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E182 (8.47%) (e182-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E182 (8.47%) (e182-il)
Reynolds number: 1,000,000
Max Cl/Cd: 92.68 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e182-il-1000000.txt
Download as CSV file: xf-e182-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E182 (8.47%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6092   0.08212   0.08075   0.0095   1.0000   0.0095
  -8.250  -0.6175   0.07721   0.07587   0.0059   1.0000   0.0095
  -8.000  -0.6272   0.07136   0.07004   0.0005   1.0000   0.0094
  -7.750  -0.6295   0.06469   0.06316  -0.0048   0.9050   0.0096
  -7.500  -0.6319   0.05814   0.05639  -0.0075   0.8702   0.0100
  -7.250  -0.6293   0.05109   0.04908  -0.0095   0.8478   0.0104
  -7.000  -0.6166   0.04355   0.04114  -0.0098   0.8315   0.0113
  -6.750  -0.6084   0.03846   0.03565  -0.0096   0.8163   0.0113
  -6.250  -0.5919   0.02751   0.02387  -0.0084   0.7915   0.0126
  -6.000  -0.5704   0.02587   0.02204  -0.0080   0.7803   0.0131
  -5.750  -0.5483   0.02406   0.01996  -0.0074   0.7702   0.0139
  -4.750  -0.4529   0.01465   0.00912  -0.0035   0.7362   0.0109
  -4.500  -0.4281   0.01286   0.00710  -0.0027   0.7291   0.0103
  -4.250  -0.4024   0.01177   0.00586  -0.0020   0.7217   0.0101
  -4.000  -0.3764   0.01100   0.00497  -0.0015   0.7150   0.0103
  -3.750  -0.3499   0.01043   0.00430  -0.0011   0.7082   0.0107
  -3.500  -0.3229   0.01005   0.00385  -0.0009   0.7020   0.0112
  -3.250  -0.2962   0.00955   0.00326  -0.0005   0.6955   0.0116
  -3.000  -0.2696   0.00907   0.00266  -0.0002   0.6896   0.0122
  -2.750  -0.2422   0.00875   0.00228   0.0000   0.6838   0.0129
  -2.500  -0.2147   0.00852   0.00200   0.0002   0.6778   0.0143
  -2.250  -0.1870   0.00833   0.00174   0.0003   0.6723   0.0157
  -2.000  -0.1598   0.00796   0.00149   0.0006   0.6667   0.0453
  -1.750  -0.1337   0.00748   0.00131   0.0008   0.6613   0.1290
  -1.500  -0.1070   0.00713   0.00119   0.0009   0.6559   0.2003
  -1.250  -0.0806   0.00675   0.00108   0.0010   0.6504   0.2884
  -1.000  -0.0554   0.00623   0.00100   0.0013   0.6452   0.4269
  -0.750  -0.0299   0.00579   0.00094   0.0017   0.6398   0.5422
  -0.500  -0.0080   0.00514   0.00089   0.0029   0.6345   0.7255
  -0.250   0.0129   0.00455   0.00091   0.0048   0.6295   0.9031
   0.000   0.0647   0.00458   0.00100  -0.0002   0.6234   0.9651
   0.500   0.1426   0.00472   0.00103  -0.0048   0.6103   0.9880
   1.000   0.2251   0.00480   0.00102  -0.0106   0.5948   0.9978
   1.250   0.2612   0.00483   0.00100  -0.0125   0.5869   1.0000
   1.500   0.2877   0.00484   0.00099  -0.0122   0.5788   1.0000
   1.750   0.3141   0.00487   0.00098  -0.0118   0.5707   1.0000
   2.000   0.3406   0.00490   0.00099  -0.0116   0.5620   1.0000
   2.250   0.3672   0.00494   0.00101  -0.0113   0.5531   1.0000
   2.500   0.3938   0.00499   0.00104  -0.0110   0.5433   1.0000
   2.750   0.4205   0.00505   0.00107  -0.0107   0.5323   1.0000
   3.000   0.4472   0.00510   0.00111  -0.0105   0.5208   1.0000
   3.250   0.4738   0.00520   0.00116  -0.0102   0.5000   1.0000
   3.500   0.5001   0.00541   0.00122  -0.0100   0.4582   1.0000
   3.750   0.5264   0.00568   0.00133  -0.0099   0.4105   1.0000
   4.000   0.5523   0.00610   0.00150  -0.0098   0.3467   1.0000
   4.250   0.5773   0.00682   0.00183  -0.0097   0.2523   1.0000
   4.500   0.6021   0.00755   0.00218  -0.0097   0.1679   1.0000
   4.750   0.6262   0.00839   0.00261  -0.0096   0.0803   1.0000
   5.000   0.6499   0.00930   0.00315  -0.0093   0.0142   1.0000
   5.250   0.6753   0.00961   0.00348  -0.0089   0.0120   1.0000
   5.500   0.7006   0.00996   0.00388  -0.0084   0.0107   1.0000
   5.750   0.7254   0.01040   0.00439  -0.0080   0.0099   1.0000
   6.000   0.7503   0.01080   0.00484  -0.0075   0.0095   1.0000
   6.250   0.7746   0.01129   0.00540  -0.0070   0.0091   1.0000
   6.500   0.7984   0.01187   0.00605  -0.0064   0.0088   1.0000
   6.750   0.8215   0.01252   0.00678  -0.0057   0.0087   1.0000
   7.000   0.8440   0.01326   0.00759  -0.0050   0.0085   1.0000
   7.250   0.8663   0.01394   0.00833  -0.0043   0.0083   1.0000
   7.500   0.8880   0.01468   0.00914  -0.0035   0.0080   1.0000
   7.750   0.9087   0.01558   0.01011  -0.0025   0.0079   1.0000
   8.000   0.9289   0.01654   0.01114  -0.0015   0.0078   1.0000
   8.250   0.9486   0.01759   0.01229  -0.0005   0.0078   1.0000
   8.500   0.9680   0.01871   0.01350   0.0006   0.0077   1.0000
   8.750   0.9871   0.01990   0.01477   0.0017   0.0076   1.0000
   9.000   1.0056   0.02121   0.01619   0.0027   0.0074   1.0000
   9.250   1.0230   0.02277   0.01786   0.0038   0.0073   1.0000
   9.500   1.0392   0.02468   0.01994   0.0051   0.0072   1.0000
  13.500   0.6825   0.12435   0.12286  -0.0193   0.0112   1.0000
  13.750   0.6701   0.13080   0.12931  -0.0226   0.0112   1.0000
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