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DAE-31 AIRFOIL (dae31-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: DAE-31 AIRFOIL (dae31-il)
Reynolds number: 500,000
Max Cl/Cd: 128.78 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dae31-il-500000-n5.txt
Download as CSV file: xf-dae31-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750   0.0267   0.08671   0.08334  -0.1001   0.7972   0.0164
  -8.500   0.0321   0.08390   0.08054  -0.1014   0.7944   0.0165
  -8.250   0.0390   0.08133   0.07798  -0.1025   0.7917   0.0165
  -8.000   0.0446   0.07866   0.07530  -0.1036   0.7890   0.0165
  -7.750   0.0488   0.07584   0.07247  -0.1047   0.7863   0.0165
  -7.250   0.0566   0.06969   0.06637  -0.1061   0.7805   0.0137
  -7.000   0.0602   0.06730   0.06400  -0.1066   0.7772   0.0136
  -6.750   0.0609   0.06466   0.06137  -0.1074   0.7738   0.0137
  -6.500   0.0679   0.06170   0.05840  -0.1097   0.7707   0.0136
  -5.500   0.1195   0.02241   0.01803  -0.1498   0.7569   0.0140
  -5.250   0.1455   0.01965   0.01487  -0.1514   0.7543   0.0142
  -5.000   0.1725   0.01815   0.01308  -0.1522   0.7518   0.0145
  -4.750   0.1997   0.01663   0.01126  -0.1528   0.7492   0.0148
  -4.500   0.2273   0.01543   0.00981  -0.1532   0.7461   0.0151
  -4.250   0.2551   0.01438   0.00852  -0.1535   0.7428   0.0155
  -4.000   0.2831   0.01356   0.00747  -0.1536   0.7396   0.0160
  -3.750   0.3113   0.01295   0.00664  -0.1537   0.7367   0.0166
  -3.500   0.3392   0.01242   0.00602  -0.1538   0.7339   0.0170
  -3.250   0.3674   0.01202   0.00558  -0.1539   0.7308   0.0175
  -3.000   0.3957   0.01163   0.00513  -0.1540   0.7272   0.0179
  -2.750   0.4239   0.01126   0.00469  -0.1540   0.7237   0.0185
  -2.500   0.4522   0.01093   0.00428  -0.1540   0.7202   0.0191
  -2.250   0.4804   0.01063   0.00390  -0.1540   0.7170   0.0198
  -2.000   0.5087   0.01038   0.00366  -0.1541   0.7132   0.0205
  -1.750   0.5370   0.01018   0.00345  -0.1542   0.7090   0.0215
  -1.500   0.5653   0.01000   0.00323  -0.1542   0.7046   0.0228
  -1.250   0.5935   0.00984   0.00305  -0.1542   0.7006   0.0245
  -1.000   0.6218   0.00970   0.00289  -0.1542   0.6962   0.0264
  -0.750   0.6500   0.00956   0.00276  -0.1542   0.6913   0.0287
  -0.500   0.6781   0.00945   0.00263  -0.1542   0.6863   0.0319
  -0.250   0.7061   0.00937   0.00253  -0.1542   0.6817   0.0379
   0.000   0.7342   0.00927   0.00248  -0.1542   0.6761   0.0480
   0.250   0.7620   0.00918   0.00242  -0.1542   0.6703   0.0660
   0.500   0.7898   0.00908   0.00239  -0.1541   0.6647   0.0975
   0.750   0.8174   0.00896   0.00241  -0.1542   0.6581   0.1480
   1.000   0.8447   0.00882   0.00243  -0.1541   0.6513   0.2267
   1.500   0.8985   0.00852   0.00259  -0.1540   0.6359   0.4354
   1.750   0.9248   0.00838   0.00268  -0.1538   0.6277   0.5448
   2.250   0.9786   0.00775   0.00281  -0.1533   0.6091   1.0000
   2.500   1.0048   0.00791   0.00287  -0.1529   0.5991   1.0000
   2.750   1.0312   0.00804   0.00295  -0.1527   0.5884   1.0000
   3.000   1.0571   0.00821   0.00304  -0.1523   0.5778   1.0000
   3.250   1.0822   0.00841   0.00316  -0.1518   0.5656   1.0000
   3.500   1.1075   0.00860   0.00328  -0.1513   0.5529   1.0000
   3.750   1.1322   0.00882   0.00342  -0.1508   0.5400   1.0000
   4.000   1.1562   0.00906   0.00359  -0.1501   0.5267   1.0000
   4.250   1.1797   0.00933   0.00378  -0.1494   0.5132   1.0000
   4.500   1.2029   0.00960   0.00397  -0.1486   0.4993   1.0000
   4.750   1.2261   0.00986   0.00418  -0.1479   0.4861   1.0000
   5.000   1.2485   0.01015   0.00441  -0.1470   0.4728   1.0000
   5.250   1.2700   0.01047   0.00466  -0.1459   0.4592   1.0000
   5.500   1.2907   0.01081   0.00493  -0.1447   0.4457   1.0000
   5.750   1.3111   0.01114   0.00521  -0.1435   0.4315   1.0000
   6.000   1.3306   0.01149   0.00551  -0.1422   0.4174   1.0000
   6.250   1.3488   0.01187   0.00584  -0.1406   0.4033   1.0000
   6.500   1.3644   0.01229   0.00619  -0.1386   0.3890   1.0000
   6.750   1.3775   0.01273   0.00658  -0.1361   0.3752   1.0000
   7.000   1.3895   0.01325   0.00703  -0.1335   0.3607   1.0000
   7.250   1.4032   0.01375   0.00750  -0.1313   0.3474   1.0000
   7.500   1.4166   0.01430   0.00801  -0.1292   0.3343   1.0000
   7.750   1.4296   0.01491   0.00858  -0.1271   0.3214   1.0000
   8.000   1.4419   0.01560   0.00921  -0.1250   0.3079   1.0000
   8.250   1.4539   0.01632   0.00989  -0.1229   0.2948   1.0000
   8.500   1.4671   0.01703   0.01057  -0.1211   0.2818   1.0000
   8.750   1.4797   0.01780   0.01129  -0.1192   0.2693   1.0000
   9.000   1.4921   0.01860   0.01207  -0.1174   0.2575   1.0000
   9.250   1.5036   0.01948   0.01290  -0.1155   0.2457   1.0000
   9.500   1.5153   0.02037   0.01376  -0.1138   0.2334   1.0000
   9.750   1.5274   0.02126   0.01463  -0.1121   0.2221   1.0000
  10.000   1.5387   0.02222   0.01557  -0.1104   0.2113   1.0000
  10.250   1.5489   0.02328   0.01659  -0.1086   0.2003   1.0000
  10.500   1.5601   0.02429   0.01759  -0.1070   0.1897   1.0000
  10.750   1.5705   0.02538   0.01866  -0.1053   0.1797   1.0000
  11.000   1.5800   0.02656   0.01981  -0.1036   0.1693   1.0000
  11.500   1.5981   0.02904   0.02226  -0.1004   0.1495   1.0000
  11.750   1.6066   0.03037   0.02357  -0.0989   0.1407   1.0000
  12.000   1.6146   0.03177   0.02495  -0.0973   0.1322   1.0000
  12.250   1.6234   0.03314   0.02634  -0.0959   0.1246   1.0000
  12.500   1.6315   0.03460   0.02781  -0.0945   0.1170   1.0000
  12.750   1.6380   0.03624   0.02944  -0.0931   0.1096   1.0000
  13.000   1.6454   0.03785   0.03106  -0.0919   0.1019   1.0000
  13.250   1.6520   0.03958   0.03279  -0.0906   0.0950   1.0000
  13.500   1.6579   0.04140   0.03463  -0.0894   0.0888   1.0000
  13.750   1.6624   0.04342   0.03664  -0.0883   0.0813   1.0000
  14.000   1.6676   0.04542   0.03865  -0.0872   0.0744   1.0000
  14.250   1.6720   0.04754   0.04079  -0.0862   0.0684   1.0000
  14.500   1.6762   0.04974   0.04301  -0.0853   0.0631   1.0000
  14.750   1.6796   0.05207   0.04537  -0.0845   0.0583   1.0000
  15.000   1.6836   0.05441   0.04775  -0.0838   0.0539   1.0000
  15.250   1.6870   0.05685   0.05024  -0.0832   0.0499   1.0000
  15.500   1.6886   0.05955   0.05298  -0.0826   0.0462   1.0000
  15.750   1.6908   0.06225   0.05573  -0.0821   0.0425   1.0000
  16.000   1.6923   0.06511   0.05864  -0.0818   0.0393   1.0000
  16.250   1.6925   0.06818   0.06177  -0.0816   0.0365   1.0000
  16.500   1.6929   0.07128   0.06494  -0.0814   0.0338   1.0000
  16.750   1.6928   0.07452   0.06825  -0.0814   0.0315   1.0000
  17.000   1.6917   0.07795   0.07175  -0.0816   0.0292   1.0000
  17.250   1.6903   0.08150   0.07539  -0.0818   0.0274   1.0000
  17.500   1.6884   0.08519   0.07916  -0.0822   0.0257   1.0000
  17.750   1.6861   0.08898   0.08303  -0.0827   0.0241   1.0000
  18.000   1.6831   0.09293   0.08708  -0.0834   0.0226   1.0000
  18.250   1.6790   0.09714   0.09137  -0.0842   0.0214   1.0000
  18.500   1.6756   0.10128   0.09562  -0.0852   0.0201   1.0000
  18.750   1.6704   0.10575   0.10018  -0.0863   0.0190   1.0000
  19.000   1.6662   0.11010   0.10463  -0.0876   0.0181   1.0000
  19.250   1.6614   0.11461   0.10924  -0.0890   0.0171   1.0000
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