NREL's S811 Airfoil (s811-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S811 Airfoil (s811-nr) Reynolds number: 1,000,000 Max Cl/Cd: 90.94 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s811-nr-1000000-n5.txt Download as CSV file: xf-s811-nr-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.9857 0.09011 0.08730 -0.0269 1.0000 0.2528
-15.750 -1.0522 0.07279 0.06982 -0.0294 1.0000 0.2668
-15.500 -1.0304 0.07274 0.06977 -0.0293 1.0000 0.2675
-15.250 -1.0065 0.07291 0.06994 -0.0291 1.0000 0.2679
-15.000 -0.9910 0.07221 0.06923 -0.0290 1.0000 0.2685
-14.750 -1.1848 0.05112 0.04790 -0.0308 1.0000 0.2806
-14.500 -1.1733 0.05024 0.04702 -0.0304 1.0000 0.2816
-14.250 -1.1535 0.04930 0.04609 -0.0315 0.9996 0.2829
-14.000 -1.1406 0.04724 0.04400 -0.0335 0.9988 0.2842
-13.750 -1.1552 0.04255 0.03924 -0.0362 0.9974 0.2865
-13.500 -1.1907 0.03601 0.03257 -0.0394 0.9944 0.2894
-13.250 -1.2162 0.03091 0.02735 -0.0419 0.9903 0.2915
-13.000 -1.2276 0.02723 0.02355 -0.0439 0.9861 0.2925
-12.750 -1.2192 0.02481 0.02105 -0.0464 0.9823 0.2931
-12.500 -1.1949 0.02362 0.01982 -0.0490 0.9795 0.2940
-12.250 -1.1804 0.02219 0.01836 -0.0503 0.9742 0.2951
-12.000 -1.1662 0.02061 0.01675 -0.0519 0.9676 0.2961
-11.500 -1.1257 0.01771 0.01376 -0.0568 0.9522 0.2978
-11.250 -1.0996 0.01648 0.01247 -0.0597 0.9361 0.2985
-11.000 -1.0575 0.01592 0.01141 -0.0642 0.7956 0.2992
-10.750 -1.0546 0.01485 0.01007 -0.0635 0.7353 0.2999
-10.500 -1.0386 0.01434 0.00937 -0.0633 0.6939 0.3005
-10.250 -1.0184 0.01404 0.00892 -0.0632 0.6596 0.3010
-10.000 -0.9960 0.01380 0.00854 -0.0632 0.6318 0.3016
-9.750 -0.9723 0.01358 0.00820 -0.0633 0.6065 0.3021
-9.500 -0.9476 0.01339 0.00789 -0.0635 0.5837 0.3026
-9.250 -0.9223 0.01321 0.00761 -0.0638 0.5620 0.3031
-9.000 -0.8961 0.01305 0.00735 -0.0641 0.5451 0.3037
-8.750 -0.8694 0.01290 0.00711 -0.0645 0.5302 0.3043
-8.500 -0.8422 0.01274 0.00688 -0.0649 0.5171 0.3048
-8.250 -0.8147 0.01260 0.00666 -0.0654 0.5061 0.3053
-8.000 -0.7869 0.01248 0.00646 -0.0658 0.4950 0.3057
-7.750 -0.7588 0.01234 0.00626 -0.0663 0.4862 0.3061
-7.500 -0.7305 0.01223 0.00608 -0.0667 0.4771 0.3064
-7.250 -0.7020 0.01212 0.00590 -0.0672 0.4696 0.3067
-7.000 -0.6732 0.01200 0.00573 -0.0677 0.4627 0.3070
-6.750 -0.6448 0.01186 0.00555 -0.0682 0.4557 0.3078
-6.500 -0.6160 0.01172 0.00537 -0.0688 0.4501 0.3086
-6.250 -0.5869 0.01159 0.00521 -0.0693 0.4448 0.3094
-6.000 -0.5578 0.01148 0.00507 -0.0698 0.4389 0.3101
-5.500 -0.4991 0.01130 0.00482 -0.0709 0.4293 0.3115
-5.250 -0.4694 0.01121 0.00470 -0.0715 0.4255 0.3122
-5.000 -0.4397 0.01114 0.00460 -0.0720 0.4217 0.3129
-4.750 -0.4100 0.01107 0.00450 -0.0725 0.4179 0.3135
-4.250 -0.3504 0.01095 0.00433 -0.0736 0.4117 0.3149
-4.000 -0.3203 0.01088 0.00425 -0.0741 0.4094 0.3155
-3.750 -0.2903 0.01082 0.00417 -0.0747 0.4069 0.3162
-3.500 -0.2602 0.01077 0.00410 -0.0752 0.4044 0.3169
-3.250 -0.2302 0.01073 0.00403 -0.0757 0.4018 0.3175
-3.000 -0.2002 0.01069 0.00397 -0.0762 0.3992 0.3181
-2.750 -0.1702 0.01066 0.00392 -0.0766 0.3965 0.3187
-2.500 -0.1402 0.01064 0.00387 -0.0771 0.3940 0.3193
-2.250 -0.1099 0.01060 0.00382 -0.0776 0.3928 0.3198
-2.000 -0.0796 0.01056 0.00378 -0.0781 0.3914 0.3203
-1.750 -0.0493 0.01054 0.00374 -0.0786 0.3897 0.3208
-1.500 -0.0191 0.01052 0.00371 -0.0790 0.3879 0.3212
-1.250 0.0111 0.01047 0.00365 -0.0795 0.3859 0.3222
-1.000 0.0414 0.01042 0.00361 -0.0800 0.3841 0.3233
-0.750 0.0715 0.01040 0.00358 -0.0805 0.3824 0.3243
-0.500 0.1017 0.01038 0.00356 -0.0809 0.3806 0.3252
-0.250 0.1318 0.01037 0.00356 -0.0813 0.3788 0.3260
0.000 0.1618 0.01038 0.00356 -0.0817 0.3770 0.3268
0.250 0.1918 0.01039 0.00357 -0.0821 0.3753 0.3277
0.500 0.2221 0.01038 0.00358 -0.0825 0.3746 0.3285
0.750 0.2524 0.01037 0.00359 -0.0829 0.3738 0.3294
1.000 0.2827 0.01037 0.00360 -0.0833 0.3729 0.3302
1.250 0.3130 0.01037 0.00362 -0.0837 0.3719 0.3310
1.500 0.3432 0.01038 0.00364 -0.0840 0.3708 0.3318
1.750 0.3733 0.01039 0.00366 -0.0844 0.3697 0.3326
2.000 0.4034 0.01041 0.00369 -0.0847 0.3685 0.3333
2.250 0.4334 0.01043 0.00372 -0.0850 0.3673 0.3340
2.500 0.4633 0.01046 0.00375 -0.0853 0.3660 0.3346
2.750 0.4932 0.01049 0.00379 -0.0856 0.3645 0.3351
3.000 0.5229 0.01053 0.00384 -0.0858 0.3631 0.3357
3.250 0.5526 0.01057 0.00389 -0.0860 0.3619 0.3364
3.500 0.5823 0.01060 0.00394 -0.0863 0.3605 0.3379
3.750 0.6118 0.01065 0.00401 -0.0865 0.3591 0.3392
4.000 0.6411 0.01072 0.00410 -0.0867 0.3576 0.3403
4.250 0.6709 0.01076 0.00417 -0.0869 0.3568 0.3413
4.500 0.7007 0.01079 0.00424 -0.0871 0.3561 0.3423
4.750 0.7305 0.01082 0.00432 -0.0874 0.3551 0.3433
5.000 0.7602 0.01086 0.00440 -0.0876 0.3539 0.3444
5.250 0.7900 0.01088 0.00446 -0.0877 0.3518 0.3453
5.500 0.8195 0.01092 0.00452 -0.0879 0.3490 0.3463
5.750 0.8486 0.01097 0.00459 -0.0880 0.3460 0.3473
6.000 0.8770 0.01106 0.00466 -0.0879 0.3414 0.3482
6.250 0.9061 0.01111 0.00474 -0.0880 0.3375 0.3490
6.500 0.9355 0.01114 0.00480 -0.0881 0.3319 0.3498
6.750 0.9632 0.01126 0.00487 -0.0880 0.3234 0.3504
7.000 0.9919 0.01133 0.00496 -0.0879 0.3172 0.3510
7.250 1.0199 0.01144 0.00507 -0.0878 0.3098 0.3519
7.500 1.0475 0.01156 0.00519 -0.0877 0.3009 0.3537
7.750 1.0731 0.01180 0.00537 -0.0872 0.2825 0.3553
8.000 1.0918 0.01247 0.00582 -0.0858 0.2429 0.3565
8.250 1.1074 0.01330 0.00644 -0.0840 0.2045 0.3576
8.500 1.1240 0.01401 0.00700 -0.0822 0.1766 0.3586
8.750 1.1417 0.01460 0.00749 -0.0806 0.1557 0.3597
9.000 1.1581 0.01520 0.00800 -0.0789 0.1374 0.3607
9.250 1.1721 0.01576 0.00849 -0.0766 0.1222 0.3617
9.500 1.1836 0.01628 0.00896 -0.0740 0.1093 0.3627
9.750 1.1954 0.01686 0.00950 -0.0715 0.0981 0.3636
10.000 1.2070 0.01749 0.01008 -0.0690 0.0881 0.3644
10.250 1.2178 0.01815 0.01072 -0.0666 0.0789 0.3652
10.500 1.2272 0.01889 0.01143 -0.0641 0.0701 0.3659
10.750 1.2372 0.01963 0.01215 -0.0617 0.0633 0.3665
11.000 1.2457 0.02045 0.01296 -0.0594 0.0574 0.3670
11.250 1.2529 0.02137 0.01388 -0.0571 0.0521 0.3677
11.500 1.2590 0.02240 0.01493 -0.0549 0.0477 0.3693
11.750 1.2644 0.02356 0.01612 -0.0529 0.0437 0.3708
12.000 1.2684 0.02492 0.01751 -0.0511 0.0402 0.3721
12.250 1.2696 0.02662 0.01925 -0.0495 0.0368 0.3733
12.500 1.2709 0.02851 0.02119 -0.0484 0.0338 0.3744
12.750 1.2707 0.03075 0.02348 -0.0476 0.0313 0.3754
13.000 1.2699 0.03326 0.02604 -0.0471 0.0292 0.3763
13.250 1.2678 0.03608 0.02892 -0.0470 0.0272 0.3772
13.500 1.2657 0.03904 0.03195 -0.0471 0.0259 0.3782
13.750 1.2615 0.04230 0.03527 -0.0473 0.0246 0.3790
14.000 1.2583 0.04552 0.03856 -0.0476 0.0235 0.3798
14.250 1.2543 0.04886 0.04196 -0.0480 0.0227 0.3805
14.500 1.2497 0.05231 0.04547 -0.0485 0.0219 0.3812
14.750 1.2452 0.05581 0.04903 -0.0491 0.0213 0.3819
15.000 1.2419 0.05924 0.05252 -0.0497 0.0207 0.3825
15.250 1.2402 0.06255 0.05589 -0.0504 0.0201 0.3831
15.500 1.2382 0.06601 0.05940 -0.0512 0.0195 0.3836
15.750 1.2364 0.06950 0.06294 -0.0520 0.0190 0.3841
16.000 1.2362 0.07285 0.06634 -0.0529 0.0184 0.3852
16.250 1.2355 0.07637 0.06993 -0.0540 0.0180 0.3865
16.500 1.2381 0.07949 0.07310 -0.0549 0.0178 0.3880
16.750 1.2405 0.08266 0.07634 -0.0559 0.0174 0.3895
17.000 1.2421 0.08602 0.07976 -0.0570 0.0172 0.3909
17.250 1.2453 0.08916 0.08295 -0.0580 0.0168 0.3925
17.500 1.2472 0.09253 0.08638 -0.0592 0.0166 0.3940
17.750 1.2492 0.09592 0.08983 -0.0604 0.0163 0.3954
18.000 1.2525 0.09911 0.09306 -0.0615 0.0160 0.3967
18.250 1.2539 0.10266 0.09667 -0.0629 0.0158 0.3979
18.500 1.2555 0.10618 0.10025 -0.0643 0.0155 0.3989
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