NREL's S808 Airfoil (s808-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NREL's S808 Airfoil (s808-nr) Reynolds number: 200,000 Max Cl/Cd: 55.11 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s808-nr-200000.txt Download as CSV file: xf-s808-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S808 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4702 0.10363 0.09868 -0.0353 1.0000 0.2270
-11.750 -0.4384 0.10512 0.10018 -0.0333 1.0000 0.2286
-11.500 -0.5083 0.09438 0.08940 -0.0378 1.0000 0.2406
-11.250 -0.4766 0.09571 0.09074 -0.0356 1.0000 0.2415
-11.000 -0.4427 0.09738 0.09242 -0.0332 1.0000 0.2426
-10.750 -0.4094 0.09887 0.09393 -0.0311 1.0000 0.2445
-10.500 -0.3907 0.09859 0.09367 -0.0298 1.0000 0.2473
-10.250 -0.4008 0.09531 0.09038 -0.0300 1.0000 0.2518
-10.000 -0.4437 0.08804 0.08310 -0.0318 1.0000 0.2579
-9.750 -0.9796 0.03523 0.02984 -0.0397 1.0000 0.2900
-9.500 -0.9600 0.03535 0.03003 -0.0380 1.0000 0.2913
-9.250 -0.9411 0.03536 0.03007 -0.0367 0.9997 0.2926
-9.000 -0.8955 0.03572 0.03045 -0.0394 0.9952 0.2944
-8.750 -0.8507 0.03576 0.03048 -0.0425 0.9906 0.2966
-8.500 -0.8186 0.03333 0.02784 -0.0477 0.9826 0.3004
-8.250 -0.7895 0.02973 0.02370 -0.0546 0.9741 0.3057
-8.000 -0.7506 0.02893 0.02292 -0.0572 0.9682 0.3078
-7.750 -0.7051 0.02865 0.02266 -0.0605 0.9646 0.3096
-7.500 -0.6717 0.02817 0.02218 -0.0618 0.9557 0.3114
-7.250 -0.6285 0.02758 0.02155 -0.0652 0.9510 0.3138
-7.000 -0.5946 0.02678 0.02067 -0.0671 0.9424 0.3164
-6.750 -0.5546 0.02571 0.01944 -0.0706 0.9363 0.3200
-6.500 -0.5193 0.02452 0.01797 -0.0735 0.9280 0.3235
-6.250 -0.4815 0.02366 0.01716 -0.0755 0.9211 0.3256
-6.000 -0.4363 0.02316 0.01670 -0.0785 0.9175 0.3277
-5.750 -0.4054 0.02267 0.01622 -0.0790 0.9062 0.3299
-5.500 -0.3614 0.02203 0.01555 -0.0820 0.9017 0.3327
-5.250 -0.3274 0.02135 0.01480 -0.0833 0.8915 0.3358
-5.000 -0.2833 0.02055 0.01385 -0.0867 0.8850 0.3397
-4.750 -0.2452 0.01976 0.01297 -0.0888 0.8744 0.3428
-4.500 -0.2005 0.01922 0.01248 -0.0916 0.8656 0.3454
-4.250 -0.1615 0.01885 0.01211 -0.0934 0.8514 0.3479
-4.000 -0.1211 0.01847 0.01167 -0.0957 0.8366 0.3510
-3.750 -0.0831 0.01808 0.01114 -0.0976 0.8198 0.3545
-3.500 -0.0488 0.01773 0.01059 -0.0989 0.8016 0.3582
-3.250 -0.0174 0.01740 0.01010 -0.0996 0.7834 0.3614
-3.000 0.0121 0.01728 0.00996 -0.0996 0.7656 0.3642
-2.750 0.0397 0.01724 0.00989 -0.0993 0.7475 0.3670
-2.500 0.0672 0.01716 0.00973 -0.0991 0.7303 0.3703
-2.250 0.0950 0.01704 0.00948 -0.0990 0.7140 0.3739
-2.000 0.1234 0.01692 0.00918 -0.0992 0.6988 0.3775
-1.750 0.1514 0.01672 0.00887 -0.0991 0.6843 0.3806
-1.500 0.1776 0.01665 0.00883 -0.0986 0.6690 0.3835
-1.250 0.2048 0.01666 0.00883 -0.0983 0.6551 0.3868
-1.000 0.2330 0.01669 0.00874 -0.0982 0.6422 0.3908
-0.750 0.2602 0.01664 0.00860 -0.0981 0.6281 0.3952
-0.500 0.2882 0.01656 0.00841 -0.0981 0.6155 0.3989
-0.250 0.3154 0.01650 0.00834 -0.0978 0.6035 0.4021
0.000 0.3420 0.01650 0.00838 -0.0974 0.5907 0.4055
0.250 0.3701 0.01656 0.00835 -0.0973 0.5796 0.4095
0.500 0.3975 0.01655 0.00829 -0.0971 0.5673 0.4142
0.750 0.4256 0.01655 0.00819 -0.0971 0.5562 0.4186
1.000 0.4522 0.01655 0.00823 -0.0967 0.5452 0.4224
1.250 0.4793 0.01663 0.00832 -0.0964 0.5343 0.4266
1.500 0.5070 0.01669 0.00831 -0.0962 0.5238 0.4313
1.750 0.5349 0.01675 0.00830 -0.0962 0.5131 0.4362
2.000 0.5621 0.01676 0.00829 -0.0960 0.5033 0.4405
2.250 0.5884 0.01684 0.00844 -0.0955 0.4929 0.4450
2.500 0.6159 0.01696 0.00851 -0.0953 0.4834 0.4505
2.750 0.6434 0.01707 0.00858 -0.0952 0.4734 0.4562
3.000 0.6703 0.01711 0.00861 -0.0949 0.4642 0.4608
3.250 0.6965 0.01723 0.00880 -0.0944 0.4548 0.4657
3.500 0.7234 0.01736 0.00890 -0.0941 0.4457 0.4718
3.750 0.7508 0.01753 0.00902 -0.0940 0.4367 0.4782
4.000 0.7764 0.01761 0.00917 -0.0934 0.4277 0.4835
4.250 0.8032 0.01782 0.00938 -0.0931 0.4195 0.4897
4.500 0.8295 0.01796 0.00951 -0.0927 0.4104 0.4966
4.750 0.8565 0.01816 0.00968 -0.0925 0.4026 0.5024
5.000 0.8809 0.01830 0.00994 -0.0917 0.3940 0.5091
5.250 0.9079 0.01854 0.01009 -0.0915 0.3861 0.5173
5.500 0.9325 0.01871 0.01037 -0.0908 0.3780 0.5237
5.750 0.9574 0.01890 0.01060 -0.0902 0.3701 0.5311
6.000 0.9842 0.01921 0.01084 -0.0900 0.3627 0.5394
6.250 1.0073 0.01936 0.01113 -0.0890 0.3547 0.5463
6.500 1.0333 0.01968 0.01138 -0.0886 0.3476 0.5553
6.750 1.0565 0.01990 0.01172 -0.0878 0.3400 0.5636
7.000 1.0798 0.02014 0.01201 -0.0869 0.3328 0.5723
7.250 1.1053 0.02052 0.01234 -0.0865 0.3259 0.5818
7.500 1.1265 0.02073 0.01271 -0.0853 0.3186 0.5901
7.750 1.1508 0.02108 0.01298 -0.0847 0.3119 0.6008
8.000 1.1723 0.02141 0.01345 -0.0835 0.3051 0.6098
8.250 1.1937 0.02171 0.01380 -0.0824 0.2982 0.6212
8.500 1.2177 0.02215 0.01419 -0.0818 0.2918 0.6312
8.750 1.2359 0.02245 0.01466 -0.0802 0.2853 0.6425
9.000 1.2548 0.02277 0.01506 -0.0786 0.2790 0.6533
9.250 1.2775 0.02327 0.01551 -0.0779 0.2729 0.6656
9.500 1.2924 0.02362 0.01603 -0.0758 0.2668 0.6785
9.750 1.3078 0.02395 0.01644 -0.0737 0.2611 0.6907
10.000 1.3281 0.02450 0.01696 -0.0726 0.2554 0.7049
10.250 1.3399 0.02493 0.01757 -0.0701 0.2498 0.7201
10.500 1.3534 0.02536 0.01810 -0.0679 0.2444 0.7355
10.750 1.3727 0.02598 0.01867 -0.0667 0.2389 0.7529
11.000 1.3811 0.02649 0.01942 -0.0639 0.2338 0.7716
11.250 1.3921 0.02701 0.02006 -0.0616 0.2287 0.7939
11.500 1.4067 0.02759 0.02062 -0.0597 0.2238 0.8205
11.750 1.4107 0.02815 0.02141 -0.0562 0.2194 0.8595
12.000 1.4096 0.02849 0.02195 -0.0520 0.2152 1.0000
12.250 1.4245 0.02936 0.02277 -0.0511 0.2102 1.0000
12.500 1.4415 0.03036 0.02369 -0.0505 0.2053 1.0000
12.750 1.4484 0.03148 0.02494 -0.0488 0.2007 1.0000
13.000 1.4579 0.03257 0.02604 -0.0474 0.1961 1.0000
13.250 1.4758 0.03358 0.02689 -0.0468 0.1913 1.0000
13.500 1.4776 0.03509 0.02858 -0.0451 0.1874 1.0000
13.750 1.4830 0.03654 0.03012 -0.0438 0.1831 1.0000
14.000 1.4913 0.03791 0.03147 -0.0428 0.1790 1.0000
14.250 1.5026 0.03935 0.03287 -0.0420 0.1749 1.0000
14.500 1.5021 0.04138 0.03506 -0.0410 0.1711 1.0000
14.750 1.5059 0.04323 0.03697 -0.0402 0.1672 1.0000
15.000 1.5146 0.04483 0.03852 -0.0397 0.1635 1.0000
15.250 1.5197 0.04686 0.04060 -0.0391 0.1599 1.0000
15.500 1.5167 0.04951 0.04341 -0.0388 0.1564 1.0000
15.750 1.5187 0.05183 0.04579 -0.0386 0.1530 1.0000
16.000 1.5269 0.05365 0.04755 -0.0384 0.1495 1.0000
16.250 1.5288 0.05624 0.05021 -0.0384 0.1463 1.0000
16.500 1.5224 0.05967 0.05381 -0.0388 0.1432 1.0000
16.750 1.5217 0.06262 0.05684 -0.0392 0.1400 1.0000
17.000 1.5272 0.06491 0.05910 -0.0394 0.1370 1.0000
17.250 1.5325 0.06738 0.06158 -0.0397 0.1339 1.0000
17.500 1.5201 0.07199 0.06641 -0.0410 0.1313 1.0000
17.750 1.5150 0.07584 0.07037 -0.0422 0.1284 1.0000
18.000 1.5177 0.07872 0.07326 -0.0430 0.1257 1.0000
18.250 1.5341 0.07982 0.07422 -0.0428 0.1226 1.0000
18.500 1.5133 0.08606 0.08074 -0.0454 0.1205 1.0000
18.750 1.4996 0.09152 0.08639 -0.0478 0.1180 1.0000
19.000 1.4963 0.09554 0.09047 -0.0495 0.1155 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NREL's S808 Airfoil (s808-nr)