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DAE-31 AIRFOIL (dae31-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: DAE-31 AIRFOIL (dae31-il)
Reynolds number: 1,000,000
Max Cl/Cd: 173.71 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dae31-il-1000000.txt
Download as CSV file: xf-dae31-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.0010   0.09466   0.09206  -0.0995   0.8131   0.0138
  -9.500   0.0069   0.09186   0.08925  -0.1009   0.8107   0.0138
  -9.250   0.0120   0.08892   0.08630  -0.1023   0.8080   0.0138
  -9.000   0.0196   0.08599   0.08335  -0.1032   0.8049   0.0139
  -8.750   0.0320   0.08391   0.08128  -0.1036   0.8030   0.0141
  -8.500   0.0417   0.08174   0.07913  -0.1043   0.8010   0.0142
  -8.250   0.0500   0.07946   0.07686  -0.1052   0.7984   0.0142
  -8.000   0.0583   0.07722   0.07463  -0.1060   0.7957   0.0144
  -7.750   0.0664   0.07505   0.07246  -0.1068   0.7931   0.0146
  -7.500   0.0737   0.07284   0.07024  -0.1075   0.7902   0.0150
  -7.250   0.0801   0.07059   0.06798  -0.1082   0.7868   0.0151
  -7.000   0.0851   0.06826   0.06568  -0.1088   0.7841   0.0154
  -6.750   0.0864   0.06580   0.06324  -0.1091   0.7811   0.0160
  -6.500   0.0800   0.06068   0.05815  -0.1139   0.7770   0.0166
  -6.250   0.0881   0.05746   0.05493  -0.1161   0.7741   0.0168
  -6.000   0.1023   0.05542   0.05287  -0.1179   0.7710   0.0169
  -5.750   0.1184   0.05347   0.05089  -0.1198   0.7676   0.0172
  -5.500   0.1356   0.05099   0.04841  -0.1226   0.7652   0.0175
  -5.250   0.1548   0.04797   0.04539  -0.1264   0.7621   0.0181
  -4.750   0.2068   0.01701   0.01281  -0.1535   0.7558   0.0167
  -4.500   0.2330   0.01424   0.00955  -0.1543   0.7530   0.0168
  -4.250   0.2605   0.01321   0.00835  -0.1546   0.7500   0.0172
  -4.000   0.2886   0.01263   0.00770  -0.1548   0.7477   0.0175
  -3.750   0.3169   0.01190   0.00685  -0.1549   0.7449   0.0178
  -3.500   0.3452   0.01121   0.00603  -0.1551   0.7420   0.0181
  -3.250   0.3736   0.01062   0.00531  -0.1551   0.7390   0.0184
  -3.000   0.4020   0.01013   0.00470  -0.1552   0.7359   0.0188
  -2.750   0.4305   0.00977   0.00424  -0.1552   0.7326   0.0192
  -2.500   0.4590   0.00937   0.00379  -0.1553   0.7296   0.0198
  -2.250   0.4874   0.00896   0.00337  -0.1554   0.7261   0.0205
  -2.000   0.5159   0.00870   0.00310  -0.1554   0.7225   0.0213
  -1.750   0.5445   0.00850   0.00284  -0.1555   0.7189   0.0222
  -1.500   0.5730   0.00827   0.00257  -0.1555   0.7151   0.0231
  -1.250   0.6016   0.00806   0.00238  -0.1556   0.7114   0.0244
  -1.000   0.6303   0.00792   0.00222  -0.1557   0.7072   0.0260
  -0.750   0.6588   0.00776   0.00204  -0.1557   0.7030   0.0282
  -0.500   0.6872   0.00767   0.00193  -0.1558   0.6986   0.0315
  -0.250   0.7158   0.00754   0.00183  -0.1558   0.6942   0.0366
   0.000   0.7443   0.00742   0.00174  -0.1559   0.6892   0.0484
   0.250   0.7724   0.00730   0.00169  -0.1559   0.6840   0.0793
   0.500   0.8006   0.00713   0.00168  -0.1560   0.6788   0.1359
   0.750   0.8287   0.00697   0.00170  -0.1561   0.6727   0.2105
   1.000   0.8561   0.00683   0.00173  -0.1561   0.6665   0.3053
   1.250   0.8840   0.00665   0.00180  -0.1563   0.6602   0.4111
   1.500   0.9108   0.00642   0.00189  -0.1562   0.6532   0.5632
   1.750   0.9383   0.00567   0.00199  -0.1561   0.6464   1.0000
   2.000   0.9662   0.00574   0.00202  -0.1561   0.6385   1.0000
   2.250   0.9935   0.00585   0.00205  -0.1559   0.6303   1.0000
   2.500   1.0209   0.00594   0.00210  -0.1558   0.6209   1.0000
   2.750   1.0480   0.00606   0.00216  -0.1557   0.6112   1.0000
   3.000   1.0745   0.00621   0.00223  -0.1554   0.6002   1.0000
   3.250   1.1013   0.00634   0.00231  -0.1552   0.5891   1.0000
   3.500   1.1275   0.00650   0.00241  -0.1549   0.5776   1.0000
   3.750   1.1531   0.00669   0.00253  -0.1545   0.5651   1.0000
   4.000   1.1790   0.00686   0.00265  -0.1542   0.5523   1.0000
   4.250   1.2045   0.00705   0.00279  -0.1538   0.5397   1.0000
   4.500   1.2294   0.00727   0.00294  -0.1534   0.5267   1.0000
   4.750   1.2538   0.00751   0.00311  -0.1528   0.5134   1.0000
   5.000   1.2781   0.00774   0.00329  -0.1522   0.4997   1.0000
   5.250   1.3023   0.00798   0.00347  -0.1516   0.4860   1.0000
   5.500   1.3257   0.00824   0.00367  -0.1509   0.4719   1.0000
   5.750   1.3484   0.00852   0.00389  -0.1501   0.4574   1.0000
   6.000   1.3705   0.00883   0.00413  -0.1492   0.4427   1.0000
   6.250   1.3919   0.00915   0.00438  -0.1482   0.4281   1.0000
   6.500   1.4128   0.00947   0.00464  -0.1470   0.4132   1.0000
   6.750   1.4333   0.00979   0.00491  -0.1459   0.3987   1.0000
   7.000   1.4527   0.01014   0.00521  -0.1445   0.3842   1.0000
   7.250   1.4707   0.01051   0.00552  -0.1429   0.3697   1.0000
   7.500   1.4854   0.01090   0.00586  -0.1406   0.3555   1.0000
   7.750   1.4977   0.01134   0.00623  -0.1379   0.3417   1.0000
   8.000   1.5092   0.01184   0.00668  -0.1353   0.3276   1.0000
   8.250   1.5219   0.01235   0.00714  -0.1329   0.3137   1.0000
   8.500   1.5344   0.01291   0.00765  -0.1306   0.2997   1.0000
   8.750   1.5467   0.01352   0.00822  -0.1284   0.2861   1.0000
   9.000   1.5584   0.01421   0.00885  -0.1262   0.2719   1.0000
   9.250   1.5703   0.01492   0.00951  -0.1241   0.2591   1.0000
   9.500   1.5817   0.01570   0.01023  -0.1220   0.2458   1.0000
  10.000   1.6038   0.01737   0.01180  -0.1180   0.2186   1.0000
  10.250   1.6145   0.01827   0.01265  -0.1160   0.2051   1.0000
  10.500   1.6241   0.01926   0.01357  -0.1140   0.1912   1.0000
  10.750   1.6347   0.02022   0.01449  -0.1121   0.1793   1.0000
  11.000   1.6442   0.02127   0.01549  -0.1102   0.1676   1.0000
  11.250   1.6540   0.02233   0.01651  -0.1084   0.1577   1.0000
  11.500   1.6644   0.02337   0.01753  -0.1067   0.1485   1.0000
  11.750   1.6746   0.02444   0.01858  -0.1050   0.1398   1.0000
  12.000   1.6837   0.02561   0.01973  -0.1033   0.1312   1.0000
  12.250   1.6917   0.02688   0.02097  -0.1016   0.1225   1.0000
  12.500   1.7013   0.02807   0.02215  -0.1001   0.1146   1.0000
  12.750   1.7090   0.02943   0.02350  -0.0984   0.1073   1.0000
  13.000   1.7161   0.03088   0.02492  -0.0968   0.0996   1.0000
  13.250   1.7245   0.03226   0.02631  -0.0954   0.0935   1.0000
  13.500   1.7326   0.03371   0.02776  -0.0941   0.0879   1.0000
  13.750   1.7388   0.03535   0.02941  -0.0927   0.0820   1.0000
  14.000   1.7466   0.03691   0.03097  -0.0914   0.0764   1.0000
  14.250   1.7521   0.03870   0.03277  -0.0901   0.0711   1.0000
  14.500   1.7574   0.04056   0.03463  -0.0889   0.0657   1.0000
  14.750   1.7628   0.04246   0.03656  -0.0878   0.0607   1.0000
  15.000   1.7676   0.04447   0.03857  -0.0867   0.0557   1.0000
  15.250   1.7706   0.04671   0.04083  -0.0857   0.0512   1.0000
  15.500   1.7734   0.04902   0.04315  -0.0847   0.0468   1.0000
  15.750   1.7766   0.05135   0.04551  -0.0839   0.0428   1.0000
  16.000   1.7784   0.05390   0.04809  -0.0831   0.0391   1.0000
  16.250   1.7800   0.05653   0.05075  -0.0825   0.0360   1.0000
  16.500   1.7803   0.05935   0.05361  -0.0819   0.0328   1.0000
  16.750   1.7813   0.06219   0.05650  -0.0815   0.0302   1.0000
  17.000   1.7810   0.06524   0.05959  -0.0812   0.0277   1.0000
  17.250   1.7803   0.06841   0.06281  -0.0810   0.0255   1.0000
  17.500   1.7794   0.07168   0.06615  -0.0809   0.0235   1.0000
  17.750   1.7760   0.07536   0.06988  -0.0810   0.0217   1.0000
  18.000   1.7747   0.07881   0.07341  -0.0812   0.0199   1.0000
  18.250   1.7708   0.08270   0.07736  -0.0815   0.0184   1.0000
  18.500   1.7669   0.08669   0.08142  -0.0821   0.0170   1.0000
  18.750   1.7609   0.09103   0.08584  -0.0828   0.0156   1.0000
  19.000   1.7563   0.09526   0.09016  -0.0836   0.0146   1.0000
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