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E186 (10.27%) (e186-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E186 (10.27%) (e186-il)
Reynolds number: 1,000,000
Max Cl/Cd: 90.72 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e186-il-1000000.txt
Download as CSV file: xf-e186-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E186  (10.27%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.8005   0.05984   0.05843   0.0041   1.0000   0.0079
  -9.750  -0.8348   0.05363   0.05206   0.0031   1.0000   0.0078
  -9.500  -0.8677   0.04862   0.04685   0.0064   1.0000   0.0077
  -9.250  -0.8931   0.04187   0.03971   0.0094   1.0000   0.0077
  -9.000  -0.9013   0.03678   0.03422   0.0122   1.0000   0.0078
  -8.750  -0.8981   0.03336   0.03034   0.0147   1.0000   0.0083
  -8.500  -0.9060   0.02870   0.02509   0.0192   0.8892   0.0087
  -8.250  -0.8909   0.02761   0.02379   0.0209   0.8491   0.0090
  -8.000  -0.8737   0.02628   0.02221   0.0223   0.8188   0.0092
  -7.750  -0.8529   0.02553   0.02132   0.0232   0.7933   0.0096
  -7.500  -0.8338   0.02404   0.01955   0.0245   0.7723   0.0099
  -7.250  -0.8146   0.02221   0.01742   0.0259   0.7541   0.0102
  -7.000  -0.7937   0.02063   0.01556   0.0271   0.7376   0.0104
  -6.750  -0.7715   0.01926   0.01395   0.0282   0.7227   0.0107
  -6.500  -0.7481   0.01814   0.01262   0.0290   0.7094   0.0110
  -6.250  -0.7236   0.01732   0.01163   0.0297   0.6972   0.0114
  -6.000  -0.6971   0.01734   0.01154   0.0301   0.6856   0.0119
  -5.750  -0.6758   0.01514   0.00907   0.0313   0.6756   0.0125
  -5.500  -0.6526   0.01396   0.00777   0.0323   0.6665   0.0129
  -5.250  -0.6284   0.01319   0.00690   0.0330   0.6578   0.0132
  -5.000  -0.6036   0.01256   0.00621   0.0337   0.6492   0.0137
  -4.750  -0.5786   0.01202   0.00558   0.0343   0.6417   0.0140
  -4.500  -0.5533   0.01153   0.00500   0.0349   0.6343   0.0144
  -4.250  -0.5274   0.01116   0.00456   0.0353   0.6276   0.0152
  -4.000  -0.5015   0.01076   0.00409   0.0359   0.6207   0.0158
  -3.750  -0.4753   0.01043   0.00367   0.0363   0.6146   0.0165
  -3.500  -0.4487   0.01014   0.00333   0.0367   0.6085   0.0170
  -3.250  -0.4221   0.00988   0.00299   0.0370   0.6025   0.0174
  -3.000  -0.3955   0.00957   0.00261   0.0374   0.5970   0.0186
  -2.750  -0.3685   0.00935   0.00233   0.0378   0.5913   0.0206
  -2.250  -0.3172   0.00855   0.00184   0.0387   0.5808   0.0996
  -2.000  -0.2920   0.00814   0.00167   0.0391   0.5756   0.1660
  -1.750  -0.2668   0.00777   0.00153   0.0396   0.5707   0.2351
  -1.500  -0.2421   0.00732   0.00139   0.0401   0.5658   0.3235
  -1.250  -0.2182   0.00686   0.00127   0.0408   0.5607   0.4257
  -1.000  -0.1947   0.00644   0.00118   0.0416   0.5561   0.5271
  -0.750  -0.1737   0.00589   0.00109   0.0430   0.5515   0.6510
  -0.500  -0.1575   0.00525   0.00100   0.0457   0.5468   0.8012
  -0.250  -0.0810   0.00510   0.00125   0.0354   0.5408   0.9344
   0.000  -0.0443   0.00526   0.00139   0.0337   0.5356   0.9481
   0.250  -0.0153   0.00543   0.00149   0.0337   0.5306   0.9595
   0.500   0.0220   0.00559   0.00161   0.0318   0.5256   0.9652
   0.750   0.0524   0.00572   0.00172   0.0314   0.5205   0.9719
   1.000   0.0919   0.00585   0.00178   0.0290   0.5151   0.9743
   1.250   0.1298   0.00595   0.00187   0.0268   0.5098   0.9776
   1.500   0.1624   0.00610   0.00198   0.0259   0.5040   0.9825
   1.750   0.2007   0.00617   0.00202   0.0237   0.4976   0.9846
   2.000   0.2403   0.00620   0.00203   0.0212   0.4903   0.9865
   2.250   0.2787   0.00625   0.00204   0.0189   0.4833   0.9888
   2.500   0.3159   0.00628   0.00206   0.0168   0.4757   0.9916
   2.750   0.3511   0.00635   0.00211   0.0152   0.4679   0.9943
   3.000   0.3897   0.00630   0.00205   0.0129   0.4592   0.9960
   3.250   0.4271   0.00627   0.00202   0.0107   0.4504   0.9980
   3.500   0.4637   0.00626   0.00199   0.0088   0.4405   0.9998
   3.750   0.4908   0.00629   0.00201   0.0088   0.4311   1.0000
   4.000   0.5168   0.00633   0.00206   0.0092   0.4214   1.0000
   4.250   0.5429   0.00639   0.00211   0.0094   0.4096   1.0000
   4.500   0.5690   0.00648   0.00216   0.0097   0.3924   1.0000
   4.750   0.5951   0.00664   0.00224   0.0099   0.3651   1.0000
   5.000   0.6214   0.00685   0.00236   0.0100   0.3347   1.0000
   5.250   0.6475   0.00734   0.00258   0.0099   0.2709   1.0000
   5.500   0.6734   0.00798   0.00291   0.0097   0.2027   1.0000
   5.750   0.6993   0.00852   0.00324   0.0095   0.1538   1.0000
   6.000   0.7250   0.00908   0.00360   0.0094   0.1099   1.0000
   6.250   0.7504   0.00964   0.00398   0.0094   0.0725   1.0000
   6.500   0.7754   0.01024   0.00441   0.0094   0.0404   1.0000
   6.750   0.7996   0.01111   0.00508   0.0095   0.0111   1.0000
   7.000   0.8243   0.01160   0.00561   0.0098   0.0088   1.0000
   7.250   0.8488   0.01200   0.00607   0.0102   0.0081   1.0000
   7.500   0.8730   0.01246   0.00658   0.0106   0.0076   1.0000
   7.750   0.8967   0.01296   0.00714   0.0110   0.0072   1.0000
   8.000   0.9197   0.01354   0.00777   0.0115   0.0068   1.0000
   8.250   0.9415   0.01431   0.00862   0.0120   0.0064   1.0000
   8.500   0.9597   0.01563   0.01009   0.0129   0.0060   1.0000
   8.750   0.9803   0.01636   0.01090   0.0137   0.0059   1.0000
   9.000   0.9998   0.01715   0.01177   0.0145   0.0057   1.0000
   9.250   1.0184   0.01798   0.01268   0.0155   0.0055   1.0000
   9.500   1.0346   0.01903   0.01382   0.0167   0.0054   1.0000
   9.750   1.0493   0.02013   0.01502   0.0181   0.0052   1.0000
  10.000   1.0619   0.02135   0.01633   0.0197   0.0052   1.0000
  10.250   1.0720   0.02272   0.01781   0.0216   0.0051   1.0000
  10.500   1.0802   0.02414   0.01934   0.0236   0.0051   1.0000
  10.750   1.0854   0.02575   0.02109   0.0258   0.0051   1.0000
  11.000   1.0822   0.02727   0.02272   0.0291   0.0051   1.0000
  11.250   1.0770   0.02908   0.02465   0.0319   0.0052   1.0000
  11.500   1.0757   0.03109   0.02679   0.0336   0.0052   1.0000
  11.750   1.0732   0.03350   0.02936   0.0350   0.0052   1.0000
  12.000   1.0741   0.03558   0.03154   0.0357   0.0051   1.0000
  12.250   1.0719   0.03817   0.03428   0.0362   0.0051   1.0000
  12.500   1.0717   0.04058   0.03679   0.0362   0.0050   1.0000
  12.750   1.0678   0.04356   0.03990   0.0361   0.0049   1.0000
  13.000   1.0541   0.04797   0.04454   0.0357   0.0050   1.0000
  13.250   1.0444   0.05195   0.04867   0.0348   0.0051   1.0000
  13.500   1.0323   0.05641   0.05329   0.0335   0.0051   1.0000
  13.750   1.0149   0.06182   0.05888   0.0316   0.0053   1.0000
  14.000   1.0014   0.06691   0.06410   0.0294   0.0053   1.0000
  14.250   0.9862   0.07261   0.06994   0.0268   0.0053   1.0000
  14.500   0.9629   0.08020   0.07770   0.0230   0.0054   1.0000
  14.750   0.9409   0.08816   0.08581   0.0187   0.0055   1.0000
  15.000   0.9228   0.09584   0.09360   0.0145   0.0055   1.0000
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