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NREL's S808 Airfoil (s808-nr) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
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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