NREL's S811 Airfoil (s811-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S811 Airfoil (s811-nr) Reynolds number: 200,000 Max Cl/Cd: 52.28 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s811-nr-200000-n5.txt Download as CSV file: xf-s811-nr-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3818 0.10944 0.10350 -0.0229 1.0000 0.2665
-11.000 -0.3645 0.10880 0.10289 -0.0225 1.0000 0.2670
-10.750 -0.3478 0.10811 0.10222 -0.0220 1.0000 0.2675
-10.500 -0.3308 0.10749 0.10163 -0.0216 1.0000 0.2682
-10.250 -0.3151 0.10675 0.10092 -0.0211 1.0000 0.2689
-10.000 -0.2830 0.10462 0.09878 -0.0249 0.9934 0.2699
-9.000 -0.1128 0.08748 0.08046 -0.0632 0.7175 0.2806
-8.750 -0.0950 0.08690 0.07958 -0.0629 0.6630 0.2811
-8.500 -0.0783 0.08624 0.07873 -0.0624 0.6287 0.2817
-8.250 -0.0623 0.08539 0.07774 -0.0622 0.6036 0.2824
-8.000 -0.0462 0.08452 0.07676 -0.0620 0.5843 0.2832
-7.750 -0.0316 0.08346 0.07560 -0.0619 0.5691 0.2842
-7.500 -0.0181 0.08227 0.07432 -0.0619 0.5561 0.2855
-7.000 -0.0391 0.07532 0.06722 -0.0629 0.5422 0.2936
-6.750 -0.0202 0.07466 0.06649 -0.0627 0.5324 0.2941
-6.500 -0.0016 0.07388 0.06568 -0.0626 0.5236 0.2945
-6.250 0.0165 0.07315 0.06490 -0.0624 0.5155 0.2951
-6.000 0.0346 0.07240 0.06411 -0.0623 0.5087 0.2957
-5.750 0.0511 0.07145 0.06314 -0.0622 0.5025 0.2964
-4.750 0.0478 0.06157 0.05309 -0.0625 0.4866 0.3072
-4.500 0.0665 0.06091 0.05242 -0.0623 0.4816 0.3076
-4.250 0.0849 0.06030 0.05179 -0.0620 0.4770 0.3081
-4.000 0.1028 0.05966 0.05112 -0.0616 0.4731 0.3086
-3.750 0.1218 0.05907 0.05053 -0.0613 0.4696 0.3092
-3.500 0.1407 0.05850 0.04998 -0.0611 0.4661 0.3099
-2.500 -0.0544 0.03455 0.02589 -0.0570 0.4629 0.3361
-2.250 -0.0358 0.03412 0.02548 -0.0566 0.4598 0.3367
-2.000 -0.0171 0.03368 0.02503 -0.0563 0.4569 0.3372
-1.750 0.0006 0.03310 0.02443 -0.0562 0.4543 0.3379
-1.500 0.0168 0.03219 0.02349 -0.0566 0.4519 0.3390
-1.250 0.0117 0.02765 0.01876 -0.0613 0.4502 0.3440
-1.000 0.0234 0.02432 0.01508 -0.0655 0.4480 0.3492
-0.750 0.0480 0.02308 0.01363 -0.0673 0.4455 0.3511
-0.500 0.0752 0.02278 0.01333 -0.0678 0.4429 0.3519
-0.250 0.1028 0.02266 0.01324 -0.0679 0.4405 0.3526
0.000 0.1304 0.02257 0.01317 -0.0681 0.4381 0.3532
0.250 0.1582 0.02252 0.01312 -0.0683 0.4358 0.3539
0.500 0.1863 0.02249 0.01307 -0.0686 0.4335 0.3546
0.750 0.2145 0.02243 0.01303 -0.0689 0.4315 0.3554
1.000 0.2427 0.02234 0.01299 -0.0692 0.4296 0.3563
1.250 0.2710 0.02223 0.01292 -0.0696 0.4277 0.3572
1.500 0.2995 0.02212 0.01283 -0.0701 0.4257 0.3583
1.750 0.3282 0.02200 0.01272 -0.0706 0.4238 0.3594
2.000 0.3570 0.02188 0.01260 -0.0711 0.4220 0.3608
2.250 0.3861 0.02175 0.01247 -0.0717 0.4203 0.3623
2.500 0.4155 0.02162 0.01231 -0.0724 0.4186 0.3639
2.750 0.4452 0.02149 0.01212 -0.0731 0.4171 0.3655
3.000 0.4753 0.02139 0.01195 -0.0739 0.4155 0.3668
3.250 0.5050 0.02137 0.01189 -0.0745 0.4137 0.3678
3.500 0.5333 0.02138 0.01199 -0.0747 0.4120 0.3687
3.750 0.5614 0.02142 0.01214 -0.0748 0.4105 0.3695
4.000 0.5896 0.02150 0.01232 -0.0749 0.4089 0.3705
4.250 0.6178 0.02159 0.01250 -0.0751 0.4073 0.3714
4.500 0.6461 0.02168 0.01268 -0.0752 0.4057 0.3724
4.750 0.6744 0.02177 0.01285 -0.0754 0.4039 0.3736
5.000 0.7028 0.02185 0.01298 -0.0755 0.4019 0.3748
5.250 0.7314 0.02193 0.01311 -0.0758 0.4002 0.3760
5.500 0.7602 0.02203 0.01324 -0.0760 0.3987 0.3774
5.750 0.7892 0.02213 0.01336 -0.0763 0.3970 0.3791
6.000 0.8188 0.02226 0.01348 -0.0767 0.3952 0.3808
6.250 0.8476 0.02243 0.01367 -0.0770 0.3934 0.3824
6.500 0.8740 0.02254 0.01387 -0.0769 0.3911 0.3838
6.750 0.9000 0.02262 0.01408 -0.0767 0.3883 0.3850
7.000 0.9260 0.02270 0.01429 -0.0764 0.3853 0.3861
7.250 0.9526 0.02277 0.01446 -0.0762 0.3823 0.3873
7.500 0.9797 0.02282 0.01456 -0.0760 0.3793 0.3885
7.750 1.0082 0.02287 0.01460 -0.0760 0.3759 0.3898
8.000 1.0301 0.02295 0.01486 -0.0750 0.3714 0.3911
8.250 1.0530 0.02296 0.01499 -0.0741 0.3661 0.3925
8.500 1.0775 0.02289 0.01496 -0.0735 0.3611 0.3940
8.750 1.1031 0.02287 0.01493 -0.0730 0.3565 0.3957
9.000 1.1228 0.02297 0.01521 -0.0717 0.3504 0.3974
9.250 1.1441 0.02295 0.01525 -0.0706 0.3439 0.3992
9.500 1.1649 0.02296 0.01527 -0.0694 0.3370 0.4008
9.750 1.1826 0.02301 0.01545 -0.0678 0.3272 0.4023
10.000 1.1986 0.02306 0.01560 -0.0659 0.3165 0.4037
10.250 1.2102 0.02315 0.01575 -0.0633 0.3042 0.4050
10.500 1.2207 0.02340 0.01605 -0.0607 0.2892 0.4062
10.750 1.2295 0.02385 0.01650 -0.0581 0.2703 0.4075
11.000 1.2314 0.02464 0.01720 -0.0548 0.2486 0.4088
11.250 1.2271 0.02586 0.01831 -0.0513 0.2281 0.4099
11.500 1.2189 0.02748 0.01987 -0.0480 0.2097 0.4109
11.750 1.2099 0.02942 0.02178 -0.0453 0.1944 0.4120
12.000 1.1994 0.03177 0.02414 -0.0433 0.1804 0.4131
12.250 1.1873 0.03463 0.02701 -0.0420 0.1679 0.4141
12.500 1.1744 0.03796 0.03036 -0.0414 0.1571 0.4150
12.750 1.1600 0.04179 0.03423 -0.0414 0.1478 0.4159
13.000 1.1465 0.04580 0.03828 -0.0418 0.1385 0.4168
13.250 1.1332 0.04996 0.04247 -0.0424 0.1303 0.4178
13.500 1.1194 0.05429 0.04682 -0.0432 0.1228 0.4186
13.750 1.1097 0.05829 0.05084 -0.0440 0.1150 0.4196
14.000 1.0993 0.06244 0.05502 -0.0450 0.1081 0.4206
14.250 1.0918 0.06639 0.05902 -0.0460 0.1010 0.4217
14.500 1.0862 0.07024 0.06291 -0.0471 0.0946 0.4228
14.750 1.0803 0.07423 0.06692 -0.0483 0.0884 0.4240
15.000 1.0783 0.07781 0.07055 -0.0494 0.0821 0.4253
15.250 1.0753 0.08162 0.07438 -0.0506 0.0767 0.4266
15.500 1.0740 0.08526 0.07805 -0.0519 0.0712 0.4280
15.750 1.0734 0.08888 0.08170 -0.0531 0.0663 0.4294
16.250 1.0736 0.09606 0.08894 -0.0558 0.0575 0.4324
16.500 1.0731 0.09984 0.09275 -0.0573 0.0541 0.4338
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