NREL's S809 Airfoil (s809-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S809 Airfoil (s809-nr) Reynolds number: 200,000 Max Cl/Cd: 51.73 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s809-nr-200000.txt Download as CSV file: xf-s809-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S809 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
------ -------- --------- --------- -------- -------- --------
-18.500 -0.3847 0.16853 0.16539 -0.0171 1.0000 0.0399
-18.250 -0.3979 0.16359 0.16047 -0.0219 1.0000 0.0415
-10.500 -0.5268 0.04432 0.03610 -0.0645 0.7562 0.0247
-10.250 -0.4882 0.04514 0.03685 -0.0630 0.7504 0.0247
-10.000 -0.4602 0.04550 0.03718 -0.0618 0.7451 0.0248
-9.750 -0.4386 0.04542 0.03701 -0.0606 0.7408 0.0260
-9.500 -0.4224 0.04504 0.03661 -0.0594 0.7373 0.0267
-9.250 -0.4128 0.04401 0.03560 -0.0585 0.7339 0.0273
-9.000 -0.4059 0.04263 0.03422 -0.0578 0.7308 0.0286
-8.750 -0.4013 0.04102 0.03258 -0.0569 0.7280 0.0304
-8.500 -0.3965 0.03946 0.03095 -0.0561 0.7255 0.0342
-8.250 -0.3955 0.03769 0.02912 -0.0551 0.7232 0.0391
-8.000 -0.3975 0.03576 0.02717 -0.0537 0.7209 0.0481
-7.750 -0.4050 0.03363 0.02516 -0.0520 0.7185 0.0688
-7.500 -0.4288 0.03063 0.02252 -0.0493 0.7164 0.1330
-7.250 -0.4563 0.02741 0.01959 -0.0463 0.7144 0.1990
-7.000 -0.4834 0.02420 0.01656 -0.0431 0.7125 0.2427
-6.750 -0.5081 0.02134 0.01379 -0.0398 0.7108 0.2733
-6.500 -0.1434 0.06175 0.05505 -0.0436 0.7076 0.5481
-6.250 -0.1118 0.06006 0.05326 -0.0448 0.7063 0.5485
-6.000 -0.0815 0.05857 0.05171 -0.0459 0.7051 0.5490
-5.750 -0.0527 0.05729 0.05039 -0.0468 0.7038 0.5497
-5.500 -0.0238 0.05622 0.04928 -0.0476 0.7026 0.5508
-5.250 0.0034 0.05534 0.04836 -0.0483 0.7014 0.5525
-5.000 -0.0377 0.05561 0.04867 -0.0436 0.7003 0.5637
-4.750 -0.0060 0.05422 0.04723 -0.0447 0.6992 0.5642
-4.500 0.0247 0.05305 0.04603 -0.0458 0.6981 0.5648
-4.250 0.0548 0.05207 0.04502 -0.0467 0.6970 0.5658
-4.000 0.0821 0.05125 0.04417 -0.0473 0.6957 0.5672
-3.750 0.0386 0.05173 0.04469 -0.0416 0.6945 0.5790
-3.500 0.0709 0.05045 0.04338 -0.0429 0.6937 0.5794
-3.250 0.1022 0.04939 0.04229 -0.0439 0.6929 0.5800
-3.000 0.1335 0.04851 0.04140 -0.0449 0.6922 0.5809
-2.750 0.1627 0.04780 0.04068 -0.0457 0.6914 0.5821
-2.500 0.1167 0.04836 0.04129 -0.0391 0.6906 0.5943
-2.250 0.1493 0.04722 0.04017 -0.0405 0.6900 0.5947
-2.000 0.1811 0.04627 0.03925 -0.0417 0.6893 0.5952
-1.750 0.2124 0.04548 0.03850 -0.0427 0.6883 0.5961
-1.500 0.2427 0.04487 0.03793 -0.0435 0.6872 0.5973
-1.250 0.2693 0.04437 0.03748 -0.0440 0.6865 0.5989
-1.000 0.2913 0.04395 0.03711 -0.0441 0.6857 0.6013
-0.750 0.1889 0.04117 0.03437 -0.0334 0.6843 0.5948
-0.500 0.2148 0.04066 0.03390 -0.0335 0.6830 0.5953
-0.250 0.2413 0.04027 0.03355 -0.0338 0.6819 0.5960
0.000 0.2675 0.03995 0.03327 -0.0340 0.6807 0.5969
0.250 0.2950 0.03968 0.03305 -0.0343 0.6794 0.5982
0.500 0.3239 0.03959 0.03300 -0.0348 0.6784 0.6007
0.750 0.2347 0.03160 0.02473 -0.0337 0.6764 0.5827
1.000 0.2584 0.03167 0.02482 -0.0336 0.6752 0.5842
1.250 0.2753 0.03147 0.02470 -0.0335 0.6737 0.5860
1.500 0.2900 0.03101 0.02431 -0.0339 0.6714 0.5880
1.750 0.3068 0.03035 0.02364 -0.0350 0.6692 0.5907
2.000 0.3277 0.02937 0.02254 -0.0374 0.6667 0.5947
2.250 0.3504 0.02957 0.02284 -0.0369 0.6646 0.5956
2.500 0.3754 0.02971 0.02305 -0.0368 0.6627 0.5966
2.750 0.4033 0.02972 0.02311 -0.0370 0.6610 0.5978
3.000 0.4330 0.02970 0.02310 -0.0377 0.6595 0.5989
3.250 0.4337 0.03064 0.02424 -0.0355 0.6530 0.6002
3.500 0.4566 0.03069 0.02434 -0.0356 0.6493 0.6018
3.750 0.4870 0.03041 0.02408 -0.0366 0.6468 0.6035
4.000 0.5220 0.02998 0.02365 -0.0382 0.6449 0.6056
4.250 0.5283 0.03078 0.02453 -0.0370 0.6375 0.6080
4.500 0.5575 0.03049 0.02424 -0.0381 0.6331 0.6100
4.750 0.5942 0.02985 0.02367 -0.0391 0.6304 0.6111
5.000 0.6365 0.02908 0.02292 -0.0407 0.6282 0.6123
5.250 0.6385 0.02989 0.02393 -0.0379 0.6180 0.6133
5.500 0.6847 0.02862 0.02270 -0.0398 0.6144 0.6148
5.750 0.7071 0.02843 0.02262 -0.0391 0.6063 0.6162
6.000 0.7501 0.02706 0.02126 -0.0406 0.5998 0.6183
6.250 0.7834 0.02621 0.02046 -0.0412 0.5922 0.6205
6.500 0.8181 0.02524 0.01952 -0.0421 0.5844 0.6226
6.750 0.8523 0.02431 0.01861 -0.0430 0.5764 0.6245
7.000 0.8880 0.02302 0.01735 -0.0437 0.5665 0.6260
7.250 0.9114 0.02224 0.01673 -0.0426 0.5543 0.6272
7.500 0.9364 0.02134 0.01596 -0.0417 0.5407 0.6286
7.750 0.9578 0.02056 0.01536 -0.0403 0.5234 0.6301
8.000 0.9735 0.02011 0.01513 -0.0382 0.4944 0.6319
8.250 0.9880 0.01910 0.01367 -0.0350 0.4166 0.6339
8.500 0.9748 0.01991 0.01399 -0.0286 0.3487 0.6355
8.750 0.9561 0.02111 0.01487 -0.0221 0.3004 0.6370
9.000 0.9392 0.02287 0.01635 -0.0170 0.2549 0.6384
9.250 0.9236 0.02497 0.01821 -0.0133 0.2148 0.6397
9.500 0.9099 0.02740 0.02040 -0.0106 0.1790 0.6408
9.750 0.8995 0.02984 0.02267 -0.0085 0.1468 0.6419
10.250 0.8886 0.03445 0.02699 -0.0054 0.0996 0.6443
10.500 0.8878 0.03652 0.02899 -0.0043 0.0855 0.6456
10.750 0.8891 0.03850 0.03094 -0.0032 0.0747 0.6471
11.000 0.8900 0.04054 0.03292 -0.0022 0.0667 0.6488
11.250 0.8969 0.04218 0.03459 -0.0016 0.0600 0.6508
11.500 0.9016 0.04403 0.03641 -0.0007 0.0552 0.6528
11.750 0.9120 0.04552 0.03794 -0.0004 0.0505 0.6549
12.000 0.9201 0.04720 0.03951 0.0005 0.0463 0.6565
12.250 0.9329 0.04848 0.04096 0.0009 0.0436 0.6581
12.500 0.9460 0.04980 0.04236 0.0014 0.0410 0.6600
12.750 0.9599 0.05112 0.04368 0.0019 0.0386 0.6619
13.000 0.9790 0.05231 0.04494 0.0026 0.0361 0.6641
13.250 0.9933 0.05378 0.04656 0.0029 0.0342 0.6665
13.500 1.0089 0.05527 0.04813 0.0031 0.0326 0.6689
14.000 1.0517 0.05849 0.05147 0.0038 0.0294 0.6736
14.250 1.0535 0.06083 0.05408 0.0039 0.0285 0.6757
14.500 1.0582 0.06335 0.05685 0.0040 0.0275 0.6782
14.750 1.0631 0.06603 0.05976 0.0040 0.0266 0.6808
15.000 1.0671 0.06882 0.06273 0.0039 0.0259 0.6837
15.250 1.0693 0.07173 0.06576 0.0035 0.0251 0.6864
15.500 1.0734 0.07444 0.06857 0.0031 0.0243 0.6888
15.750 1.0737 0.07897 0.07328 0.0028 0.0234 0.6910
16.000 1.0585 0.08333 0.07792 0.0016 0.0232 0.6929
16.250 1.0427 0.08833 0.08321 0.0001 0.0229 0.6948
16.500 1.0251 0.09402 0.08918 -0.0019 0.0227 0.6967
16.750 1.0066 0.10014 0.09555 -0.0045 0.0225 0.6985
17.000 0.9867 0.10700 0.10265 -0.0077 0.0226 0.7002
17.250 0.9648 0.11460 0.11048 -0.0117 0.0225 0.7017
17.500 0.9440 0.12245 0.11854 -0.0161 0.0227 0.7030
17.750 0.9196 0.13156 0.12786 -0.0217 0.0228 0.7039
18.000 0.8950 0.14143 0.13791 -0.0280 0.0231 0.7047
18.250 0.8739 0.15115 0.14774 -0.0340 0.0234 0.7056
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