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DAE-11 AIRFOIL (dae11-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: DAE-11 AIRFOIL (dae11-il)
Reynolds number: 200,000
Max Cl/Cd: 79 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dae11-il-200000.txt
Download as CSV file: xf-dae11-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAE-11 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0664   0.10642   0.10221  -0.0765   0.7797   0.0375
  -9.500  -0.0707   0.10465   0.10047  -0.0802   0.7773   0.0379
  -9.250  -0.0643   0.10098   0.09681  -0.0814   0.7752   0.0382
  -9.000  -0.0444   0.09737   0.09315  -0.0798   0.7734   0.0391
  -8.750  -0.0339   0.09493   0.09069  -0.0802   0.7716   0.0400
  -8.500  -0.0245   0.09253   0.08833  -0.0814   0.7692   0.0420
  -8.250  -0.0178   0.09005   0.08589  -0.0831   0.7667   0.0431
  -8.000  -0.0214   0.08808   0.08399  -0.0871   0.7637   0.0451
  -7.750  -0.0279   0.08609   0.08205  -0.0912   0.7606   0.0455
  -7.500  -0.0262   0.08263   0.07862  -0.0922   0.7584   0.0459
  -7.250  -0.0044   0.07935   0.07529  -0.0901   0.7569   0.0468
  -7.000   0.0060   0.07721   0.07313  -0.0899   0.7552   0.0479
  -6.750   0.0116   0.07526   0.07126  -0.0908   0.7522   0.0490
  -6.500   0.0181   0.07301   0.06905  -0.0928   0.7489   0.0505
  -6.250   0.0256   0.07023   0.06628  -0.0970   0.7460   0.0527
  -6.000   0.0381   0.06387   0.05975  -0.1142   0.7430   0.0550
  -5.750   0.0485   0.06172   0.05767  -0.1105   0.7413   0.0559
  -5.500   0.0622   0.06001   0.05595  -0.1092   0.7396   0.0572
  -5.250   0.0788   0.05787   0.05384  -0.1112   0.7360   0.0593
  -5.000   0.1077   0.05179   0.04726  -0.1244   0.7321   0.0662
  -4.750   0.1228   0.04929   0.04491  -0.1234   0.7296   0.0675
  -4.500   0.1410   0.04796   0.04362  -0.1228   0.7275   0.0702
  -4.250   0.1693   0.04392   0.03909  -0.1280   0.7255   0.0799
  -4.000   0.1893   0.04209   0.03730  -0.1275   0.7238   0.0822
  -3.750   0.2117   0.04072   0.03589  -0.1287   0.7196   0.0872
  -3.500   0.2368   0.03829   0.03320  -0.1309   0.7160   0.0960
  -3.250   0.2612   0.03686   0.03169  -0.1313   0.7132   0.1018
  -3.000   0.3004   0.02858   0.02191  -0.1327   0.7113   0.0511
  -2.750   0.3290   0.02665   0.01955  -0.1325   0.7096   0.0498
  -2.500   0.3572   0.02555   0.01815  -0.1322   0.7080   0.0512
  -2.250   0.3814   0.02506   0.01749  -0.1322   0.7036   0.0514
  -2.000   0.4064   0.02459   0.01687  -0.1320   0.6993   0.0525
  -1.750   0.4338   0.02403   0.01615  -0.1317   0.6966   0.0544
  -1.500   0.4612   0.02319   0.01534  -0.1315   0.6947   0.0596
  -1.250   0.4898   0.02267   0.01474  -0.1312   0.6931   0.0649
  -1.000   0.5177   0.02205   0.01414  -0.1310   0.6916   0.0743
  -0.750   0.5360   0.02265   0.01489  -0.1308   0.6845   0.0874
  -0.500   0.5621   0.02219   0.01466  -0.1307   0.6814   0.1444
  -0.250   0.5866   0.02100   0.01464  -0.1305   0.6793   0.4899
   0.000   0.6186   0.01968   0.01439  -0.1301   0.6778   1.0000
   0.250   0.6483   0.01963   0.01411  -0.1301   0.6763   1.0000
   0.500   0.6656   0.02079   0.01524  -0.1297   0.6692   1.0000
   0.750   0.6917   0.02102   0.01535  -0.1295   0.6657   1.0000
   1.000   0.7209   0.02097   0.01516  -0.1295   0.6636   1.0000
   1.250   0.7513   0.02081   0.01486  -0.1295   0.6620   1.0000
   1.500   0.7815   0.02067   0.01459  -0.1295   0.6606   1.0000
   1.750   0.7946   0.02208   0.01604  -0.1287   0.6523   1.0000
   2.000   0.8225   0.02210   0.01598  -0.1286   0.6494   1.0000
   2.250   0.8529   0.02192   0.01571  -0.1286   0.6476   1.0000
   2.500   0.8838   0.02169   0.01540  -0.1287   0.6461   1.0000
   2.750   0.9153   0.02144   0.01505  -0.1289   0.6448   1.0000
   3.000   0.9250   0.02294   0.01665  -0.1276   0.6355   1.0000
   3.250   0.9554   0.02271   0.01636  -0.1276   0.6333   1.0000
   3.500   0.9872   0.02237   0.01595  -0.1278   0.6316   1.0000
   3.750   1.0196   0.02199   0.01552  -0.1281   0.6302   1.0000
   4.000   1.0518   0.02166   0.01513  -0.1284   0.6286   1.0000
   4.250   1.0609   0.02300   0.01659  -0.1267   0.6191   1.0000
   4.500   1.0928   0.02260   0.01615  -0.1270   0.6171   1.0000
   4.750   1.1264   0.02210   0.01562  -0.1274   0.6155   1.0000
   5.000   1.1608   0.02158   0.01505  -0.1279   0.6140   1.0000
   5.250   1.1693   0.02280   0.01640  -0.1260   0.6047   1.0000
   5.500   1.2024   0.02228   0.01587  -0.1264   0.6023   1.0000
   5.750   1.2372   0.02166   0.01523  -0.1270   0.6004   1.0000
   6.000   1.2546   0.02222   0.01587  -0.1258   0.5938   1.0000
   6.250   1.2817   0.02205   0.01574  -0.1256   0.5893   1.0000
   6.500   1.3164   0.02141   0.01509  -0.1262   0.5866   1.0000
   6.750   1.3530   0.02071   0.01435  -0.1270   0.5844   1.0000
   7.000   1.3641   0.02145   0.01524  -0.1251   0.5755   1.0000
   7.250   1.3986   0.02079   0.01459  -0.1257   0.5718   1.0000
   7.500   1.4230   0.02076   0.01461  -0.1251   0.5659   1.0000
   7.750   1.4470   0.02066   0.01457  -0.1245   0.5592   1.0000
   8.000   1.4843   0.01992   0.01381  -0.1255   0.5551   1.0000
   8.250   1.4966   0.02041   0.01444  -0.1235   0.5456   1.0000
   8.500   1.5328   0.01976   0.01375  -0.1243   0.5402   1.0000
   8.750   1.5443   0.02022   0.01434  -0.1221   0.5299   1.0000
   9.000   1.5666   0.02022   0.01438  -0.1213   0.5212   1.0000
   9.250   1.5903   0.02013   0.01430  -0.1206   0.5118   1.0000
   9.500   1.6007   0.02059   0.01486  -0.1182   0.5005   1.0000
   9.750   1.6139   0.02091   0.01522  -0.1161   0.4893   1.0000
  10.000   1.6262   0.02122   0.01553  -0.1138   0.4778   1.0000
  10.250   1.6363   0.02167   0.01596  -0.1114   0.4654   1.0000
  10.500   1.6370   0.02262   0.01695  -0.1082   0.4521   1.0000
  10.750   1.6381   0.02374   0.01809  -0.1054   0.4381   1.0000
  11.000   1.6398   0.02497   0.01932  -0.1028   0.4235   1.0000
  11.250   1.6411   0.02634   0.02067  -0.1004   0.4083   1.0000
  11.500   1.6418   0.02784   0.02216  -0.0981   0.3930   1.0000
  11.750   1.6415   0.02950   0.02378  -0.0959   0.3773   1.0000
  12.000   1.6407   0.03129   0.02555  -0.0937   0.3616   1.0000
  12.250   1.6387   0.03322   0.02745  -0.0916   0.3457   1.0000
  12.500   1.6357   0.03534   0.02956  -0.0896   0.3298   1.0000
  12.750   1.6321   0.03757   0.03177  -0.0877   0.3139   1.0000
  13.000   1.6282   0.03992   0.03411  -0.0860   0.2981   1.0000
  13.250   1.6238   0.04245   0.03662  -0.0843   0.2819   1.0000
  13.500   1.6198   0.04508   0.03923  -0.0829   0.2661   1.0000
  13.750   1.6152   0.04788   0.04201  -0.0816   0.2501   1.0000
  14.000   1.6101   0.05084   0.04496  -0.0805   0.2342   1.0000
  14.250   1.6049   0.05394   0.04803  -0.0794   0.2188   1.0000
  14.500   1.5991   0.05722   0.05128  -0.0786   0.2035   1.0000
  14.750   1.5931   0.06061   0.05465  -0.0779   0.1886   1.0000
  15.000   1.5865   0.06420   0.05820  -0.0773   0.1741   1.0000
  15.250   1.5800   0.06790   0.06188  -0.0769   0.1602   1.0000
  15.500   1.5729   0.07176   0.06572  -0.0766   0.1467   1.0000
  15.750   1.5658   0.07574   0.06969  -0.0765   0.1339   1.0000
  16.000   1.5586   0.07983   0.07377  -0.0765   0.1219   1.0000
  16.250   1.5514   0.08402   0.07796  -0.0766   0.1108   1.0000
  16.500   1.5436   0.08834   0.08228  -0.0769   0.1009   1.0000
  16.750   1.5345   0.09295   0.08684  -0.0774   0.0925   1.0000
  17.000   1.5293   0.09712   0.09106  -0.0779   0.0840   1.0000
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