NREL's S811 Airfoil (s811-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S811 Airfoil (s811-nr) Reynolds number: 100,000 Max Cl/Cd: 28.39 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s811-nr-100000-n5.txt Download as CSV file: xf-s811-nr-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1936 0.11612 0.10832 -0.0183 1.0000 0.3027
-9.000 -0.1940 0.11415 0.10637 -0.0182 1.0000 0.3052
-8.750 -0.1869 0.11088 0.10309 -0.0209 0.9918 0.3075
-8.500 -0.1509 0.10840 0.10062 -0.0246 0.9704 0.3083
-8.250 -0.1179 0.10588 0.09809 -0.0284 0.8987 0.3093
-8.000 -0.0108 0.09976 0.09128 -0.0498 0.7714 0.3115
-7.750 0.0144 0.09820 0.08930 -0.0521 0.7070 0.3136
-7.500 0.0286 0.09678 0.08763 -0.0526 0.6712 0.3155
-7.250 0.0402 0.09516 0.08584 -0.0531 0.6463 0.3166
-7.000 0.0505 0.09344 0.08397 -0.0538 0.6272 0.3179
-6.500 0.0576 0.08960 0.07991 -0.0551 0.6007 0.3218
-6.250 0.0836 0.08859 0.07882 -0.0556 0.5866 0.3228
-6.000 0.1059 0.08754 0.07770 -0.0559 0.5751 0.3239
-5.750 0.1249 0.08640 0.07652 -0.0563 0.5658 0.3250
-5.500 0.1407 0.08512 0.07518 -0.0565 0.5577 0.3260
-5.250 0.1547 0.08376 0.07376 -0.0568 0.5513 0.3268
-5.000 0.1682 0.08241 0.07239 -0.0569 0.5448 0.3276
-4.750 0.1810 0.08107 0.07101 -0.0570 0.5389 0.3286
-4.500 0.1928 0.07972 0.06959 -0.0571 0.5341 0.3295
-4.250 0.2033 0.07840 0.06825 -0.0572 0.5294 0.3313
-4.000 0.2071 0.07686 0.06670 -0.0572 0.5250 0.3336
-3.750 0.2006 0.07478 0.06458 -0.0572 0.5214 0.3353
-3.500 0.2053 0.07310 0.06288 -0.0571 0.5175 0.3364
-3.250 0.2262 0.07219 0.06192 -0.0570 0.5133 0.3370
-3.000 0.2456 0.07123 0.06097 -0.0569 0.5089 0.3376
-2.750 0.2638 0.07027 0.06005 -0.0567 0.5047 0.3382
-2.500 0.2808 0.06930 0.05910 -0.0566 0.5010 0.3389
-2.250 0.2985 0.06845 0.05826 -0.0564 0.4977 0.3400
-2.000 0.3155 0.06764 0.05743 -0.0561 0.4949 0.3414
-1.750 0.3300 0.06672 0.05649 -0.0559 0.4923 0.3429
-1.500 0.3415 0.06562 0.05544 -0.0556 0.4897 0.3442
-1.250 0.3506 0.06436 0.05422 -0.0553 0.4871 0.3452
-1.000 0.3583 0.06303 0.05293 -0.0549 0.4846 0.3462
-0.750 0.3623 0.06152 0.05144 -0.0545 0.4823 0.3477
-0.500 0.3282 0.05780 0.04769 -0.0537 0.4811 0.3514
-0.250 0.3512 0.05744 0.04738 -0.0532 0.4783 0.3521
0.000 0.3726 0.05701 0.04697 -0.0527 0.4758 0.3528
0.250 0.3930 0.05656 0.04653 -0.0522 0.4735 0.3537
0.500 0.4109 0.05604 0.04604 -0.0516 0.4711 0.3547
0.750 0.4239 0.05528 0.04539 -0.0507 0.4688 0.3556
1.000 0.4342 0.05442 0.04462 -0.0498 0.4666 0.3566
1.250 0.4423 0.05356 0.04384 -0.0487 0.4646 0.3578
1.500 0.4455 0.05263 0.04298 -0.0472 0.4627 0.3592
1.750 0.4430 0.05151 0.04190 -0.0454 0.4610 0.3609
2.000 0.4316 0.04931 0.03971 -0.0449 0.4595 0.3639
2.250 0.4171 0.04583 0.03619 -0.0467 0.4583 0.3688
2.500 0.4372 0.04560 0.03602 -0.0461 0.4564 0.3696
2.750 0.4563 0.04516 0.03561 -0.0458 0.4547 0.3706
3.000 0.4754 0.04456 0.03503 -0.0459 0.4529 0.3718
3.250 0.4909 0.04379 0.03432 -0.0461 0.4509 0.3733
3.500 0.5037 0.04256 0.03319 -0.0469 0.4486 0.3756
3.750 0.5170 0.03683 0.02714 -0.0566 0.4467 0.3851
4.000 0.5387 0.03698 0.02744 -0.0560 0.4446 0.3860
4.250 0.5610 0.03708 0.02766 -0.0556 0.4426 0.3870
4.500 0.5841 0.03706 0.02774 -0.0554 0.4404 0.3882
4.750 0.6082 0.03696 0.02770 -0.0556 0.4383 0.3894
5.000 0.6342 0.03675 0.02754 -0.0561 0.4362 0.3909
5.250 0.6620 0.03648 0.02727 -0.0571 0.4344 0.3927
5.500 0.6920 0.03612 0.02687 -0.0588 0.4329 0.3950
5.750 0.7144 0.03586 0.02670 -0.0598 0.4302 0.3977
6.000 0.7403 0.03539 0.02619 -0.0620 0.4271 0.4017
6.250 0.7597 0.03577 0.02676 -0.0612 0.4241 0.4028
6.500 0.7809 0.03610 0.02725 -0.0604 0.4213 0.4039
6.750 0.8047 0.03634 0.02760 -0.0600 0.4187 0.4052
7.000 0.8314 0.03647 0.02780 -0.0601 0.4163 0.4067
7.250 0.8619 0.03648 0.02784 -0.0607 0.4141 0.4083
7.500 0.8785 0.03696 0.02849 -0.0598 0.4107 0.4098
7.750 0.8884 0.03765 0.02939 -0.0582 0.4062 0.4114
8.000 0.9079 0.03794 0.02978 -0.0577 0.4022 0.4132
8.250 0.9367 0.03782 0.02967 -0.0583 0.3988 0.4155
8.500 0.9743 0.03736 0.02912 -0.0599 0.3957 0.4183
8.750 0.9897 0.03780 0.02966 -0.0590 0.3911 0.4204
9.000 0.9892 0.03873 0.03084 -0.0558 0.3852 0.4214
9.250 1.0136 0.03853 0.03075 -0.0551 0.3804 0.4230
9.500 1.0573 0.03751 0.02970 -0.0563 0.3762 0.4252
9.750 1.0421 0.03891 0.03138 -0.0518 0.3699 0.4262
10.000 1.0410 0.03947 0.03208 -0.0485 0.3641 0.4276
10.250 1.0850 0.03822 0.03080 -0.0497 0.3588 0.4303
10.500 1.0696 0.03960 0.03236 -0.0454 0.3529 0.4314
10.750 1.0516 0.04158 0.03450 -0.0420 0.3462 0.4325
11.000 1.1000 0.03974 0.03258 -0.0431 0.3403 0.4355
11.250 0.9402 0.05382 0.04707 -0.0387 0.3278 0.4322
11.500 1.0126 0.04884 0.04205 -0.0381 0.3247 0.4360
11.750 0.8734 0.06665 0.06002 -0.0420 0.3015 0.4329
12.250 0.8641 0.07338 0.06685 -0.0441 0.2791 0.4354
12.500 0.8994 0.07172 0.06519 -0.0437 0.2745 0.4381
12.750 0.8889 0.07598 0.06949 -0.0451 0.2614 0.4391
13.000 0.8977 0.07761 0.07122 -0.0453 0.2516 0.4405
13.250 0.9273 0.07638 0.07005 -0.0446 0.2430 0.4428
13.500 0.9345 0.07826 0.07196 -0.0450 0.2298 0.4445
13.750 0.9481 0.07927 0.07293 -0.0450 0.2159 0.4467
14.000 0.9594 0.08062 0.07418 -0.0453 0.2009 0.4489
14.250 0.9653 0.08282 0.07627 -0.0459 0.1861 0.4510
14.500 0.9683 0.08556 0.07892 -0.0468 0.1724 0.4529
14.750 0.9700 0.08859 0.08186 -0.0479 0.1598 0.4547
15.000 0.9708 0.09184 0.08501 -0.0491 0.1481 0.4564
15.250 0.9711 0.09531 0.08842 -0.0505 0.1373 0.4579
15.500 0.9712 0.09881 0.09194 -0.0519 0.1274 0.4592
15.750 0.9718 0.10227 0.09540 -0.0532 0.1186 0.4606
16.000 0.9727 0.10571 0.09880 -0.0547 0.1104 0.4621
16.250 0.9738 0.10931 0.10245 -0.0562 0.1025 0.4637
16.500 0.9756 0.11278 0.10592 -0.0578 0.0957 0.4655
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