NREL's S808 Airfoil (s808-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S808 Airfoil (s808-nr) Reynolds number: 500,000 Max Cl/Cd: 76.57 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s808-nr-500000-n5.txt Download as CSV file: xf-s808-nr-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.9432 0.08787 0.08340 -0.0518 1.0000 0.0897
-17.000 -0.9575 0.08336 0.07889 -0.0531 1.0000 0.0949
-16.500 -0.9871 0.07449 0.07001 -0.0556 1.0000 0.1057
-16.250 -1.0033 0.07005 0.06555 -0.0567 1.0000 0.1111
-16.000 -1.0249 0.06513 0.06062 -0.0579 1.0000 0.1171
-15.750 -1.0457 0.06045 0.05592 -0.0589 1.0000 0.1229
-15.500 -1.0704 0.05554 0.05100 -0.0599 1.0000 0.1299
-15.250 -1.0943 0.05091 0.04635 -0.0606 1.0000 0.1355
-15.000 -1.1189 0.04646 0.04188 -0.0609 1.0000 0.1424
-14.750 -1.1450 0.04225 0.03764 -0.0609 1.0000 0.1480
-14.500 -1.1683 0.03854 0.03390 -0.0604 1.0000 0.1539
-14.250 -1.1935 0.03489 0.03023 -0.0595 1.0000 0.1592
-14.000 -1.2150 0.03179 0.02710 -0.0581 1.0000 0.1644
-13.750 -1.2317 0.02926 0.02452 -0.0564 1.0000 0.1689
-13.500 -1.2438 0.02629 0.02152 -0.0565 0.9988 0.1742
-13.250 -1.2237 0.02427 0.01944 -0.0602 0.9951 0.1816
-13.000 -1.2061 0.02212 0.01726 -0.0641 0.9911 0.1879
-12.750 -1.1888 0.02058 0.01565 -0.0661 0.9865 0.1937
-12.500 -1.1605 0.01931 0.01432 -0.0694 0.9830 0.1986
-12.250 -1.1283 0.01835 0.01334 -0.0726 0.9806 0.2050
-12.000 -1.0932 0.01784 0.01274 -0.0751 0.9791 0.2102
-11.750 -1.0703 0.01717 0.01207 -0.0756 0.9752 0.2144
-11.500 -1.0431 0.01666 0.01154 -0.0765 0.9715 0.2187
-11.250 -1.0108 0.01629 0.01110 -0.0781 0.9690 0.2234
-11.000 -0.9769 0.01586 0.01066 -0.0800 0.9669 0.2287
-10.500 -0.9096 0.01519 0.00995 -0.0833 0.9628 0.2363
-10.250 -0.8869 0.01488 0.00958 -0.0827 0.9570 0.2382
-10.000 -0.8540 0.01458 0.00922 -0.0839 0.9539 0.2397
-9.750 -0.8188 0.01424 0.00884 -0.0856 0.9515 0.2414
-9.500 -0.7820 0.01388 0.00848 -0.0877 0.9497 0.2436
-9.250 -0.7635 0.01359 0.00818 -0.0861 0.9410 0.2453
-9.000 -0.7311 0.01329 0.00786 -0.0871 0.9365 0.2471
-8.750 -0.6953 0.01299 0.00753 -0.0888 0.9333 0.2490
-8.500 -0.6774 0.01274 0.00725 -0.0869 0.9206 0.2506
-8.250 -0.6465 0.01248 0.00695 -0.0875 0.9128 0.2523
-8.000 -0.6119 0.01222 0.00664 -0.0889 0.9031 0.2541
-7.750 -0.5712 0.01198 0.00634 -0.0913 0.8933 0.2558
-7.500 -0.5264 0.01166 0.00598 -0.0947 0.8807 0.2583
-7.250 -0.4835 0.01139 0.00565 -0.0977 0.8609 0.2605
-7.000 -0.4478 0.01124 0.00538 -0.0992 0.8349 0.2625
-6.750 -0.4174 0.01116 0.00517 -0.0996 0.8087 0.2645
-6.500 -0.3894 0.01112 0.00500 -0.0995 0.7850 0.2665
-6.250 -0.3621 0.01108 0.00484 -0.0994 0.7628 0.2684
-6.000 -0.3349 0.01106 0.00469 -0.0992 0.7424 0.2702
-5.750 -0.3077 0.01104 0.00456 -0.0990 0.7233 0.2718
-5.500 -0.2806 0.01098 0.00442 -0.0988 0.7051 0.2740
-5.250 -0.2532 0.01091 0.00431 -0.0987 0.6884 0.2765
-5.000 -0.2256 0.01087 0.00420 -0.0986 0.6724 0.2788
-4.750 -0.1979 0.01084 0.00410 -0.0985 0.6575 0.2811
-4.500 -0.1703 0.01083 0.00401 -0.0983 0.6425 0.2833
-4.250 -0.1421 0.01080 0.00391 -0.0983 0.6283 0.2855
-4.000 -0.1140 0.01079 0.00383 -0.0983 0.6152 0.2874
-3.750 -0.0861 0.01080 0.00375 -0.0982 0.6018 0.2891
-3.500 -0.0577 0.01074 0.00367 -0.0982 0.5888 0.2916
-3.250 -0.0294 0.01072 0.00361 -0.0982 0.5770 0.2941
-3.000 -0.0012 0.01071 0.00355 -0.0982 0.5645 0.2968
-2.750 0.0274 0.01070 0.00351 -0.0982 0.5532 0.2996
-2.250 0.0844 0.01073 0.00342 -0.0982 0.5307 0.3045
-2.000 0.1126 0.01076 0.00339 -0.0981 0.5198 0.3065
-1.750 0.1415 0.01073 0.00336 -0.0982 0.5096 0.3093
-1.500 0.1698 0.01075 0.00334 -0.0982 0.4993 0.3119
-1.250 0.1985 0.01076 0.00333 -0.0983 0.4887 0.3147
-1.000 0.2269 0.01080 0.00333 -0.0982 0.4795 0.3174
-0.750 0.2557 0.01083 0.00332 -0.0983 0.4696 0.3202
-0.500 0.2839 0.01090 0.00333 -0.0982 0.4599 0.3229
-0.250 0.3127 0.01091 0.00334 -0.0982 0.4507 0.3259
0.000 0.3408 0.01096 0.00337 -0.0982 0.4418 0.3291
0.250 0.3697 0.01099 0.00339 -0.0982 0.4327 0.3321
0.500 0.3977 0.01106 0.00343 -0.0981 0.4236 0.3352
0.750 0.4264 0.01111 0.00346 -0.0981 0.4155 0.3382
1.000 0.4544 0.01120 0.00351 -0.0980 0.4063 0.3408
1.250 0.4828 0.01125 0.00356 -0.0980 0.3985 0.3440
1.500 0.5111 0.01131 0.00362 -0.0979 0.3901 0.3479
1.750 0.5390 0.01140 0.00369 -0.0978 0.3821 0.3519
2.000 0.5673 0.01148 0.00376 -0.0977 0.3740 0.3556
2.250 0.5947 0.01160 0.00384 -0.0975 0.3662 0.3587
2.500 0.6230 0.01167 0.00392 -0.0974 0.3589 0.3620
2.750 0.6507 0.01177 0.00402 -0.0973 0.3508 0.3660
3.000 0.6782 0.01188 0.00413 -0.0971 0.3438 0.3705
3.250 0.7060 0.01198 0.00424 -0.0969 0.3363 0.3750
3.500 0.7327 0.01215 0.00436 -0.0966 0.3286 0.3787
3.750 0.7606 0.01223 0.00448 -0.0965 0.3222 0.3831
4.000 0.7877 0.01236 0.00461 -0.0962 0.3150 0.3876
4.250 0.8143 0.01252 0.00476 -0.0959 0.3080 0.3925
4.500 0.8415 0.01265 0.00490 -0.0956 0.3014 0.3972
4.750 0.8678 0.01281 0.00506 -0.0952 0.2944 0.4023
5.000 0.8943 0.01296 0.00524 -0.0949 0.2882 0.4077
5.250 0.9207 0.01312 0.00540 -0.0945 0.2815 0.4128
5.500 0.9459 0.01334 0.00559 -0.0939 0.2749 0.4173
5.750 0.9723 0.01348 0.00578 -0.0935 0.2689 0.4229
6.000 0.9979 0.01367 0.00598 -0.0930 0.2626 0.4294
6.250 1.0221 0.01391 0.00621 -0.0923 0.2563 0.4353
6.500 1.0478 0.01407 0.00641 -0.0918 0.2507 0.4410
6.750 1.0722 0.01429 0.00665 -0.0911 0.2444 0.4471
7.000 1.0956 0.01455 0.00690 -0.0903 0.2385 0.4532
7.250 1.1199 0.01475 0.00713 -0.0895 0.2330 0.4588
7.500 1.1422 0.01499 0.00740 -0.0885 0.2271 0.4656
7.750 1.1632 0.01526 0.00768 -0.0872 0.2217 0.4729
8.000 1.1853 0.01548 0.00794 -0.0861 0.2165 0.4796
8.250 1.2061 0.01577 0.00825 -0.0849 0.2109 0.4870
8.500 1.2262 0.01611 0.00859 -0.0835 0.2056 0.4942
8.750 1.2476 0.01639 0.00892 -0.0824 0.2006 0.5007
9.000 1.2673 0.01674 0.00930 -0.0810 0.1951 0.5083
9.250 1.2863 0.01714 0.00970 -0.0796 0.1902 0.5163
9.500 1.3067 0.01746 0.01009 -0.0784 0.1856 0.5247
9.750 1.3252 0.01787 0.01053 -0.0770 0.1804 0.5337
10.000 1.3423 0.01836 0.01102 -0.0754 0.1757 0.5417
10.250 1.3614 0.01874 0.01147 -0.0741 0.1716 0.5505
10.500 1.3787 0.01922 0.01198 -0.0725 0.1668 0.5592
10.750 1.3938 0.01980 0.01259 -0.0708 0.1624 0.5689
11.000 1.4109 0.02030 0.01315 -0.0694 0.1587 0.5792
11.250 1.4271 0.02085 0.01376 -0.0679 0.1544 0.5893
11.500 1.4404 0.02156 0.01450 -0.0661 0.1500 0.5993
11.750 1.4543 0.02225 0.01525 -0.0645 0.1463 0.6104
12.000 1.4688 0.02294 0.01600 -0.0630 0.1427 0.6220
12.250 1.4810 0.02377 0.01690 -0.0614 0.1387 0.6344
12.500 1.4904 0.02479 0.01797 -0.0596 0.1350 0.6460
12.750 1.5035 0.02565 0.01891 -0.0583 0.1318 0.6599
13.000 1.5143 0.02667 0.02002 -0.0569 0.1282 0.6750
13.250 1.5224 0.02793 0.02134 -0.0554 0.1247 0.6901
13.500 1.5305 0.02924 0.02274 -0.0541 0.1217 0.7074
13.750 1.5400 0.03050 0.02411 -0.0530 0.1187 0.7271
14.000 1.5467 0.03202 0.02573 -0.0518 0.1154 0.7500
14.500 1.5556 0.03549 0.02947 -0.0497 0.1099 0.8193
14.750 1.5540 0.03697 0.03122 -0.0475 0.1075 1.0000
15.000 1.5579 0.03913 0.03342 -0.0470 0.1047 1.0000
15.250 1.5587 0.04168 0.03600 -0.0467 0.1020 1.0000
15.500 1.5609 0.04418 0.03856 -0.0465 0.0997 1.0000
15.750 1.5640 0.04666 0.04111 -0.0465 0.0974 1.0000
16.000 1.5642 0.04954 0.04404 -0.0466 0.0948 1.0000
16.250 1.5619 0.05280 0.04735 -0.0470 0.0926 1.0000
16.500 1.5586 0.05626 0.05087 -0.0475 0.0905 1.0000
16.750 1.5588 0.05940 0.05409 -0.0480 0.0885 1.0000
17.000 1.5566 0.06291 0.05768 -0.0488 0.0865 1.0000
17.250 1.5519 0.06684 0.06166 -0.0498 0.0845 1.0000
17.500 1.5446 0.07122 0.06611 -0.0510 0.0826 1.0000
17.750 1.5407 0.07523 0.07019 -0.0522 0.0809 1.0000
18.000 1.5372 0.07926 0.07431 -0.0535 0.0791 1.0000
18.250 1.5314 0.08370 0.07883 -0.0551 0.0773 1.0000
18.500 1.5235 0.08852 0.08372 -0.0569 0.0756 1.0000
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