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NREL's S833 Airfoil (s833-nr) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
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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