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DAE-11 AIRFOIL (dae11-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: DAE-11 AIRFOIL (dae11-il)
Reynolds number: 100,000
Max Cl/Cd: 32.62 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dae11-il-100000-n5.txt
Download as CSV file: xf-dae11-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.0516   0.10331   0.09760  -0.0760   0.7621   0.0515
  -9.000  -0.0475   0.10099   0.09529  -0.0779   0.7597   0.0531
  -8.750  -0.0483   0.09916   0.09348  -0.0807   0.7573   0.0541
  -8.500  -0.0496   0.09709   0.09143  -0.0836   0.7551   0.0545
  -8.250  -0.0475   0.09469   0.08910  -0.0865   0.7519   0.0547
  -8.000  -0.0362   0.09081   0.08526  -0.0868   0.7496   0.0552
  -7.750  -0.0203   0.08756   0.08200  -0.0860   0.7473   0.0562
  -7.500  -0.0099   0.08493   0.07937  -0.0863   0.7448   0.0572
  -7.250  -0.0020   0.08252   0.07695  -0.0869   0.7424   0.0585
  -7.000   0.0034   0.08027   0.07470  -0.0878   0.7403   0.0607
  -6.750   0.0039   0.07830   0.07278  -0.0897   0.7377   0.0630
  -6.500   0.0047   0.07550   0.07002  -0.1007   0.7335   0.0654
  -5.500   0.0555   0.05588   0.05006  -0.1139   0.7240   0.0375
  -5.250   0.0723   0.05297   0.04709  -0.1162   0.7213   0.0367
  -5.000   0.0909   0.04933   0.04331  -0.1195   0.7176   0.0358
  -4.750   0.1121   0.04513   0.03884  -0.1229   0.7145   0.0349
  -4.500   0.1354   0.04095   0.03423  -0.1256   0.7119   0.0343
  -4.250   0.1603   0.03759   0.03040  -0.1274   0.7099   0.0345
  -4.000   0.1866   0.03494   0.02721  -0.1285   0.7082   0.0361
  -3.750   0.2124   0.03276   0.02449  -0.1292   0.7055   0.0371
  -3.500   0.2366   0.03126   0.02258  -0.1295   0.7013   0.0375
  -3.250   0.2623   0.02990   0.02085  -0.1295   0.6982   0.0382
  -3.000   0.2882   0.02886   0.01964  -0.1295   0.6958   0.0392
  -2.750   0.3150   0.02808   0.01871  -0.1295   0.6938   0.0415
  -2.500   0.3429   0.02727   0.01763  -0.1293   0.6921   0.0446
  -2.250   0.3668   0.02677   0.01704  -0.1290   0.6885   0.0466
  -2.000   0.3891   0.02658   0.01687  -0.1287   0.6842   0.0489
  -1.750   0.4143   0.02627   0.01646  -0.1284   0.6812   0.0537
  -1.500   0.4406   0.02579   0.01599  -0.1282   0.6788   0.0591
  -1.250   0.4680   0.02534   0.01544  -0.1279   0.6770   0.0667
  -1.000   0.4961   0.02490   0.01497  -0.1278   0.6755   0.0798
  -0.750   0.5126   0.02545   0.01567  -0.1272   0.6690   0.0984
  -0.500   0.5371   0.02520   0.01564  -0.1271   0.6656   0.1570
  -0.250   0.5636   0.02459   0.01564  -0.1272   0.6632   0.3466
   0.000   0.5887   0.02390   0.01563  -0.1265   0.6614   0.5821
   0.500   0.6344   0.02421   0.01647  -0.1253   0.6525   1.0000
   0.750   0.6594   0.02451   0.01659  -0.1250   0.6492   1.0000
   1.000   0.6873   0.02460   0.01650  -0.1249   0.6469   1.0000
   1.250   0.7166   0.02460   0.01632  -0.1249   0.6452   1.0000
   1.750   0.7516   0.02623   0.01781  -0.1233   0.6340   1.0000
   2.000   0.7797   0.02627   0.01773  -0.1231   0.6317   1.0000
   2.250   0.8095   0.02618   0.01753  -0.1231   0.6300   1.0000
   2.750   0.8400   0.02799   0.01927  -0.1210   0.6180   1.0000
   3.000   0.8691   0.02792   0.01913  -0.1209   0.6160   1.0000
   3.250   0.8999   0.02774   0.01887  -0.1210   0.6145   1.0000
   3.750   0.9256   0.02968   0.02081  -0.1183   0.6015   1.0000
   4.000   0.9570   0.02940   0.02048  -0.1183   0.6000   1.0000
   4.500   0.9790   0.03139   0.02250  -0.1152   0.5866   1.0000
   4.750   1.0115   0.03101   0.02209  -0.1153   0.5851   1.0000
   5.250   1.0282   0.03315   0.02426  -0.1116   0.5711   1.0000
   5.500   1.0619   0.03255   0.02367  -0.1117   0.5699   1.0000
   6.000   1.0683   0.03575   0.02693  -0.1078   0.5524   1.0000
   6.500   1.1059   0.03659   0.02785  -0.1060   0.5419   1.0000
   6.750   1.1393   0.03583   0.02711  -0.1059   0.5405   1.0000
   7.250   1.1463   0.03925   0.03062  -0.1026   0.5217   1.0000
   7.500   1.1608   0.04003   0.03148  -0.1015   0.5147   1.0000
   7.750   1.1926   0.03926   0.03075  -0.1012   0.5125   1.0000
   8.000   1.2251   0.03843   0.02997  -0.1010   0.5102   1.0000
   8.500   1.2287   0.04228   0.03398  -0.0978   0.4891   1.0000
   8.750   1.2544   0.04197   0.03374  -0.0972   0.4844   1.0000
   9.000   1.2901   0.04073   0.03256  -0.0970   0.4817   1.0000
   9.500   1.3251   0.04162   0.03362  -0.0951   0.4667   1.0000
   9.750   1.3244   0.04382   0.03590  -0.0935   0.4548   1.0000
  10.250   1.3625   0.04440   0.03665  -0.0918   0.4387   1.0000
  10.500   1.3713   0.04572   0.03805  -0.0906   0.4282   1.0000
  10.750   1.4051   0.04449   0.03687  -0.0901   0.4214   1.0000
  11.000   1.4078   0.04640   0.03887  -0.0888   0.4091   1.0000
  11.250   1.4185   0.04752   0.04008  -0.0877   0.3976   1.0000
  11.500   1.4362   0.04790   0.04050  -0.0867   0.3866   1.0000
  11.750   1.4557   0.04806   0.04069  -0.0858   0.3751   1.0000
  12.000   1.4631   0.04950   0.04218  -0.0846   0.3619   1.0000
  12.250   1.4687   0.05119   0.04393  -0.0835   0.3483   1.0000
  12.500   1.4744   0.05290   0.04568  -0.0824   0.3344   1.0000
  12.750   1.4797   0.05470   0.04752  -0.0814   0.3204   1.0000
  13.000   1.4839   0.05667   0.04950  -0.0804   0.3058   1.0000
  13.250   1.4872   0.05879   0.05164  -0.0795   0.2913   1.0000
  13.500   1.4891   0.06112   0.05401  -0.0787   0.2767   1.0000
  13.750   1.4904   0.06361   0.05651  -0.0779   0.2621   1.0000
  14.000   1.4904   0.06632   0.05923  -0.0773   0.2477   1.0000
  14.250   1.4896   0.06921   0.06213  -0.0768   0.2334   1.0000
  14.500   1.4880   0.07227   0.06522  -0.0763   0.2194   1.0000
  14.750   1.4857   0.07551   0.06847  -0.0761   0.2058   1.0000
  15.000   1.4827   0.07892   0.07190  -0.0759   0.1925   1.0000
  15.250   1.4792   0.08249   0.07550  -0.0759   0.1797   1.0000
  15.500   1.4751   0.08620   0.07922  -0.0760   0.1677   1.0000
  15.750   1.4704   0.09009   0.08313  -0.0762   0.1561   1.0000
  16.000   1.4656   0.09411   0.08718  -0.0767   0.1448   1.0000
  16.250   1.4609   0.09818   0.09131  -0.0772   0.1341   1.0000
  16.500   1.4560   0.10234   0.09552  -0.0779   0.1243   1.0000
  16.750   1.4504   0.10665   0.09985  -0.0787   0.1153   1.0000
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