NREL's S811 Airfoil (s811-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S811 Airfoil (s811-nr) Reynolds number: 1,000,000 Max Cl/Cd: 99.52 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s811-nr-1000000.txt Download as CSV file: xf-s811-nr-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6203 0.09782 0.09506 -0.0237 1.0000 0.2557
-13.000 -0.6045 0.09718 0.09442 -0.0234 1.0000 0.2561
-12.750 -1.3260 0.02575 0.02231 -0.0291 0.9983 0.3064
-12.500 -1.3081 0.02328 0.01973 -0.0344 0.9945 0.3070
-12.250 -1.2964 0.02065 0.01700 -0.0383 0.9903 0.3089
-12.000 -1.2714 0.01945 0.01576 -0.0409 0.9863 0.3098
-11.750 -1.2370 0.01850 0.01477 -0.0446 0.9833 0.3105
-11.500 -1.1995 0.01776 0.01399 -0.0485 0.9812 0.3111
-11.250 -1.1598 0.01720 0.01339 -0.0522 0.9796 0.3117
-11.000 -1.1185 0.01671 0.01287 -0.0559 0.9783 0.3122
-10.750 -1.0965 0.01621 0.01234 -0.0561 0.9727 0.3127
-10.500 -1.0607 0.01576 0.01187 -0.0586 0.9692 0.3132
-10.250 -1.0200 0.01533 0.01141 -0.0620 0.9666 0.3138
-10.000 -0.9776 0.01491 0.01095 -0.0656 0.9638 0.3144
-9.750 -0.9571 0.01453 0.01055 -0.0650 0.9533 0.3149
-9.500 -0.9273 0.01416 0.01014 -0.0661 0.9418 0.3155
-9.250 -0.8890 0.01376 0.00967 -0.0687 0.9118 0.3161
-9.000 -0.8571 0.01368 0.00918 -0.0699 0.8065 0.3167
-8.750 -0.8382 0.01367 0.00889 -0.0688 0.7405 0.3172
-8.500 -0.8160 0.01361 0.00863 -0.0683 0.6950 0.3177
-8.250 -0.7921 0.01351 0.00837 -0.0682 0.6582 0.3182
-8.000 -0.7668 0.01340 0.00812 -0.0682 0.6287 0.3187
-7.750 -0.7409 0.01329 0.00788 -0.0684 0.6032 0.3192
-7.500 -0.7142 0.01319 0.00767 -0.0686 0.5810 0.3197
-7.250 -0.6870 0.01312 0.00749 -0.0689 0.5615 0.3201
-7.000 -0.6594 0.01303 0.00731 -0.0692 0.5446 0.3205
-6.750 -0.6316 0.01296 0.00714 -0.0696 0.5294 0.3208
-6.500 -0.6035 0.01289 0.00699 -0.0699 0.5156 0.3211
-6.250 -0.5757 0.01269 0.00672 -0.0704 0.5042 0.3216
-6.000 -0.5488 0.01238 0.00633 -0.0707 0.4924 0.3229
-5.750 -0.5204 0.01217 0.00609 -0.0711 0.4840 0.3239
-5.500 -0.4920 0.01205 0.00592 -0.0715 0.4750 0.3247
-5.250 -0.4629 0.01195 0.00579 -0.0720 0.4683 0.3254
-5.000 -0.4336 0.01186 0.00567 -0.0725 0.4621 0.3261
-4.750 -0.4046 0.01181 0.00558 -0.0729 0.4556 0.3268
-4.500 -0.3751 0.01175 0.00549 -0.0734 0.4505 0.3274
-4.250 -0.3454 0.01168 0.00541 -0.0739 0.4466 0.3280
-4.000 -0.3158 0.01163 0.00533 -0.0743 0.4423 0.3287
-3.750 -0.2863 0.01159 0.00525 -0.0748 0.4379 0.3294
-3.500 -0.2571 0.01158 0.00519 -0.0752 0.4329 0.3301
-3.250 -0.2270 0.01151 0.00512 -0.0757 0.4307 0.3308
-3.000 -0.1970 0.01145 0.00505 -0.0762 0.4283 0.3315
-2.750 -0.1670 0.01140 0.00498 -0.0767 0.4256 0.3321
-2.500 -0.1371 0.01136 0.00492 -0.0771 0.4228 0.3328
-2.250 -0.1073 0.01133 0.00486 -0.0776 0.4199 0.3334
-2.000 -0.0777 0.01133 0.00482 -0.0779 0.4166 0.3340
-1.750 -0.0482 0.01135 0.00480 -0.0783 0.4131 0.3346
-1.500 -0.0179 0.01131 0.00476 -0.0788 0.4118 0.3350
-1.250 0.0124 0.01128 0.00473 -0.0793 0.4103 0.3355
-1.000 0.0426 0.01128 0.00472 -0.0797 0.4087 0.3358
-0.750 0.0726 0.01116 0.00459 -0.0802 0.4069 0.3369
-0.500 0.1025 0.01101 0.00446 -0.0807 0.4052 0.3385
-0.250 0.1325 0.01096 0.00441 -0.0811 0.4034 0.3397
0.000 0.1624 0.01094 0.00440 -0.0815 0.4016 0.3406
0.250 0.1923 0.01095 0.00440 -0.0818 0.3997 0.3415
0.500 0.2220 0.01099 0.00444 -0.0822 0.3975 0.3423
0.750 0.2516 0.01106 0.00450 -0.0825 0.3952 0.3431
1.000 0.2815 0.01110 0.00455 -0.0828 0.3937 0.3440
1.250 0.3118 0.01110 0.00457 -0.0832 0.3930 0.3448
1.500 0.3420 0.01110 0.00459 -0.0836 0.3921 0.3457
1.750 0.3721 0.01111 0.00462 -0.0839 0.3910 0.3465
2.000 0.4023 0.01112 0.00465 -0.0843 0.3897 0.3474
2.250 0.4323 0.01114 0.00468 -0.0846 0.3884 0.3482
2.500 0.4623 0.01116 0.00471 -0.0849 0.3871 0.3489
2.750 0.4923 0.01120 0.00476 -0.0852 0.3858 0.3496
3.000 0.5222 0.01124 0.00481 -0.0855 0.3846 0.3502
3.250 0.5520 0.01129 0.00487 -0.0857 0.3834 0.3507
3.500 0.5817 0.01136 0.00494 -0.0859 0.3821 0.3512
3.750 0.6114 0.01135 0.00494 -0.0862 0.3807 0.3525
4.000 0.6411 0.01136 0.00497 -0.0865 0.3790 0.3544
4.250 0.6706 0.01149 0.00511 -0.0868 0.3768 0.3559
4.500 0.7003 0.01162 0.00527 -0.0870 0.3752 0.3570
4.750 0.7301 0.01163 0.00533 -0.0873 0.3745 0.3580
5.000 0.7597 0.01164 0.00539 -0.0874 0.3734 0.3591
5.250 0.7892 0.01164 0.00543 -0.0876 0.3716 0.3601
5.500 0.8186 0.01165 0.00548 -0.0877 0.3696 0.3611
5.750 0.8479 0.01167 0.00553 -0.0878 0.3675 0.3622
6.000 0.8769 0.01167 0.00554 -0.0878 0.3644 0.3632
6.250 0.9052 0.01175 0.00560 -0.0877 0.3603 0.3642
6.500 0.9336 0.01183 0.00570 -0.0877 0.3562 0.3651
6.750 0.9630 0.01176 0.00567 -0.0878 0.3527 0.3658
7.000 0.9920 0.01175 0.00570 -0.0878 0.3490 0.3665
7.250 1.0205 0.01181 0.00577 -0.0877 0.3458 0.3671
7.500 1.0481 0.01188 0.00583 -0.0875 0.3416 0.3681
7.750 1.0768 0.01187 0.00587 -0.0876 0.3379 0.3705
8.000 1.1062 0.01185 0.00591 -0.0877 0.3331 0.3723
8.250 1.1339 0.01191 0.00599 -0.0875 0.3268 0.3738
8.500 1.1609 0.01202 0.00611 -0.0872 0.3212 0.3752
8.750 1.1891 0.01209 0.00622 -0.0870 0.3145 0.3764
9.000 1.2148 0.01225 0.00637 -0.0866 0.3049 0.3777
9.250 1.2400 0.01246 0.00654 -0.0860 0.2903 0.3789
9.500 1.2607 0.01289 0.00685 -0.0848 0.2632 0.3801
9.750 1.2741 0.01370 0.00745 -0.0825 0.2285 0.3810
10.000 1.2861 0.01452 0.00810 -0.0801 0.1996 0.3819
10.250 1.2936 0.01528 0.00873 -0.0768 0.1756 0.3827
10.500 1.2996 0.01606 0.00939 -0.0734 0.1538 0.3833
10.750 1.3059 0.01690 0.01013 -0.0702 0.1362 0.3838
11.000 1.3129 0.01772 0.01088 -0.0672 0.1212 0.3844
11.250 1.3199 0.01853 0.01165 -0.0645 0.1082 0.3864
11.500 1.3255 0.01943 0.01252 -0.0617 0.0972 0.3883
11.750 1.3296 0.02044 0.01350 -0.0589 0.0877 0.3898
12.000 1.3329 0.02155 0.01461 -0.0562 0.0795 0.3912
12.250 1.3349 0.02282 0.01589 -0.0538 0.0721 0.3925
12.500 1.3354 0.02431 0.01739 -0.0515 0.0659 0.3937
12.750 1.3330 0.02616 0.01925 -0.0496 0.0602 0.3947
13.000 1.3293 0.02837 0.02148 -0.0481 0.0552 0.3957
13.250 1.3249 0.03092 0.02407 -0.0472 0.0502 0.3966
13.500 1.3191 0.03388 0.02707 -0.0467 0.0462 0.3975
13.750 1.3104 0.03736 0.03060 -0.0466 0.0423 0.3983
14.000 1.3019 0.04099 0.03428 -0.0468 0.0386 0.3990
14.250 1.2929 0.04477 0.03812 -0.0471 0.0357 0.3997
14.500 1.2831 0.04872 0.04211 -0.0476 0.0334 0.4003
14.750 1.2752 0.05251 0.04596 -0.0481 0.0315 0.4008
15.000 1.2663 0.05648 0.04998 -0.0488 0.0298 0.4013
15.250 1.2576 0.06053 0.05408 -0.0496 0.0283 0.4017
15.500 1.2538 0.06415 0.05777 -0.0504 0.0272 0.4031
15.750 1.2509 0.06773 0.06140 -0.0513 0.0262 0.4049
16.000 1.2464 0.07162 0.06535 -0.0524 0.0253 0.4065
16.250 1.2429 0.07544 0.06924 -0.0535 0.0245 0.4079
16.500 1.2437 0.07878 0.07265 -0.0545 0.0240 0.4094
16.750 1.2451 0.08207 0.07599 -0.0555 0.0234 0.4108
17.000 1.2445 0.08572 0.07970 -0.0567 0.0229 0.4122
17.250 1.2453 0.08918 0.08321 -0.0578 0.0224 0.4137
17.500 1.2442 0.09297 0.08706 -0.0592 0.0219 0.4150
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