NREL's S808 Airfoil (s808-nr) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S808 Airfoil (s808-nr) Reynolds number: 50,000 Max Cl/Cd: 24.59 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s808-nr-50000-n5.txt Download as CSV file: xf-s808-nr-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3512 0.11792 0.10794 -0.0304 1.0000 0.2655
-11.000 -0.3568 0.11525 0.10525 -0.0307 1.0000 0.2696
-10.750 -0.3586 0.11287 0.10288 -0.0306 1.0000 0.2736
-10.500 -0.3412 0.11159 0.10160 -0.0297 1.0000 0.2765
-10.250 -0.3326 0.10987 0.09990 -0.0292 1.0000 0.2797
-10.000 -0.3313 0.10771 0.09773 -0.0289 1.0000 0.2828
-9.750 -0.3445 0.10493 0.09496 -0.0289 1.0000 0.2872
-9.500 -0.3424 0.10287 0.09292 -0.0283 1.0000 0.2903
-9.250 -0.3274 0.10163 0.09170 -0.0273 1.0000 0.2926
-9.000 -0.3201 0.09996 0.09005 -0.0265 1.0000 0.2949
-8.750 -0.3171 0.09818 0.08829 -0.0256 1.0000 0.2978
-8.500 -0.3215 0.09606 0.08621 -0.0249 1.0000 0.3013
-8.250 -0.3441 0.09285 0.08303 -0.0244 1.0000 0.3051
-8.000 -0.3437 0.09098 0.08121 -0.0232 1.0000 0.3071
-7.750 -0.3326 0.08999 0.08026 -0.0217 1.0000 0.3088
-7.500 -0.3262 0.08890 0.07923 -0.0200 1.0000 0.3111
-7.250 -0.3260 0.08761 0.07800 -0.0183 1.0000 0.3137
-7.000 -0.3341 0.08602 0.07648 -0.0164 1.0000 0.3164
-6.750 -0.3523 0.08403 0.07457 -0.0142 1.0000 0.3190
-6.500 -0.3865 0.08144 0.07205 -0.0116 1.0000 0.3216
-6.250 -0.3648 0.07846 0.06903 -0.0165 0.9899 0.3251
-6.000 -0.3235 0.07725 0.06780 -0.0201 0.9806 0.3277
-5.750 -0.2928 0.07537 0.06589 -0.0237 0.9692 0.3308
-5.500 -0.2741 0.07269 0.06317 -0.0273 0.9555 0.3340
-5.000 -0.2794 0.06506 0.05544 -0.0336 0.9197 0.3432
-4.750 -0.2475 0.06422 0.05461 -0.0347 0.9062 0.3455
-4.500 -0.2214 0.06264 0.05303 -0.0365 0.8925 0.3485
-4.000 -0.2265 0.05247 0.04258 -0.0460 0.8599 0.3613
-3.750 -0.1896 0.05212 0.04226 -0.0468 0.8488 0.3634
-3.500 -0.1591 0.05123 0.04137 -0.0478 0.8364 0.3664
-3.250 -0.1297 0.04867 0.03871 -0.0518 0.8264 0.3717
-3.000 -0.1305 0.04374 0.03350 -0.0564 0.8101 0.3800
-2.750 -0.0978 0.04344 0.03323 -0.0567 0.7978 0.3823
-2.500 -0.0597 0.04281 0.03259 -0.0581 0.7874 0.3856
-2.250 -0.0377 0.04159 0.03129 -0.0590 0.7729 0.3905
-2.000 -0.0137 0.03860 0.02802 -0.0636 0.7607 0.3987
-1.750 0.0185 0.03826 0.02770 -0.0638 0.7483 0.4011
-1.500 0.0452 0.03792 0.02735 -0.0637 0.7346 0.4043
-1.250 0.0812 0.03713 0.02647 -0.0655 0.7240 0.4092
-1.000 0.1040 0.03539 0.02450 -0.0681 0.7094 0.4175
-0.750 0.1314 0.03533 0.02448 -0.0675 0.6966 0.4201
-0.500 0.1634 0.03504 0.02417 -0.0678 0.6852 0.4237
-0.250 0.1864 0.03471 0.02382 -0.0676 0.6713 0.4280
0.000 0.2189 0.03377 0.02268 -0.0699 0.6599 0.4353
0.250 0.2448 0.03352 0.02243 -0.0698 0.6472 0.4396
0.500 0.2696 0.03351 0.02247 -0.0690 0.6350 0.4434
0.750 0.3002 0.03322 0.02211 -0.0696 0.6241 0.4486
1.000 0.3259 0.03277 0.02157 -0.0705 0.6114 0.4553
1.250 0.3578 0.03254 0.02129 -0.0710 0.6015 0.4600
1.500 0.3777 0.03270 0.02154 -0.0697 0.5888 0.4642
1.750 0.4074 0.03255 0.02135 -0.0702 0.5788 0.4703
2.000 0.4352 0.03229 0.02100 -0.0712 0.5670 0.4778
2.250 0.4599 0.03239 0.02117 -0.0703 0.5568 0.4817
2.500 0.4843 0.03248 0.02131 -0.0697 0.5462 0.4868
2.750 0.5120 0.03245 0.02123 -0.0701 0.5360 0.4942
3.000 0.5379 0.03248 0.02126 -0.0700 0.5257 0.5004
3.250 0.5612 0.03268 0.02153 -0.0691 0.5162 0.5056
3.500 0.5865 0.03278 0.02164 -0.0690 0.5061 0.5125
3.750 0.6138 0.03286 0.02169 -0.0693 0.4966 0.5199
4.000 0.6352 0.03313 0.02207 -0.0681 0.4870 0.5253
4.250 0.6625 0.03329 0.02220 -0.0681 0.4784 0.5332
4.500 0.6851 0.03359 0.02256 -0.0677 0.4683 0.5409
4.750 0.7127 0.03370 0.02268 -0.0673 0.4606 0.5474
5.000 0.7307 0.03423 0.02333 -0.0664 0.4505 0.5553
5.250 0.7612 0.03428 0.02333 -0.0665 0.4430 0.5635
5.500 0.7754 0.03496 0.02418 -0.0648 0.4333 0.5707
5.750 0.8046 0.03516 0.02434 -0.0652 0.4254 0.5809
6.000 0.8214 0.03573 0.02506 -0.0636 0.4171 0.5878
6.250 0.8437 0.03618 0.02555 -0.0631 0.4086 0.5978
6.500 0.8697 0.03644 0.02582 -0.0626 0.4018 0.6067
6.750 0.8813 0.03734 0.02691 -0.0609 0.3928 0.6160
7.000 0.9091 0.03751 0.02706 -0.0606 0.3859 0.6262
7.250 0.9203 0.03847 0.02819 -0.0589 0.3779 0.6361
7.500 0.9383 0.03907 0.02889 -0.0577 0.3704 0.6465
7.750 0.9667 0.03932 0.02910 -0.0576 0.3640 0.6598
8.000 0.9661 0.04069 0.03075 -0.0546 0.3560 0.6684
8.250 0.9905 0.04106 0.03114 -0.0541 0.3494 0.6821
8.500 1.0015 0.04195 0.03216 -0.0521 0.3430 0.6939
8.750 0.9995 0.04335 0.03376 -0.0491 0.3358 0.7054
9.000 1.0267 0.04348 0.03389 -0.0487 0.3299 0.7217
9.250 1.0236 0.04513 0.03574 -0.0458 0.3237 0.7347
9.500 1.0167 0.04708 0.03791 -0.0430 0.3170 0.7483
9.750 1.0437 0.04696 0.03780 -0.0422 0.3116 0.7691
10.000 1.0293 0.04950 0.04058 -0.0393 0.3056 0.7853
10.250 1.0017 0.05333 0.04467 -0.0369 0.2989 0.8011
10.500 1.0246 0.05297 0.04438 -0.0351 0.2942 0.8337
10.750 0.9984 0.05668 0.04832 -0.0329 0.2885 0.8659
11.000 0.9210 0.06745 0.05940 -0.0344 0.2783 0.8783
11.250 0.9702 0.06441 0.05629 -0.0333 0.2754 1.0000
11.500 0.8497 0.08372 0.07593 -0.0402 0.2596 1.0000
11.750 0.8964 0.08141 0.07352 -0.0397 0.2575 1.0000
12.250 0.8170 0.10254 0.09482 -0.0492 0.2365 1.0000
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Polar data table (+)
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