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DAE-31 AIRFOIL (dae31-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: DAE-31 AIRFOIL (dae31-il)
Reynolds number: 1,000,000
Max Cl/Cd: 151.47 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dae31-il-1000000-n5.txt
Download as CSV file: xf-dae31-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAE-31 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0025   0.09468   0.09189  -0.0966   0.7825   0.0098
  -9.500   0.0028   0.09130   0.08852  -0.0980   0.7804   0.0093
  -7.000  -0.0486   0.01754   0.01346  -0.1509   0.7489   0.0110
  -6.750  -0.0228   0.01579   0.01141  -0.1517   0.7466   0.0111
  -6.500   0.0042   0.01472   0.01013  -0.1521   0.7439   0.0112
  -6.250   0.0308   0.01347   0.00865  -0.1525   0.7411   0.0115
  -6.000   0.0584   0.01280   0.00785  -0.1528   0.7384   0.0117
  -5.750   0.0862   0.01230   0.00724  -0.1529   0.7356   0.0118
  -5.500   0.1142   0.01190   0.00675  -0.1531   0.7328   0.0120
  -5.250   0.1425   0.01146   0.00624  -0.1532   0.7301   0.0122
  -5.000   0.1708   0.01107   0.00577  -0.1534   0.7269   0.0124
  -4.750   0.1991   0.01068   0.00530  -0.1535   0.7237   0.0126
  -4.500   0.2274   0.01032   0.00486  -0.1536   0.7204   0.0128
  -4.250   0.2557   0.01000   0.00444  -0.1537   0.7173   0.0130
  -4.000   0.2842   0.00970   0.00407  -0.1538   0.7144   0.0133
  -3.750   0.3129   0.00941   0.00374  -0.1539   0.7112   0.0135
  -3.500   0.3415   0.00920   0.00347  -0.1540   0.7076   0.0138
  -3.250   0.3699   0.00892   0.00316  -0.1541   0.7038   0.0143
  -3.000   0.3982   0.00876   0.00295  -0.1541   0.7001   0.0148
  -2.750   0.4270   0.00858   0.00276  -0.1542   0.6965   0.0152
  -2.500   0.4556   0.00842   0.00257  -0.1543   0.6923   0.0157
  -2.250   0.4842   0.00828   0.00239  -0.1544   0.6877   0.0162
  -2.000   0.5125   0.00816   0.00222  -0.1544   0.6831   0.0167
  -1.750   0.5412   0.00801   0.00207  -0.1545   0.6788   0.0175
  -1.500   0.5697   0.00791   0.00196  -0.1545   0.6737   0.0183
  -1.250   0.5980   0.00784   0.00185  -0.1546   0.6683   0.0193
  -1.000   0.6264   0.00776   0.00176  -0.1546   0.6632   0.0206
  -0.750   0.6549   0.00770   0.00169  -0.1547   0.6574   0.0224
  -0.500   0.6830   0.00766   0.00163  -0.1546   0.6510   0.0248
  -0.250   0.7113   0.00761   0.00158  -0.1547   0.6450   0.0281
   0.000   0.7393   0.00758   0.00155  -0.1547   0.6375   0.0334
   0.250   0.7672   0.00756   0.00153  -0.1547   0.6302   0.0437
   0.500   0.7950   0.00754   0.00153  -0.1546   0.6214   0.0591
   0.750   0.8225   0.00752   0.00155  -0.1546   0.6126   0.0822
   1.000   0.8499   0.00750   0.00158  -0.1545   0.6023   0.1198
   1.250   0.8771   0.00747   0.00163  -0.1545   0.5923   0.1651
   1.500   0.9038   0.00744   0.00171  -0.1543   0.5817   0.2404
   1.750   0.9307   0.00738   0.00181  -0.1543   0.5705   0.3289
   2.000   0.9572   0.00738   0.00192  -0.1541   0.5597   0.4004
   2.250   0.9830   0.00739   0.00206  -0.1538   0.5476   0.4888
   2.500   1.0080   0.00722   0.00223  -0.1535   0.5349   0.6593
   3.000   1.0603   0.00700   0.00250  -0.1529   0.5085   1.0000
   3.250   1.0856   0.00722   0.00263  -0.1524   0.4949   1.0000
   3.750   1.1359   0.00766   0.00292  -0.1515   0.4678   1.0000
   4.000   1.1607   0.00788   0.00307  -0.1511   0.4546   1.0000
   4.250   1.1850   0.00813   0.00325  -0.1505   0.4413   1.0000
   4.500   1.2087   0.00840   0.00343  -0.1498   0.4273   1.0000
   4.750   1.2323   0.00866   0.00363  -0.1491   0.4136   1.0000
   5.000   1.2557   0.00892   0.00383  -0.1484   0.3998   1.0000
   5.250   1.2783   0.00921   0.00405  -0.1476   0.3857   1.0000
   5.500   1.3001   0.00953   0.00429  -0.1466   0.3713   1.0000
   5.750   1.3210   0.00987   0.00455  -0.1455   0.3561   1.0000
   6.000   1.3410   0.01022   0.00483  -0.1442   0.3408   1.0000
   6.250   1.3603   0.01059   0.00513  -0.1428   0.3266   1.0000
   6.500   1.3787   0.01096   0.00543  -0.1413   0.3127   1.0000
   6.750   1.3946   0.01131   0.00573  -0.1393   0.2998   1.0000
   7.000   1.4089   0.01170   0.00608  -0.1369   0.2879   1.0000
   7.250   1.4221   0.01216   0.00649  -0.1345   0.2752   1.0000
   7.750   1.4502   0.01314   0.00737  -0.1303   0.2520   1.0000
   8.000   1.4643   0.01368   0.00787  -0.1283   0.2411   1.0000
   8.250   1.4775   0.01430   0.00844  -0.1263   0.2295   1.0000
   8.500   1.4911   0.01492   0.00902  -0.1244   0.2181   1.0000
   8.750   1.5048   0.01557   0.00963  -0.1226   0.2070   1.0000
   9.000   1.5182   0.01627   0.01029  -0.1208   0.1966   1.0000
   9.250   1.5309   0.01702   0.01101  -0.1190   0.1865   1.0000
   9.500   1.5452   0.01771   0.01167  -0.1174   0.1776   1.0000
   9.750   1.5573   0.01854   0.01246  -0.1156   0.1670   1.0000
  10.000   1.5691   0.01941   0.01329  -0.1138   0.1574   1.0000
  10.250   1.5804   0.02033   0.01418  -0.1121   0.1470   1.0000
  10.500   1.5911   0.02131   0.01511  -0.1103   0.1360   1.0000
  10.750   1.6013   0.02235   0.01611  -0.1085   0.1256   1.0000
  11.000   1.6113   0.02342   0.01714  -0.1067   0.1156   1.0000
  11.250   1.6211   0.02453   0.01822  -0.1050   0.1075   1.0000
  11.500   1.6316   0.02561   0.01928  -0.1035   0.1005   1.0000
  11.750   1.6415   0.02676   0.02042  -0.1019   0.0934   1.0000
  12.000   1.6515   0.02792   0.02157  -0.1004   0.0874   1.0000
  12.250   1.6595   0.02926   0.02289  -0.0988   0.0808   1.0000
  12.500   1.6678   0.03062   0.02423  -0.0972   0.0737   1.0000
  12.750   1.6769   0.03194   0.02556  -0.0959   0.0684   1.0000
  13.000   1.6840   0.03347   0.02708  -0.0944   0.0621   1.0000
  13.250   1.6912   0.03502   0.02863  -0.0930   0.0569   1.0000
  13.500   1.6984   0.03664   0.03025  -0.0917   0.0523   1.0000
  13.750   1.7058   0.03827   0.03190  -0.0905   0.0478   1.0000
  14.000   1.7122   0.04002   0.03366  -0.0893   0.0437   1.0000
  14.250   1.7180   0.04188   0.03554  -0.0882   0.0397   1.0000
  14.500   1.7235   0.04382   0.03750  -0.0871   0.0363   1.0000
  14.750   1.7289   0.04582   0.03953  -0.0862   0.0332   1.0000
  15.000   1.7339   0.04788   0.04162  -0.0853   0.0302   1.0000
  15.250   1.7380   0.05011   0.04389  -0.0844   0.0278   1.0000
  15.500   1.7427   0.05231   0.04613  -0.0837   0.0256   1.0000
  15.750   1.7461   0.05472   0.04859  -0.0830   0.0235   1.0000
  16.000   1.7487   0.05727   0.05118  -0.0824   0.0216   1.0000
  16.250   1.7527   0.05970   0.05367  -0.0820   0.0202   1.0000
  16.500   1.7539   0.06254   0.05655  -0.0816   0.0186   1.0000
  16.750   1.7566   0.06522   0.05930  -0.0813   0.0174   1.0000
  17.000   1.7570   0.06828   0.06241  -0.0811   0.0160   1.0000
  17.250   1.7583   0.07127   0.06548  -0.0810   0.0150   1.0000
  17.500   1.7579   0.07453   0.06880  -0.0811   0.0139   1.0000
  17.750   1.7580   0.07779   0.07214  -0.0812   0.0129   1.0000
  18.000   1.7561   0.08140   0.07582  -0.0815   0.0119   1.0000
  18.250   1.7540   0.08512   0.07961  -0.0820   0.0111   1.0000
  18.500   1.7523   0.08879   0.08337  -0.0825   0.0103   1.0000
  18.750   1.7487   0.09282   0.08747  -0.0832   0.0096   1.0000
  19.000   1.7452   0.09691   0.09165  -0.0841   0.0092   1.0000
  19.250   1.7415   0.10109   0.09592  -0.0851   0.0087   1.0000
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