Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: AG27 Bubble Dancer DLG by Mark Drela (ag27-il)
Reynolds number: 100,000
Max Cl/Cd: 55.13 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag27-il-100000.txt
Download as CSV file: xf-ag27-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG27 Bubble Dancer DLG by Mark Drela            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4815   0.10209   0.09732   0.0036   1.0000   0.0691
  -7.750  -0.4769   0.09892   0.09417   0.0015   1.0000   0.0718
  -7.500  -0.4763   0.09641   0.09173  -0.0037   1.0000   0.0744
  -7.250  -0.4658   0.09331   0.08870  -0.0195   1.0000   0.0756
  -7.000  -0.4602   0.08793   0.08335  -0.0114   1.0000   0.0773
  -6.750  -0.4492   0.08446   0.07989  -0.0094   1.0000   0.0803
  -6.500  -0.4370   0.08082   0.07628  -0.0128   1.0000   0.0846
  -6.250  -0.4131   0.07524   0.07063  -0.0310   1.0000   0.0898
  -6.000  -0.4069   0.07193   0.06742  -0.0243   1.0000   0.0922
  -5.750  -0.3917   0.06851   0.06400  -0.0256   1.0000   0.0974
  -5.500  -0.3673   0.06307   0.05846  -0.0355   1.0000   0.1048
  -5.250  -0.3527   0.06025   0.05568  -0.0344   1.0000   0.1125
  -5.000  -0.3334   0.05635   0.05175  -0.0374   1.0000   0.1227
  -4.750  -0.3121   0.05259   0.04792  -0.0405   1.0000   0.1357
  -4.500  -0.2900   0.04898   0.04421  -0.0431   1.0000   0.1493
  -4.250  -0.2614   0.04551   0.04046  -0.0481   1.0000   0.1731
  -4.000  -0.2445   0.04255   0.03761  -0.0465   1.0000   0.1816
  -3.750  -0.1934   0.03405   0.02816  -0.0560   1.0000   0.1328
  -3.500  -0.1430   0.02459   0.01691  -0.0586   1.0000   0.0605
  -3.250  -0.1148   0.02205   0.01387  -0.0585   1.0000   0.0606
  -3.000  -0.0879   0.01998   0.01152  -0.0583   1.0000   0.0663
  -2.750  -0.0605   0.01831   0.00962  -0.0578   1.0000   0.0710
  -2.500  -0.0333   0.01681   0.00801  -0.0574   1.0000   0.0814
  -2.250  -0.0061   0.01557   0.00672  -0.0569   1.0000   0.1011
  -2.000   0.0216   0.01425   0.00570  -0.0569   1.0000   0.1493
  -1.750   0.0504   0.01257   0.00507  -0.0575   1.0000   0.3548
  -1.500   0.0745   0.01126   0.00490  -0.0565   1.0000   0.6507
  -1.250   0.0921   0.01054   0.00460  -0.0536   1.0000   1.0000
  -1.000   0.1184   0.01069   0.00441  -0.0536   1.0000   1.0000
  -0.750   0.1441   0.01087   0.00436  -0.0537   1.0000   1.0000
  -0.500   0.1693   0.01109   0.00439  -0.0537   1.0000   1.0000
  -0.250   0.1941   0.01136   0.00451  -0.0538   1.0000   1.0000
   0.000   0.2185   0.01169   0.00470  -0.0540   1.0000   1.0000
   0.250   0.2424   0.01207   0.00499  -0.0543   1.0000   1.0000
   0.500   0.2911   0.01239   0.00521  -0.0591   0.9878   1.0000
   0.750   0.3464   0.01259   0.00535  -0.0649   0.9718   1.0000
   1.000   0.4017   0.01265   0.00539  -0.0703   0.9557   1.0000
   1.250   0.4482   0.01264   0.00539  -0.0736   0.9356   1.0000
   1.500   0.4913   0.01255   0.00534  -0.0758   0.9153   1.0000
   1.750   0.5252   0.01248   0.00528  -0.0760   0.8909   1.0000
   2.000   0.5543   0.01243   0.00522  -0.0750   0.8650   1.0000
   2.250   0.5800   0.01241   0.00519  -0.0733   0.8371   1.0000
   2.500   0.6041   0.01244   0.00518  -0.0714   0.8076   1.0000
   2.750   0.6278   0.01251   0.00523  -0.0694   0.7767   1.0000
   3.000   0.6513   0.01262   0.00527  -0.0674   0.7439   1.0000
   3.250   0.6750   0.01279   0.00536  -0.0657   0.7082   1.0000
   3.500   0.6988   0.01300   0.00548  -0.0641   0.6706   1.0000
   3.750   0.7226   0.01326   0.00568  -0.0625   0.6305   1.0000
   4.000   0.7464   0.01358   0.00587  -0.0611   0.5868   1.0000
   4.250   0.7701   0.01397   0.00611  -0.0597   0.5401   1.0000
   4.500   0.7935   0.01444   0.00641  -0.0585   0.4884   1.0000
   4.750   0.8166   0.01503   0.00679  -0.0573   0.4339   1.0000
   5.000   0.8394   0.01577   0.00733  -0.0563   0.3781   1.0000
   5.250   0.8620   0.01666   0.00794  -0.0553   0.3257   1.0000
   5.500   0.8849   0.01763   0.00870  -0.0545   0.2803   1.0000
   5.750   0.9078   0.01869   0.00955  -0.0537   0.2438   1.0000
   6.000   0.9311   0.01978   0.01059  -0.0529   0.2133   1.0000
   6.250   0.9544   0.02096   0.01167  -0.0522   0.1886   1.0000
   6.500   0.9778   0.02213   0.01279  -0.0515   0.1664   1.0000
   6.750   1.0013   0.02353   0.01420  -0.0508   0.1480   1.0000
   7.000   1.0243   0.02480   0.01558  -0.0500   0.1297   1.0000
   7.250   1.0474   0.02637   0.01721  -0.0492   0.1146   1.0000
   7.500   1.0694   0.02791   0.01884  -0.0484   0.0997   1.0000
   7.750   1.0913   0.02981   0.02090  -0.0475   0.0868   1.0000
   8.000   1.1121   0.03188   0.02322  -0.0464   0.0751   1.0000
   8.250   1.1313   0.03431   0.02596  -0.0453   0.0651   1.0000
   8.500   1.1490   0.03754   0.02938  -0.0442   0.0584   1.0000
   8.750   1.1642   0.04062   0.03309  -0.0425   0.0528   1.0000
   9.000   1.1773   0.04419   0.03668  -0.0417   0.0476   1.0000
   9.250   1.1831   0.04852   0.04181  -0.0396   0.0461   1.0000
   9.500   1.1828   0.05371   0.04763  -0.0378   0.0454   1.0000
   9.750   1.1765   0.05912   0.05357  -0.0363   0.0453   1.0000
  10.000   1.1647   0.06447   0.05931  -0.0352   0.0454   1.0000
  10.250   1.1482   0.06956   0.06470  -0.0344   0.0457   1.0000
  10.500   1.1280   0.07434   0.06967  -0.0341   0.0461   1.0000
  10.750   1.1078   0.07975   0.07523  -0.0357   0.0466   1.0000
  11.000   1.0884   0.08606   0.08163  -0.0389   0.0471   1.0000
  11.250   1.0715   0.09312   0.08876  -0.0428   0.0476   1.0000
  11.500   0.9859   0.12644   0.12209  -0.0701   0.0695   1.0000
  11.750   0.9831   0.13247   0.12811  -0.0716   0.0708   1.0000
  12.000   0.9835   0.13812   0.13375  -0.0722   0.0715   1.0000
  12.250   0.7768   0.14692   0.14257  -0.0639   0.1362   1.0000
  12.500   0.7524   0.14921   0.14482  -0.0666   0.1331   1.0000
<< Back to AG27 Bubble Dancer DLG by Mark Drela (ag27-il)

Polar data table (+)

Polar graphs


<< Back to AG27 Bubble Dancer DLG by Mark Drela (ag27-il)