.000 0.1438 0.01343 0.00545 -0.0769 0.3982 0.3370
0.250 0.1731 0.01340 0.00543 -0.0772 0.3964 0.3379
0.500 0.2024 0.01341 0.00544 -0.0776 0.3946 0.3387
0.750 0.2322 0.01340 0.00545 -0.0779 0.3933 0.3396
1.000 0.2620 0.01338 0.00547 -0.0783 0.3922 0.3404
1.250 0.2918 0.01338 0.00550 -0.0786 0.3909 0.3413
1.500 0.3216 0.01338 0.00553 -0.0790 0.3896 0.3421
1.750 0.3514 0.01339 0.00556 -0.0793 0.3882 0.3430
2.000 0.3811 0.01341 0.00560 -0.0796 0.3869 0.3440
2.250 0.4108 0.01343 0.00565 -0.0799 0.3855 0.3450
2.500 0.4404 0.01347 0.00569 -0.0802 0.3842 0.3461
2.750 0.4699 0.01351 0.00575 -0.0805 0.3827 0.3472
3.000 0.4993 0.01355 0.00579 -0.0807 0.3812 0.3481
3.250 0.5287 0.01360 0.00584 -0.0810 0.3796 0.3491
3.500 0.5580 0.01366 0.00591 -0.0812 0.3782 0.3498
3.750 0.5873 0.01375 0.00599 -0.0814 0.3768 0.3505
4.000 0.6167 0.01386 0.00610 -0.0816 0.3754 0.3512
4.250 0.6463 0.01388 0.00617 -0.0819 0.3746 0.3522
4.500 0.6758 0.01390 0.00626 -0.0821 0.3737 0.3533
4.750 0.7051 0.01394 0.00637 -0.0823 0.3725 0.3544
5.000 0.7344 0.01399 0.00648 -0.0825 0.3711 0.3554
5.250 0.7636 0.01405 0.00661 -0.0826 0.3697 0.3564
5.500 0.7926 0.01412 0.00673 -0.0827 0.3682 0.3575
5.750 0.8214 0.01418 0.00684 -0.0828 0.3662 0.3586
6.000 0.8498 0.01424 0.00694 -0.0828 0.3637 0.3597
6.250 0.8779 0.01432 0.00703 -0.0827 0.3610 0.3609
6.500 0.9057 0.01445 0.00716 -0.0826 0.3581 0.3621
6.750 0.9337 0.01450 0.00728 -0.0825 0.3552 0.3634
7.000 0.9615 0.01450 0.00735 -0.0823 0.3507 0.3646
7.250 0.9884 0.01452 0.00738 -0.0820 0.3449 0.3657
7.500 1.0142 0.01461 0.00745 -0.0816 0.3389 0.3665
7.750 1.0419 0.01463 0.00755 -0.0814 0.3328 0.3673
8.000 1.0681 0.01468 0.00763 -0.0810 0.3259 0.3686
8.250 1.0942 0.01477 0.00777 -0.0806 0.3193 0.3699
8.500 1.1195 0.01487 0.00790 -0.0801 0.3086 0.3712
8.750 1.1433 0.01505 0.00807 -0.0793 0.2940 0.3724
9.000 1.1622 0.01541 0.00834 -0.0778 0.2692 0.3736
9.250 1.1747 0.01608 0.00885 -0.0755 0.2388 0.3747
9.500 1.1818 0.01685 0.00948 -0.0723 0.2120 0.3757
9.750 1.1885 0.01765 0.01018 -0.0692 0.1895 0.3768
10.000 1.1948 0.01855 0.01100 -0.0662 0.1684 0.3779
10.250 1.2003 0.01951 0.01188 -0.0632 0.1503 0.3790
10.500 1.2059 0.02048 0.01279 -0.0604 0.1355 0.3801
10.750 1.2105 0.02151 0.01378 -0.0577 0.1223 0.3812
11.000 1.2145 0.02261 0.01486 -0.0551 0.1111 0.3822
11.250 1.2173 0.02385 0.01609 -0.0527 0.1015 0.3830
11.500 1.2186 0.02527 0.01752 -0.0505 0.0935 0.3837
11.750 1.2180 0.02697 0.01923 -0.0486 0.0865 0.3845
12.000 1.2166 0.02895 0.02125 -0.0472 0.0801 0.3857
12.250 1.2142 0.03126 0.02362 -0.0463 0.0744 0.3867
12.500 1.2090 0.03408 0.02649 -0.0458 0.0695 0.3877
12.750 1.2054 0.03701 0.02949 -0.0457 0.0648 0.3886
13.000 1.1989 0.04039 0.03293 -0.0458 0.0608 0.3895
13.250 1.1925 0.04389 0.03649 -0.0462 0.0569 0.3904
13.500 1.1858 0.04747 0.04014 -0.0466 0.0538 0.3913
13.750 1.1790 0.05112 0.04385 -0.0471 0.0505 0.3922
14.000 1.1711 0.05495 0.04773 -0.0478 0.0473 0.3930
14.250 1.1658 0.05854 0.05138 -0.0484 0.0445 0.3940
14.500 1.1608 0.06219 0.05507 -0.0492 0.0418 0.3949
14.750 1.1572 0.06579 0.05872 -0.0501 0.0391 0.3959
15.000 1.1539 0.06943 0.06240 -0.0510 0.0367 0.3969
15.250 1.1532 0.07283 0.06585 -0.0519 0.0343 0.3979
15.500 1.1515 0.07645 0.06950 -0.0530 0.0324 0.3989
15.750 1.1526 0.07973 0.07283 -0.0539 0.0306 0.3999
16.000 1.1530 0.08318 0.07631 -0.0550 0.0291 0.4009
16.250 1.1540 0.08660 0.07978 -0.0561 0.0277 0.4018
16.500 1.1570 0.08979 0.08303 -0.0572 0.0266 0.4034
16.750 1.1581 0.09331 0.08661 -0.0585 0.0256 0.4050
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