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DAE-11 AIRFOIL (dae11-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: DAE-11 AIRFOIL (dae11-il)
Reynolds number: 500,000
Max Cl/Cd: 135.81 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dae11-il-500000.txt
Download as CSV file: xf-dae11-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.0484   0.08616   0.08260  -0.0786   0.7081   0.0218
  -8.250  -0.0452   0.08299   0.07945  -0.0808   0.7064   0.0218
  -8.000  -0.0449   0.07910   0.07562  -0.0830   0.7048   0.0220
  -7.750  -0.0324   0.07700   0.07353  -0.0824   0.7031   0.0224
  -7.500  -0.0221   0.07490   0.07144  -0.0828   0.7012   0.0227
  -7.250  -0.0157   0.07250   0.06906  -0.0837   0.6993   0.0229
  -7.000  -0.0108   0.07019   0.06677  -0.0844   0.6974   0.0234
  -6.750  -0.0078   0.06784   0.06444  -0.0856   0.6957   0.0239
  -6.500  -0.0001   0.06486   0.06144  -0.0885   0.6939   0.0245
  -6.250   0.0104   0.05659   0.05311  -0.1029   0.6920   0.0263
  -6.000   0.0205   0.05252   0.04903  -0.1056   0.6902   0.0268
  -5.750   0.0371   0.05040   0.04691  -0.1070   0.6885   0.0271
  -5.500   0.0559   0.04789   0.04437  -0.1092   0.6866   0.0277
  -5.250   0.0768   0.04460   0.04101  -0.1126   0.6846   0.0284
  -5.000   0.1034   0.03416   0.02991  -0.1218   0.6828   0.0321
  -4.750   0.1258   0.03247   0.02823  -0.1225   0.6809   0.0326
  -4.500   0.1500   0.03101   0.02670  -0.1233   0.6792   0.0334
  -4.250   0.1793   0.02887   0.02409  -0.1245   0.6776   0.0376
  -4.000   0.2041   0.02022   0.01429  -0.1257   0.6762   0.0266
  -3.750   0.2315   0.01869   0.01257  -0.1259   0.6744   0.0261
  -3.500   0.2590   0.01685   0.01050  -0.1261   0.6724   0.0256
  -3.250   0.2872   0.01566   0.00910  -0.1262   0.6703   0.0256
  -3.000   0.3156   0.01486   0.00813  -0.1263   0.6683   0.0260
  -2.750   0.3439   0.01406   0.00720  -0.1263   0.6663   0.0267
  -2.500   0.3719   0.01336   0.00648  -0.1264   0.6644   0.0277
  -2.250   0.4004   0.01299   0.00606  -0.1265   0.6626   0.0291
  -2.000   0.4291   0.01277   0.00578  -0.1266   0.6609   0.0312
  -1.750   0.4572   0.01235   0.00534  -0.1267   0.6589   0.0333
  -1.500   0.4856   0.01208   0.00511  -0.1269   0.6567   0.0360
  -1.250   0.5141   0.01178   0.00480  -0.1270   0.6543   0.0399
  -1.000   0.5428   0.01159   0.00462  -0.1272   0.6520   0.0465
  -0.750   0.5716   0.01131   0.00437  -0.1274   0.6498   0.0611
  -0.500   0.6002   0.01095   0.00419  -0.1276   0.6478   0.1230
  -0.250   0.6283   0.01053   0.00414  -0.1280   0.6458   0.2591
   0.000   0.6560   0.01023   0.00422  -0.1282   0.6437   0.4081
   0.250   0.6826   0.00988   0.00431  -0.1282   0.6410   0.5583
   0.500   0.7052   0.00930   0.00439  -0.1271   0.6383   0.7769
   0.750   0.7410   0.00893   0.00429  -0.1285   0.6357   1.0000
   1.000   0.7698   0.00895   0.00423  -0.1287   0.6333   1.0000
   1.250   0.7988   0.00899   0.00417  -0.1289   0.6310   1.0000
   1.500   0.8275   0.00910   0.00419  -0.1291   0.6287   1.0000
   1.750   0.8555   0.00915   0.00424  -0.1292   0.6258   1.0000
   2.000   0.8838   0.00920   0.00428  -0.1293   0.6227   1.0000
   2.250   0.9123   0.00922   0.00426  -0.1295   0.6197   1.0000
   2.500   0.9410   0.00924   0.00423  -0.1297   0.6170   1.0000
   2.750   0.9697   0.00930   0.00421  -0.1299   0.6144   1.0000
   3.000   0.9975   0.00938   0.00430  -0.1300   0.6111   1.0000
   3.250   1.0253   0.00942   0.00435  -0.1301   0.6074   1.0000
   3.500   1.0536   0.00944   0.00436  -0.1303   0.6040   1.0000
   3.750   1.0820   0.00947   0.00435  -0.1304   0.6009   1.0000
   4.000   1.1100   0.00955   0.00441  -0.1306   0.5975   1.0000
   4.250   1.1373   0.00961   0.00451  -0.1306   0.5931   1.0000
   4.500   1.1651   0.00964   0.00454  -0.1307   0.5890   1.0000
   4.750   1.1932   0.00968   0.00454  -0.1309   0.5854   1.0000
   5.000   1.2203   0.00977   0.00466  -0.1309   0.5809   1.0000
   5.250   1.2474   0.00983   0.00477  -0.1309   0.5759   1.0000
   5.500   1.2749   0.00989   0.00480  -0.1310   0.5714   1.0000
   5.750   1.3017   0.00999   0.00492  -0.1310   0.5662   1.0000
   6.000   1.3282   0.01007   0.00505  -0.1310   0.5602   1.0000
   6.250   1.3551   0.01017   0.00510  -0.1309   0.5548   1.0000
   6.500   1.3808   0.01028   0.00530  -0.1308   0.5478   1.0000
   6.750   1.4068   0.01041   0.00541  -0.1307   0.5413   1.0000
   7.000   1.4321   0.01056   0.00562  -0.1305   0.5337   1.0000
   7.250   1.4572   0.01073   0.00577  -0.1302   0.5262   1.0000
   7.500   1.4816   0.01092   0.00602  -0.1299   0.5174   1.0000
   7.750   1.5054   0.01115   0.00623  -0.1295   0.5087   1.0000
   8.000   1.5284   0.01139   0.00650  -0.1289   0.4985   1.0000
   8.250   1.5507   0.01167   0.00681  -0.1283   0.4878   1.0000
   8.500   1.5715   0.01200   0.00714  -0.1274   0.4763   1.0000
   8.750   1.5905   0.01239   0.00751  -0.1263   0.4637   1.0000
   9.000   1.6074   0.01285   0.00796  -0.1249   0.4499   1.0000
   9.250   1.6214   0.01339   0.00848  -0.1230   0.4349   1.0000
   9.500   1.6304   0.01402   0.00908  -0.1203   0.4197   1.0000
   9.750   1.6319   0.01482   0.00986  -0.1165   0.4050   1.0000
  10.000   1.6318   0.01592   0.01093  -0.1131   0.3897   1.0000
  10.250   1.6322   0.01724   0.01222  -0.1102   0.3742   1.0000
  10.500   1.6330   0.01872   0.01367  -0.1076   0.3588   1.0000
  10.750   1.6336   0.02033   0.01524  -0.1052   0.3431   1.0000
  11.000   1.6338   0.02204   0.01692  -0.1030   0.3276   1.0000
  11.250   1.6330   0.02388   0.01872  -0.1007   0.3113   1.0000
  11.500   1.6318   0.02582   0.02061  -0.0986   0.2953   1.0000
  11.750   1.6302   0.02784   0.02259  -0.0965   0.2795   1.0000
  12.000   1.6277   0.02998   0.02468  -0.0944   0.2631   1.0000
  12.250   1.6259   0.03212   0.02678  -0.0925   0.2479   1.0000
  12.500   1.6237   0.03436   0.02898  -0.0907   0.2324   1.0000
  12.750   1.6219   0.03670   0.03126  -0.0891   0.2167   1.0000
  13.000   1.6205   0.03908   0.03360  -0.0877   0.2020   1.0000
  13.250   1.6190   0.04156   0.03603  -0.0863   0.1872   1.0000
  13.500   1.6177   0.04408   0.03850  -0.0851   0.1727   1.0000
  13.750   1.6163   0.04670   0.04109  -0.0840   0.1589   1.0000
  14.000   1.6151   0.04938   0.04372  -0.0830   0.1453   1.0000
  14.250   1.6137   0.05213   0.04643  -0.0821   0.1322   1.0000
  14.500   1.6125   0.05493   0.04921  -0.0813   0.1202   1.0000
  14.750   1.6115   0.05778   0.05203  -0.0806   0.1084   1.0000
  15.000   1.6100   0.06077   0.05500  -0.0800   0.0978   1.0000
  15.250   1.6082   0.06384   0.05805  -0.0795   0.0877   1.0000
  15.500   1.6064   0.06698   0.06118  -0.0791   0.0788   1.0000
  15.750   1.6031   0.07041   0.06460  -0.0789   0.0707   1.0000
  16.000   1.6025   0.07354   0.06776  -0.0787   0.0635   1.0000
  16.250   1.6005   0.07693   0.07116  -0.0786   0.0568   1.0000
  16.500   1.5959   0.08073   0.07497  -0.0787   0.0513   1.0000
  16.750   1.5959   0.08398   0.07827  -0.0788   0.0466   1.0000
  17.000   1.5913   0.08793   0.08226  -0.0792   0.0425   1.0000
  17.250   1.5902   0.09143   0.08582  -0.0795   0.0390   1.0000
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