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NREL's S826 Airfoil (s826-nr) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NREL's S826 Airfoil (s826-nr)
Reynolds number: 200,000
Max Cl/Cd: 81.38 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s826-nr-200000-n5.txt
Download as CSV file: xf-s826-nr-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S826 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2412   0.10627   0.10293  -0.0549   0.9898   0.0129
 -10.500  -0.3664   0.11419   0.11070  -0.0416   1.0000   0.0136
 -10.250  -0.3637   0.11095   0.10749  -0.0424   0.9995   0.0132
 -10.000  -0.3540   0.10611   0.10265  -0.0464   0.9974   0.0126
  -9.500  -0.3537   0.08944   0.08602  -0.0583   0.9922   0.0102
  -9.250  -0.3495   0.08332   0.07991  -0.0636   0.9888   0.0101
  -9.000  -0.3471   0.07588   0.07246  -0.0709   0.9854   0.0099
  -8.750  -0.3528   0.06830   0.06483  -0.0785   0.9802   0.0096
  -8.250  -0.3719   0.05585   0.05215  -0.0918   0.9628   0.0094
  -8.000  -0.3705   0.04936   0.04541  -0.1005   0.9519   0.0091
  -7.750  -0.3560   0.04245   0.03806  -0.1090   0.9453   0.0089
  -7.500  -0.3464   0.03759   0.03280  -0.1115   0.9350   0.0087
  -7.250  -0.3262   0.03277   0.02747  -0.1144   0.9279   0.0085
  -7.000  -0.3004   0.02891   0.02311  -0.1167   0.9219   0.0085
  -6.750  -0.2680   0.02595   0.01973  -0.1191   0.9188   0.0086
  -6.500  -0.2466   0.02409   0.01762  -0.1186   0.9098   0.0088
  -6.250  -0.2146   0.02231   0.01560  -0.1200   0.9060   0.0091
  -6.000  -0.1903   0.02096   0.01408  -0.1198   0.8972   0.0096
  -5.500  -0.1276   0.01849   0.01139  -0.1225   0.8843   0.0109
  -5.250  -0.0908   0.01753   0.01035  -0.1250   0.8794   0.0128
  -5.000  -0.0562   0.01671   0.00948  -0.1271   0.8722   0.0163
  -4.750  -0.0158   0.01569   0.00837  -0.1305   0.8662   0.0220
  -4.500   0.0250   0.01486   0.00748  -0.1338   0.8592   0.0328
  -4.250   0.0691   0.01397   0.00657  -0.1379   0.8518   0.0536
  -4.000   0.1154   0.01308   0.00578  -0.1426   0.8437   0.1079
  -3.750   0.1700   0.01157   0.00509  -0.1502   0.8361   0.3866
  -3.500   0.2109   0.01166   0.00503  -0.1527   0.8247   0.4276
  -3.250   0.2505   0.01175   0.00497  -0.1549   0.8124   0.4453
  -3.000   0.2875   0.01184   0.00490  -0.1567   0.7992   0.4566
  -2.750   0.3214   0.01197   0.00491  -0.1577   0.7853   0.4656
  -2.500   0.3546   0.01206   0.00478  -0.1588   0.7714   0.4738
  -2.250   0.3849   0.01213   0.00476  -0.1592   0.7581   0.4778
  -1.750   0.4442   0.01218   0.00453  -0.1601   0.7338   0.4827
  -1.500   0.4733   0.01220   0.00442  -0.1604   0.7231   0.4853
  -1.250   0.5027   0.01225   0.00431  -0.1608   0.7133   0.4883
  -1.000   0.5307   0.01229   0.00430  -0.1609   0.7035   0.4903
  -0.750   0.5586   0.01235   0.00430  -0.1610   0.6943   0.4924
  -0.250   0.6148   0.01248   0.00430  -0.1613   0.6776   0.4973
   0.000   0.6434   0.01257   0.00431  -0.1615   0.6708   0.5003
   0.250   0.6715   0.01264   0.00433  -0.1617   0.6637   0.5036
   0.500   0.6993   0.01273   0.00441  -0.1618   0.6573   0.5059
   0.750   0.7269   0.01281   0.00450  -0.1619   0.6508   0.5085
   1.000   0.7548   0.01291   0.00458  -0.1620   0.6447   0.5113
   1.250   0.7829   0.01301   0.00466  -0.1622   0.6395   0.5144
   1.500   0.8108   0.01311   0.00477  -0.1623   0.6339   0.5179
   1.750   0.8386   0.01322   0.00490  -0.1624   0.6289   0.5208
   2.000   0.8664   0.01334   0.00504  -0.1625   0.6241   0.5238
   2.250   0.8938   0.01345   0.00523  -0.1626   0.6188   0.5273
   2.500   0.9218   0.01358   0.00538  -0.1627   0.6144   0.5310
   2.750   0.9499   0.01373   0.00553  -0.1629   0.6101   0.5345
   3.000   0.9766   0.01384   0.00575  -0.1628   0.6045   0.5375
   3.250   1.0037   0.01398   0.00595  -0.1627   0.5988   0.5411
   3.500   1.0304   0.01412   0.00614  -0.1626   0.5925   0.5455
   3.750   1.0563   0.01426   0.00633  -0.1623   0.5847   0.5498
   4.000   1.0814   0.01438   0.00655  -0.1618   0.5758   0.5535
   4.250   1.1066   0.01454   0.00672  -0.1613   0.5665   0.5578
   4.500   1.1310   0.01466   0.00694  -0.1607   0.5565   0.5624
   4.750   1.1558   0.01481   0.00718  -0.1602   0.5474   0.5664
   5.000   1.1801   0.01497   0.00741  -0.1595   0.5375   0.5708
   5.250   1.2039   0.01512   0.00767  -0.1588   0.5267   0.5759
   5.500   1.2275   0.01529   0.00793  -0.1581   0.5158   0.5810
   5.750   1.2504   0.01547   0.00823  -0.1571   0.5036   0.5862
   6.000   1.2723   0.01568   0.00851  -0.1560   0.4888   0.5924
   6.250   1.2931   0.01589   0.00882  -0.1547   0.4704   0.5978
   6.500   1.3120   0.01615   0.00913  -0.1531   0.4457   0.6038
   6.750   1.3278   0.01654   0.00947  -0.1509   0.4076   0.6098
   7.000   1.3351   0.01728   0.00999  -0.1472   0.3528   0.6153
   7.250   1.3386   0.01826   0.01073  -0.1430   0.3042   0.6217
   7.500   1.3428   0.01936   0.01163  -0.1392   0.2600   0.6279
   7.750   1.3492   0.02045   0.01258  -0.1359   0.2223   0.6354
   8.000   1.3565   0.02154   0.01357  -0.1328   0.1911   0.6432
   8.250   1.3644   0.02263   0.01460  -0.1299   0.1646   0.6522
   8.500   1.3723   0.02373   0.01569  -0.1271   0.1429   0.6613
   8.750   1.3804   0.02485   0.01680  -0.1245   0.1232   0.6716
   9.250   1.3952   0.02726   0.01923  -0.1193   0.0927   0.6959
   9.500   1.4024   0.02852   0.02055  -0.1168   0.0807   0.7111
   9.750   1.4093   0.02984   0.02195  -0.1145   0.0701   0.7293
  10.000   1.4154   0.03123   0.02343  -0.1121   0.0608   0.7523
  10.250   1.4201   0.03273   0.02502  -0.1098   0.0528   0.7840
  10.500   1.4229   0.03408   0.02657  -0.1070   0.0459   0.8491
  10.750   1.4243   0.03556   0.02817  -0.1043   0.0406   1.0000
  11.000   1.4288   0.03753   0.03016  -0.1027   0.0350   1.0000
  11.250   1.4350   0.03941   0.03214  -0.1013   0.0303   1.0000
  11.500   1.4376   0.04173   0.03447  -0.0999   0.0261   1.0000
  11.750   1.4428   0.04385   0.03670  -0.0987   0.0223   1.0000
  12.000   1.4446   0.04641   0.03930  -0.0976   0.0191   1.0000
  12.250   1.4480   0.04888   0.04188  -0.0966   0.0163   1.0000
  12.500   1.4484   0.05177   0.04484  -0.0958   0.0143   1.0000
  12.750   1.4511   0.05447   0.04767  -0.0951   0.0123   1.0000
  13.000   1.4509   0.05760   0.05089  -0.0946   0.0109   1.0000
  13.250   1.4519   0.06070   0.05413  -0.0942   0.0097   1.0000
  13.500   1.4523   0.06393   0.05750  -0.0939   0.0087   1.0000
  13.750   1.4509   0.06748   0.06116  -0.0939   0.0079   1.0000
  14.000   1.4495   0.07115   0.06498  -0.0940   0.0073   1.0000
  14.250   1.4490   0.07477   0.06876  -0.0942   0.0066   1.0000
  14.500   1.4481   0.07851   0.07263  -0.0946   0.0060   1.0000
  14.750   1.4449   0.08270   0.07695  -0.0953   0.0056   1.0000
  15.000   1.4390   0.08740   0.08180  -0.0963   0.0054   1.0000
  15.250   1.4351   0.09192   0.08652  -0.0972   0.0050   1.0000
  15.500   1.4294   0.09683   0.09161  -0.0985   0.0048   1.0000
  15.750   1.4234   0.10191   0.09687  -0.1001   0.0046   1.0000
  16.000   1.4170   0.10718   0.10231  -0.1019   0.0045   1.0000
  16.250   1.4101   0.11264   0.10794  -0.1040   0.0043   1.0000
  16.500   1.4030   0.11825   0.11372  -0.1063   0.0042   1.0000
  16.750   1.3954   0.12411   0.11974  -0.1090   0.0041   1.0000
  17.000   1.3877   0.13014   0.12596  -0.1120   0.0040   1.0000
  17.250   1.3796   0.13639   0.13237  -0.1153   0.0040   1.0000
  17.500   1.3709   0.14296   0.13910  -0.1191   0.0039   1.0000
  17.750   1.3630   0.14952   0.14581  -0.1229   0.0039   1.0000
  18.000   1.3538   0.15650   0.15295  -0.1273   0.0038   1.0000
  18.250   1.3454   0.16348   0.16008  -0.1318   0.0038   1.0000
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