NREL's S808 Airfoil (s808-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S808 Airfoil (s808-nr) Reynolds number: 1,000,000 Max Cl/Cd: 92.84 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s808-nr-1000000-n5.txt Download as CSV file: xf-s808-nr-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.9522 0.09042 0.08643 -0.0491 1.0000 0.0557
-17.250 -0.9570 0.08713 0.08312 -0.0499 1.0000 0.0585
-17.000 -0.9695 0.08288 0.07884 -0.0510 1.0000 0.0613
-16.750 -0.9768 0.07939 0.07533 -0.0518 1.0000 0.0644
-16.500 -0.9897 0.07526 0.07117 -0.0528 1.0000 0.0672
-16.250 -1.0010 0.07143 0.06732 -0.0536 1.0000 0.0706
-16.000 -1.0143 0.06743 0.06328 -0.0543 1.0000 0.0737
-15.750 -1.0321 0.06305 0.05887 -0.0552 1.0000 0.0769
-15.500 -1.0472 0.05912 0.05491 -0.0557 1.0000 0.0809
-15.250 -1.0661 0.05490 0.05065 -0.0562 1.0000 0.0837
-15.000 -1.0879 0.05056 0.04626 -0.0566 1.0000 0.0875
-14.750 -1.1047 0.04643 0.04208 -0.0575 0.9998 0.0909
-14.500 -1.1259 0.04113 0.03673 -0.0603 0.9988 0.0966
-14.250 -1.1383 0.03676 0.03231 -0.0629 0.9975 0.1013
-14.000 -1.1493 0.03243 0.02793 -0.0658 0.9955 0.1069
-13.750 -1.1566 0.02779 0.02326 -0.0701 0.9930 0.1155
-13.500 -1.1606 0.02344 0.01889 -0.0745 0.9885 0.1267
-13.250 -1.1539 0.01971 0.01516 -0.0795 0.9828 0.1403
-13.000 -1.1342 0.01670 0.01218 -0.0856 0.9794 0.1567
-12.750 -1.1191 0.01523 0.01070 -0.0870 0.9751 0.1669
-12.500 -1.0977 0.01441 0.00990 -0.0876 0.9718 0.1746
-12.250 -1.0685 0.01388 0.00936 -0.0889 0.9698 0.1812
-12.000 -1.0379 0.01326 0.00876 -0.0906 0.9683 0.1893
-11.750 -1.0041 0.01288 0.00837 -0.0924 0.9672 0.1956
-11.500 -0.9702 0.01242 0.00793 -0.0943 0.9662 0.2008
-11.250 -0.9363 0.01207 0.00757 -0.0960 0.9651 0.2053
-11.000 -0.9091 0.01182 0.00730 -0.0961 0.9625 0.2090
-10.750 -0.8880 0.01154 0.00701 -0.0952 0.9576 0.2131
-10.500 -0.8590 0.01120 0.00670 -0.0958 0.9544 0.2201
-10.250 -0.8266 0.01099 0.00647 -0.0968 0.9517 0.2238
-10.000 -0.7932 0.01078 0.00622 -0.0980 0.9494 0.2254
-9.750 -0.7730 0.01054 0.00597 -0.0967 0.9421 0.2276
-9.500 -0.7439 0.01028 0.00570 -0.0971 0.9359 0.2295
-9.250 -0.7149 0.01005 0.00546 -0.0974 0.9290 0.2315
-9.000 -0.6835 0.00983 0.00522 -0.0981 0.9182 0.2335
-8.750 -0.6486 0.00961 0.00495 -0.0995 0.9015 0.2353
-8.500 -0.6137 0.00946 0.00466 -0.1008 0.8707 0.2368
-8.250 -0.5853 0.00943 0.00446 -0.1008 0.8347 0.2382
-8.000 -0.5590 0.00943 0.00431 -0.1004 0.8051 0.2393
-7.750 -0.5323 0.00942 0.00418 -0.1001 0.7791 0.2403
-7.500 -0.5057 0.00936 0.00403 -0.0999 0.7562 0.2423
-7.250 -0.4788 0.00930 0.00388 -0.0997 0.7350 0.2447
-7.000 -0.4514 0.00925 0.00376 -0.0996 0.7159 0.2470
-6.750 -0.4238 0.00921 0.00364 -0.0996 0.6980 0.2489
-6.500 -0.3959 0.00918 0.00354 -0.0995 0.6810 0.2508
-6.250 -0.3678 0.00915 0.00344 -0.0995 0.6649 0.2525
-6.000 -0.3393 0.00912 0.00334 -0.0995 0.6498 0.2541
-5.750 -0.3108 0.00911 0.00325 -0.0996 0.6353 0.2554
-5.500 -0.2824 0.00909 0.00316 -0.0996 0.6212 0.2569
-5.250 -0.2536 0.00903 0.00306 -0.0997 0.6073 0.2594
-5.000 -0.2248 0.00899 0.00298 -0.0998 0.5948 0.2617
-4.750 -0.1961 0.00897 0.00291 -0.0999 0.5817 0.2642
-4.500 -0.1669 0.00894 0.00285 -0.1001 0.5698 0.2667
-4.250 -0.1380 0.00894 0.00279 -0.1002 0.5581 0.2689
-4.000 -0.1089 0.00894 0.00274 -0.1003 0.5460 0.2707
-3.750 -0.0798 0.00895 0.00269 -0.1004 0.5352 0.2720
-3.500 -0.0507 0.00893 0.00263 -0.1005 0.5237 0.2745
-3.250 -0.0214 0.00891 0.00258 -0.1007 0.5135 0.2772
-2.750 0.0371 0.00890 0.00251 -0.1010 0.4931 0.2821
-2.500 0.0661 0.00893 0.00249 -0.1010 0.4825 0.2843
-2.250 0.0955 0.00894 0.00247 -0.1012 0.4728 0.2865
-2.000 0.1245 0.00898 0.00246 -0.1012 0.4628 0.2883
-1.750 0.1540 0.00898 0.00244 -0.1014 0.4545 0.2910
-1.500 0.1830 0.00900 0.00243 -0.1015 0.4444 0.2941
-1.250 0.2124 0.00901 0.00243 -0.1017 0.4359 0.2968
-1.000 0.2416 0.00905 0.00243 -0.1017 0.4270 0.2993
-0.750 0.2707 0.00909 0.00244 -0.1018 0.4187 0.3017
-0.500 0.2998 0.00913 0.00246 -0.1019 0.4096 0.3039
-0.250 0.3288 0.00919 0.00248 -0.1019 0.4015 0.3055
0.000 0.3580 0.00922 0.00249 -0.1020 0.3932 0.3083
0.500 0.4161 0.00931 0.00255 -0.1022 0.3775 0.3150
0.750 0.4449 0.00937 0.00259 -0.1022 0.3690 0.3182
1.000 0.4737 0.00944 0.00264 -0.1022 0.3614 0.3208
1.250 0.5026 0.00951 0.00268 -0.1022 0.3540 0.3229
1.500 0.5311 0.00960 0.00274 -0.1022 0.3461 0.3256
1.750 0.5601 0.00964 0.00279 -0.1022 0.3391 0.3291
2.000 0.5885 0.00973 0.00286 -0.1022 0.3314 0.3324
2.250 0.6171 0.00981 0.00293 -0.1022 0.3249 0.3360
2.500 0.6456 0.00990 0.00301 -0.1021 0.3172 0.3393
2.750 0.6735 0.01002 0.00310 -0.1020 0.3097 0.3420
3.000 0.7022 0.01008 0.00317 -0.1020 0.3043 0.3462
3.250 0.7303 0.01019 0.00327 -0.1019 0.2968 0.3500
3.500 0.7581 0.01031 0.00337 -0.1017 0.2900 0.3537
3.750 0.7863 0.01040 0.00347 -0.1016 0.2843 0.3575
4.000 0.8137 0.01054 0.00358 -0.1014 0.2769 0.3608
4.250 0.8416 0.01065 0.00370 -0.1012 0.2710 0.3660
4.500 0.8693 0.01076 0.00382 -0.1010 0.2650 0.3706
4.750 0.8962 0.01093 0.00397 -0.1007 0.2579 0.3747
5.000 0.9236 0.01106 0.00409 -0.1005 0.2527 0.3782
5.250 0.9508 0.01119 0.00423 -0.1002 0.2468 0.3836
5.500 0.9772 0.01137 0.00440 -0.0998 0.2400 0.3893
5.750 1.0042 0.01150 0.00455 -0.0995 0.2350 0.3943
6.250 1.0563 0.01187 0.00490 -0.0986 0.2225 0.4036
6.500 1.0827 0.01202 0.00507 -0.0982 0.2177 0.4092
6.750 1.1082 0.01222 0.00526 -0.0977 0.2116 0.4148
7.000 1.1332 0.01243 0.00547 -0.0971 0.2059 0.4204
7.250 1.1588 0.01260 0.00567 -0.0966 0.2011 0.4271
7.500 1.1831 0.01283 0.00589 -0.0958 0.1950 0.4328
8.000 1.2315 0.01327 0.00635 -0.0943 0.1849 0.4439
8.250 1.2539 0.01353 0.00660 -0.0933 0.1792 0.4502
8.500 1.2754 0.01376 0.00685 -0.0920 0.1746 0.4562
8.750 1.2970 0.01397 0.00709 -0.0908 0.1702 0.4636
9.000 1.3174 0.01426 0.00738 -0.0894 0.1654 0.4711
9.250 1.3375 0.01457 0.00769 -0.0880 0.1607 0.4769
9.500 1.3587 0.01483 0.00799 -0.0868 0.1567 0.4839
9.750 1.3783 0.01516 0.00833 -0.0854 0.1522 0.4912
10.000 1.3971 0.01554 0.00870 -0.0838 0.1477 0.4975
10.250 1.4174 0.01584 0.00905 -0.0826 0.1441 0.5060
10.500 1.4359 0.01622 0.00945 -0.0811 0.1398 0.5147
10.750 1.4529 0.01668 0.00991 -0.0794 0.1352 0.5225
11.000 1.4719 0.01704 0.01032 -0.0780 0.1319 0.5312
11.250 1.4890 0.01749 0.01078 -0.0764 0.1281 0.5386
11.500 1.5045 0.01802 0.01134 -0.0746 0.1238 0.5477
11.750 1.5212 0.01850 0.01185 -0.0731 0.1208 0.5577
12.000 1.5370 0.01903 0.01242 -0.0714 0.1172 0.5675
12.250 1.5509 0.01966 0.01308 -0.0696 0.1136 0.5769
12.500 1.5649 0.02031 0.01377 -0.0679 0.1104 0.5866
12.750 1.5789 0.02097 0.01447 -0.0663 0.1073 0.5980
13.000 1.5912 0.02175 0.01529 -0.0645 0.1040 0.6087
13.250 1.6014 0.02267 0.01624 -0.0627 0.1007 0.6196
13.500 1.6140 0.02349 0.01713 -0.0612 0.0983 0.6319
13.750 1.6242 0.02449 0.01818 -0.0595 0.0952 0.6448
14.000 1.6320 0.02569 0.01943 -0.0579 0.0921 0.6586
14.250 1.6413 0.02685 0.02066 -0.0565 0.0898 0.6733
14.500 1.6505 0.02808 0.02197 -0.0552 0.0875 0.6891
14.750 1.6572 0.02955 0.02351 -0.0540 0.0849 0.7069
15.000 1.6620 0.03124 0.02528 -0.0528 0.0825 0.7274
15.250 1.6690 0.03283 0.02697 -0.0518 0.0807 0.7514
15.500 1.6750 0.03456 0.02883 -0.0510 0.0786 0.7826
15.750 1.6781 0.03655 0.03098 -0.0502 0.0765 0.8330
16.000 1.6740 0.03855 0.03324 -0.0485 0.0747 1.0000
16.250 1.6763 0.04093 0.03567 -0.0481 0.0730 1.0000
16.500 1.6792 0.04334 0.03814 -0.0479 0.0715 1.0000
16.750 1.6792 0.04612 0.04097 -0.0478 0.0695 1.0000
17.000 1.6771 0.04923 0.04413 -0.0479 0.0678 1.0000
17.250 1.6727 0.05270 0.04765 -0.0483 0.0660 1.0000
17.500 1.6721 0.05584 0.05088 -0.0487 0.0647 1.0000
17.750 1.6693 0.05933 0.05443 -0.0493 0.0633 1.0000
18.000 1.6638 0.06325 0.05842 -0.0502 0.0617 1.0000
18.250 1.6563 0.06755 0.06279 -0.0513 0.0603 1.0000
18.500 1.6479 0.07206 0.06737 -0.0526 0.0589 1.0000
18.750 1.6428 0.07624 0.07164 -0.0539 0.0579 1.0000
19.000 1.6366 0.08066 0.07614 -0.0553 0.0568 1.0000
19.250 1.6281 0.08549 0.08104 -0.0571 0.0554 1.0000
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