NREL's S833 Airfoil (s833-nr) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S833 Airfoil (s833-nr) Reynolds number: 50,000 Max Cl/Cd: 27.55 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s833-nr-50000.txt Download as CSV file: xf-s833-nr-50000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S833 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4634 0.10721 0.09830 -0.0143 1.0000 0.4112
-8.250 -0.4594 0.10368 0.09474 -0.0140 1.0000 0.4074
-8.000 -0.4719 0.09999 0.09105 -0.0131 1.0000 0.4046
-7.750 -0.4889 0.09626 0.08733 -0.0120 1.0000 0.4038
-7.500 -0.5071 0.09258 0.08366 -0.0106 1.0000 0.4046
-7.250 -0.5305 0.08874 0.07985 -0.0089 1.0000 0.4070
-7.000 -0.5741 0.08371 0.07489 -0.0065 1.0000 0.4101
-6.750 -0.5581 0.08296 0.07411 -0.0046 1.0000 0.4183
-6.500 -0.5834 0.07948 0.07066 -0.0019 1.0000 0.4239
-6.250 -0.6743 0.07155 0.06291 0.0034 1.0000 0.4270
-6.000 -0.6334 0.07305 0.06431 0.0049 1.0000 0.4364
-5.750 -0.7491 0.05886 0.05020 0.0054 1.0000 0.4475
-5.500 -0.6900 0.06471 0.05602 0.0101 1.0000 0.4534
-5.250 -0.7267 0.05761 0.04887 0.0099 1.0000 0.4665
-5.000 -0.7359 0.05349 0.04463 0.0099 1.0000 0.4809
-4.750 -0.7040 0.05648 0.04765 0.0143 1.0000 0.4866
-4.500 -0.7059 0.05339 0.04446 0.0147 1.0000 0.5001
-4.250 -0.7017 0.05096 0.04193 0.0148 1.0000 0.5145
-4.000 -0.6779 0.05313 0.04412 0.0193 1.0000 0.5207
-3.750 -0.6709 0.05130 0.04221 0.0199 1.0000 0.5341
-3.500 -0.6613 0.04971 0.04054 0.0203 1.0000 0.5485
-3.250 -0.6427 0.05111 0.04197 0.0244 1.0000 0.5556
-3.000 -0.6317 0.05002 0.04080 0.0254 1.0000 0.5687
-2.750 -0.6197 0.04896 0.03967 0.0261 1.0000 0.5829
-2.500 -0.6044 0.04957 0.04029 0.0293 1.0000 0.5923
-2.250 -0.5912 0.04917 0.03986 0.0310 1.0000 0.6043
-2.000 -0.5783 0.04848 0.03911 0.0320 1.0000 0.6182
-1.750 -0.5646 0.04778 0.03836 0.0327 1.0000 0.6327
-1.500 -0.5510 0.04816 0.03874 0.0358 1.0000 0.6424
-1.250 -0.5378 0.04788 0.03844 0.0376 1.0000 0.6553
-1.000 -0.5243 0.04737 0.03789 0.0386 1.0000 0.6695
-0.750 -0.5104 0.04690 0.03737 0.0394 1.0000 0.6844
-0.500 -0.4979 0.04691 0.03738 0.0419 1.0000 0.6965
-0.250 -0.4852 0.04672 0.03718 0.0439 1.0000 0.7092
0.000 -0.4723 0.04640 0.03684 0.0453 1.0000 0.7235
0.250 -0.4592 0.04606 0.03648 0.0466 1.0000 0.7384
0.500 -0.4459 0.04573 0.03614 0.0476 1.0000 0.7535
0.750 -0.4333 0.04550 0.03589 0.0491 1.0000 0.7685
1.000 -0.4223 0.04532 0.03572 0.0514 1.0000 0.7821
1.250 -0.4105 0.04507 0.03547 0.0531 1.0000 0.7965
1.500 -0.3987 0.04480 0.03520 0.0547 1.0000 0.8116
1.750 -0.3870 0.04453 0.03493 0.0562 1.0000 0.8271
2.000 -0.3752 0.04428 0.03468 0.0576 1.0000 0.8429
2.250 -0.3633 0.04405 0.03445 0.0589 1.0000 0.8589
2.500 -0.3504 0.04386 0.03427 0.0599 1.0000 0.8752
2.750 -0.3373 0.04371 0.03413 0.0608 1.0000 0.8920
3.000 -0.3218 0.04368 0.03412 0.0612 1.0000 0.9089
3.250 -0.3021 0.04387 0.03433 0.0605 1.0000 0.9259
3.500 -0.2722 0.04452 0.03502 0.0577 1.0000 0.9416
3.750 -0.2291 0.04582 0.03638 0.0520 1.0000 0.9558
4.000 -0.1729 0.04784 0.03849 0.0433 0.9980 0.9679
4.250 -0.0777 0.05209 0.04285 0.0269 0.9800 0.9773
4.500 0.1034 0.05572 0.04663 -0.0008 0.8807 0.9846
4.750 0.1937 0.05706 0.04810 -0.0135 0.8528 0.9962
5.000 0.2209 0.05722 0.04835 -0.0157 0.8316 1.0000
5.250 0.2365 0.05718 0.04836 -0.0156 0.8129 1.0000
5.500 0.2537 0.05712 0.04835 -0.0154 0.7944 1.0000
5.750 0.2726 0.05703 0.04832 -0.0153 0.7760 1.0000
6.000 0.2909 0.05693 0.04827 -0.0149 0.7581 1.0000
6.250 0.3111 0.05676 0.04816 -0.0146 0.7404 1.0000
6.500 0.3355 0.05650 0.04799 -0.0145 0.7225 1.0000
6.750 0.3435 0.05656 0.04810 -0.0128 0.7029 1.0000
7.000 0.3639 0.05672 0.04835 -0.0128 0.6824 1.0000
7.250 0.3983 0.05665 0.04840 -0.0140 0.6619 1.0000
7.500 0.4438 0.05605 0.04796 -0.0159 0.6420 1.0000
7.750 0.4989 0.05468 0.04678 -0.0180 0.6229 1.0000
8.000 0.5201 0.05500 0.04724 -0.0178 0.5989 1.0000
8.250 0.5706 0.05325 0.04569 -0.0187 0.5775 1.0000
8.500 0.6462 0.04868 0.04140 -0.0196 0.5583 1.0000
8.750 0.7687 0.03978 0.03285 -0.0222 0.5342 1.0000
9.000 0.8694 0.03432 0.02736 -0.0257 0.4829 1.0000
9.250 0.9118 0.03362 0.02637 -0.0259 0.4304 1.0000
9.500 0.9404 0.03414 0.02653 -0.0253 0.3816 1.0000
9.750 0.9577 0.03534 0.02748 -0.0239 0.3402 1.0000
10.000 0.9821 0.03674 0.02848 -0.0235 0.2996 1.0000
10.250 1.0001 0.03844 0.02995 -0.0226 0.2659 1.0000
10.500 1.0137 0.04028 0.03173 -0.0213 0.2381 1.0000
10.750 1.0329 0.04238 0.03373 -0.0208 0.2128 1.0000
11.000 1.0515 0.04456 0.03587 -0.0202 0.1914 1.0000
11.250 1.0856 0.04710 0.03812 -0.0217 0.1699 1.0000
11.500 1.0883 0.04944 0.04080 -0.0193 0.1588 1.0000
11.750 1.0991 0.05234 0.04388 -0.0181 0.1480 1.0000
12.000 1.1187 0.05526 0.04679 -0.0181 0.1374 1.0000
12.250 1.1107 0.05829 0.05023 -0.0151 0.1325 1.0000
12.500 1.1340 0.06155 0.05340 -0.0156 0.1239 1.0000
12.750 1.1144 0.06502 0.05734 -0.0121 0.1222 1.0000
13.000 1.0929 0.06892 0.06162 -0.0092 0.1208 1.0000
13.250 1.0688 0.07328 0.06631 -0.0070 0.1201 1.0000
13.500 1.0398 0.07828 0.07161 -0.0055 0.1200 1.0000
13.750 1.0068 0.08418 0.07778 -0.0052 0.1208 1.0000
14.000 0.9710 0.09108 0.08492 -0.0063 0.1220 1.0000
14.250 0.9371 0.09888 0.09288 -0.0088 0.1233 1.0000
14.500 0.9065 0.10748 0.10159 -0.0123 0.1245 1.0000
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Polar data table (+)
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