NREL's S808 Airfoil (s808-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S808 Airfoil (s808-nr) Reynolds number: 100,000 Max Cl/Cd: 41.38 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s808-nr-100000-n5.txt Download as CSV file: xf-s808-nr-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4784 0.10336 0.09618 -0.0387 1.0000 0.2132
-12.000 -0.4650 0.10253 0.09535 -0.0379 1.0000 0.2155
-11.750 -0.5017 0.09520 0.08798 -0.0405 1.0000 0.2254
-11.500 -0.4823 0.09518 0.08796 -0.0393 1.0000 0.2265
-11.250 -0.4656 0.09480 0.08759 -0.0382 1.0000 0.2279
-11.000 -0.4530 0.09393 0.08672 -0.0373 1.0000 0.2300
-10.500 -0.4829 0.08557 0.07833 -0.0385 1.0000 0.2414
-8.500 -0.7634 0.04027 0.03282 -0.0455 0.9845 0.2897
-8.250 -0.7221 0.04028 0.03283 -0.0475 0.9797 0.2909
-8.000 -0.6870 0.03999 0.03253 -0.0491 0.9728 0.2923
-7.750 -0.6501 0.03947 0.03198 -0.0515 0.9662 0.2943
-7.500 -0.6279 0.03752 0.02992 -0.0543 0.9552 0.2979
-7.250 -0.6234 0.03233 0.02420 -0.0603 0.9399 0.3050
-7.000 -0.5871 0.03135 0.02315 -0.0630 0.9334 0.3072
-6.750 -0.5596 0.03098 0.02281 -0.0630 0.9217 0.3087
-6.500 -0.5266 0.03051 0.02235 -0.0642 0.9126 0.3106
-6.250 -0.4944 0.02993 0.02173 -0.0655 0.9028 0.3130
-6.000 -0.4659 0.02908 0.02080 -0.0666 0.8913 0.3161
-5.750 -0.4316 0.02772 0.01925 -0.0694 0.8832 0.3202
-5.500 -0.4041 0.02637 0.01766 -0.0711 0.8704 0.3239
-5.250 -0.3633 0.02598 0.01732 -0.0731 0.8634 0.3257
-5.000 -0.3314 0.02562 0.01697 -0.0737 0.8505 0.3277
-4.750 -0.2925 0.02518 0.01651 -0.0758 0.8403 0.3303
-4.500 -0.2548 0.02463 0.01589 -0.0778 0.8286 0.3336
-4.250 -0.2192 0.02394 0.01505 -0.0798 0.8151 0.3377
-4.000 -0.1800 0.02311 0.01398 -0.0826 0.8027 0.3420
-3.750 -0.1440 0.02286 0.01376 -0.0838 0.7883 0.3441
-3.500 -0.1105 0.02263 0.01352 -0.0847 0.7727 0.3465
-3.250 -0.0769 0.02237 0.01319 -0.0857 0.7576 0.3493
-3.000 -0.0431 0.02206 0.01277 -0.0869 0.7427 0.3528
-2.750 -0.0119 0.02169 0.01224 -0.0878 0.7271 0.3570
-2.500 0.0180 0.02137 0.01179 -0.0884 0.7117 0.3608
-2.250 0.0476 0.02131 0.01173 -0.0885 0.6970 0.3634
-2.000 0.0779 0.02123 0.01160 -0.0888 0.6834 0.3664
-1.750 0.1053 0.02111 0.01144 -0.0887 0.6686 0.3697
-1.500 0.1338 0.02094 0.01117 -0.0889 0.6549 0.3735
-1.250 0.1638 0.02073 0.01076 -0.0895 0.6424 0.3779
-1.000 0.1904 0.02066 0.01072 -0.0892 0.6286 0.3809
-0.750 0.2178 0.02067 0.01073 -0.0889 0.6162 0.3841
-0.500 0.2456 0.02066 0.01068 -0.0888 0.6041 0.3879
-0.250 0.2728 0.02061 0.01058 -0.0887 0.5917 0.3922
0.000 0.3018 0.02051 0.01032 -0.0890 0.5806 0.3969
0.250 0.3282 0.02049 0.01033 -0.0887 0.5685 0.4001
0.500 0.3553 0.02054 0.01038 -0.0884 0.5579 0.4036
0.750 0.3820 0.02057 0.01042 -0.0881 0.5465 0.4078
1.000 0.4096 0.02059 0.01038 -0.0880 0.5361 0.4129
1.250 0.4373 0.02059 0.01029 -0.0880 0.5254 0.4179
1.500 0.4635 0.02066 0.01042 -0.0876 0.5152 0.4214
1.750 0.4899 0.02074 0.01051 -0.0872 0.5051 0.4255
2.000 0.5168 0.02082 0.01057 -0.0870 0.4953 0.4306
2.250 0.5443 0.02088 0.01055 -0.0870 0.4854 0.4366
2.500 0.5702 0.02099 0.01072 -0.0865 0.4761 0.4407
2.750 0.5961 0.02111 0.01088 -0.0860 0.4666 0.4455
3.000 0.6227 0.02124 0.01099 -0.0858 0.4577 0.4511
3.500 0.6751 0.02151 0.01126 -0.0851 0.4400 0.4616
3.750 0.7001 0.02168 0.01151 -0.0845 0.4306 0.4672
4.000 0.7269 0.02186 0.01161 -0.0843 0.4228 0.4740
4.250 0.7518 0.02203 0.01188 -0.0838 0.4136 0.4798
4.500 0.7768 0.02223 0.01210 -0.0832 0.4057 0.4852
4.750 0.8019 0.02245 0.01237 -0.0827 0.3974 0.4919
5.000 0.8269 0.02267 0.01260 -0.0822 0.3892 0.4989
5.250 0.8511 0.02292 0.01288 -0.0815 0.3821 0.5050
5.500 0.8748 0.02318 0.01323 -0.0808 0.3735 0.5125
5.750 0.8997 0.02344 0.01345 -0.0802 0.3665 0.5200
6.000 0.9224 0.02373 0.01387 -0.0793 0.3588 0.5264
6.250 0.9458 0.02402 0.01420 -0.0786 0.3512 0.5346
6.500 0.9695 0.02434 0.01452 -0.0779 0.3445 0.5423
6.750 0.9912 0.02468 0.01501 -0.0769 0.3369 0.5503
7.000 1.0145 0.02502 0.01532 -0.0762 0.3302 0.5598
7.250 1.0355 0.02540 0.01581 -0.0751 0.3233 0.5672
7.500 1.0566 0.02578 0.01628 -0.0741 0.3162 0.5768
7.750 1.0782 0.02616 0.01664 -0.0731 0.3102 0.5855
8.000 1.0975 0.02661 0.01723 -0.0718 0.3032 0.5954
8.250 1.1166 0.02704 0.01774 -0.0706 0.2966 0.6050
8.500 1.1371 0.02748 0.01816 -0.0695 0.2911 0.6156
8.750 1.1527 0.02799 0.01885 -0.0677 0.2844 0.6257
9.000 1.1686 0.02846 0.01939 -0.0660 0.2784 0.6370
9.250 1.1860 0.02895 0.01988 -0.0644 0.2732 0.6481
9.500 1.1995 0.02960 0.02069 -0.0626 0.2669 0.6607
9.750 1.2132 0.03019 0.02138 -0.0606 0.2612 0.6725
10.000 1.2297 0.03077 0.02193 -0.0592 0.2564 0.6861
10.500 1.2515 0.03230 0.02379 -0.0551 0.2450 0.7152
10.750 1.2646 0.03297 0.02449 -0.0534 0.2404 0.7320
11.000 1.2730 0.03389 0.02559 -0.0513 0.2352 0.7503
11.250 1.2803 0.03482 0.02669 -0.0491 0.2300 0.7712
11.750 1.2939 0.03650 0.02856 -0.0445 0.2214 0.8320
12.000 1.2860 0.03734 0.02970 -0.0404 0.2173 0.9689
12.250 1.2951 0.03878 0.03119 -0.0397 0.2122 1.0000
12.500 1.3064 0.04007 0.03243 -0.0391 0.2080 1.0000
12.750 1.3124 0.04184 0.03427 -0.0384 0.2036 1.0000
13.000 1.3155 0.04384 0.03639 -0.0378 0.1988 1.0000
13.250 1.3208 0.04569 0.03826 -0.0373 0.1945 1.0000
13.500 1.3313 0.04720 0.03969 -0.0369 0.1908 1.0000
13.750 1.3273 0.05008 0.04277 -0.0367 0.1865 1.0000
14.000 1.3266 0.05274 0.04554 -0.0366 0.1823 1.0000
14.250 1.3303 0.05501 0.04783 -0.0366 0.1785 1.0000
14.500 1.3355 0.05724 0.05004 -0.0367 0.1750 1.0000
14.750 1.3255 0.06127 0.05429 -0.0374 0.1711 1.0000
15.000 1.3205 0.06483 0.05796 -0.0381 0.1673 1.0000
15.250 1.3231 0.06754 0.06068 -0.0386 0.1638 1.0000
15.500 1.3249 0.07046 0.06362 -0.0393 0.1605 1.0000
15.750 1.3046 0.07649 0.06989 -0.0414 0.1569 1.0000
16.000 1.2930 0.08153 0.07508 -0.0433 0.1532 1.0000
16.250 1.2962 0.08448 0.07803 -0.0443 0.1500 1.0000
16.500 1.2979 0.08771 0.08128 -0.0453 0.1470 1.0000
16.750 1.2485 0.09926 0.09319 -0.0511 0.1430 1.0000
17.000 1.2239 0.10721 0.10130 -0.0551 0.1391 1.0000
17.250 1.2434 0.10766 0.10168 -0.0549 0.1365 1.0000
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