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E182 (8.47%) (e182-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E182 (8.47%) (e182-il)
Reynolds number: 200,000
Max Cl/Cd: 58.8 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e182-il-200000-n5.txt
Download as CSV file: xf-e182-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5905   0.09035   0.08721   0.0099   1.0000   0.0200
  -8.500  -0.5900   0.08623   0.08313   0.0078   1.0000   0.0190
  -8.250  -0.5944   0.08096   0.07791   0.0041   1.0000   0.0179
  -8.000  -0.6117   0.06925   0.06620  -0.0065   1.0000   0.0150
  -7.750  -0.6111   0.06373   0.06061  -0.0102   1.0000   0.0147
  -7.500  -0.6083   0.05787   0.05463  -0.0134   1.0000   0.0143
  -7.250  -0.6031   0.05193   0.04850  -0.0157   1.0000   0.0140
  -7.000  -0.5955   0.04589   0.04217  -0.0173   1.0000   0.0136
  -6.750  -0.5822   0.03980   0.03564  -0.0187   0.9501   0.0132
  -6.500  -0.5686   0.03465   0.02992  -0.0185   0.9134   0.0129
  -6.250  -0.5551   0.03056   0.02525  -0.0169   0.8897   0.0127
  -6.000  -0.5383   0.02728   0.02139  -0.0154   0.8714   0.0127
  -5.750  -0.5186   0.02467   0.01823  -0.0140   0.8560   0.0128
  -5.500  -0.4970   0.02258   0.01568  -0.0127   0.8424   0.0130
  -5.250  -0.4739   0.02109   0.01382  -0.0117   0.8301   0.0137
  -5.000  -0.4496   0.01989   0.01230  -0.0108   0.8188   0.0146
  -4.750  -0.4248   0.01869   0.01084  -0.0100   0.8079   0.0150
  -4.500  -0.4001   0.01757   0.00951  -0.0093   0.7981   0.0152
  -4.000  -0.3512   0.01548   0.00715  -0.0078   0.7799   0.0160
  -3.750  -0.3262   0.01477   0.00632  -0.0072   0.7717   0.0168
  -3.500  -0.3004   0.01422   0.00564  -0.0067   0.7634   0.0179
  -3.250  -0.2742   0.01375   0.00504  -0.0062   0.7556   0.0195
  -3.000  -0.2481   0.01331   0.00451  -0.0058   0.7481   0.0236
  -2.750  -0.2217   0.01285   0.00403  -0.0054   0.7408   0.0340
  -2.500  -0.1962   0.01228   0.00362  -0.0050   0.7338   0.0824
  -2.250  -0.1708   0.01172   0.00335  -0.0048   0.7270   0.1593
  -2.000  -0.1459   0.01117   0.00312  -0.0044   0.7203   0.2529
  -1.750  -0.1246   0.01023   0.00296  -0.0036   0.7141   0.4475
  -1.500  -0.1036   0.00951   0.00285  -0.0021   0.7075   0.6071
  -1.250  -0.0818   0.00891   0.00278  -0.0002   0.7022   0.7648
  -1.000  -0.0270   0.00871   0.00281  -0.0049   0.6954   0.9078
  -0.750   0.0225   0.00877   0.00275  -0.0091   0.6896   0.9591
  -0.500   0.0636   0.00883   0.00268  -0.0118   0.6834   0.9841
  -0.250   0.1096   0.00883   0.00256  -0.0158   0.6771   0.9994
   0.000   0.1362   0.00886   0.00248  -0.0155   0.6714   1.0000
   0.250   0.1621   0.00888   0.00244  -0.0152   0.6649   1.0000
   0.500   0.1877   0.00893   0.00240  -0.0147   0.6594   1.0000
   0.750   0.2139   0.00898   0.00241  -0.0144   0.6528   1.0000
   1.000   0.2398   0.00903   0.00241  -0.0140   0.6467   1.0000
   1.250   0.2659   0.00909   0.00243  -0.0137   0.6405   1.0000
   1.500   0.2920   0.00915   0.00247  -0.0134   0.6337   1.0000
   1.750   0.3181   0.00922   0.00251  -0.0130   0.6268   1.0000
   2.000   0.3442   0.00928   0.00257  -0.0126   0.6185   1.0000
   2.250   0.3704   0.00935   0.00263  -0.0122   0.6097   1.0000
   2.500   0.3964   0.00942   0.00267  -0.0118   0.6010   1.0000
   2.750   0.4227   0.00948   0.00276  -0.0114   0.5900   1.0000
   3.000   0.4489   0.00955   0.00287  -0.0111   0.5787   1.0000
   3.250   0.4751   0.00963   0.00296  -0.0107   0.5669   1.0000
   3.500   0.5012   0.00971   0.00306  -0.0103   0.5539   1.0000
   3.750   0.5273   0.00980   0.00320  -0.0099   0.5390   1.0000
   4.000   0.5534   0.00990   0.00333  -0.0095   0.5215   1.0000
   4.250   0.5791   0.01003   0.00344  -0.0090   0.4949   1.0000
   4.500   0.6039   0.01027   0.00352  -0.0084   0.4425   1.0000
   4.750   0.6281   0.01072   0.00373  -0.0080   0.3720   1.0000
   5.000   0.6493   0.01187   0.00423  -0.0077   0.2458   1.0000
   5.250   0.6710   0.01295   0.00486  -0.0074   0.1551   1.0000
   5.500   0.6923   0.01406   0.00555  -0.0071   0.0802   1.0000
   5.750   0.7137   0.01510   0.00631  -0.0066   0.0308   1.0000
   6.000   0.7363   0.01590   0.00709  -0.0060   0.0196   1.0000
   6.250   0.7595   0.01655   0.00784  -0.0054   0.0172   1.0000
   6.500   0.7820   0.01729   0.00867  -0.0047   0.0157   1.0000
   6.750   0.8033   0.01819   0.00967  -0.0040   0.0144   1.0000
   7.000   0.8249   0.01896   0.01057  -0.0033   0.0133   1.0000
   7.250   0.8454   0.01989   0.01164  -0.0025   0.0126   1.0000
   7.500   0.8647   0.02095   0.01281  -0.0016   0.0121   1.0000
   7.750   0.8833   0.02208   0.01404  -0.0006   0.0117   1.0000
   8.000   0.9013   0.02332   0.01538   0.0005   0.0114   1.0000
   8.250   0.9189   0.02465   0.01680   0.0016   0.0111   1.0000
   8.500   0.9363   0.02608   0.01835   0.0027   0.0109   1.0000
   8.750   0.9534   0.02769   0.02008   0.0038   0.0107   1.0000
   9.000   0.9703   0.02945   0.02203   0.0049   0.0106   1.0000
   9.250   0.9864   0.03138   0.02415   0.0060   0.0105   1.0000
   9.500   1.0009   0.03359   0.02660   0.0071   0.0105   1.0000
   9.750   1.0132   0.03589   0.02916   0.0083   0.0104   1.0000
  10.000   1.0212   0.03864   0.03220   0.0097   0.0103   1.0000
  10.500   1.0199   0.04479   0.03894   0.0129   0.0100   1.0000
  10.750   1.0134   0.04685   0.04129   0.0148   0.0098   1.0000
  11.000   1.0044   0.04992   0.04461   0.0156   0.0097   1.0000
  11.250   0.9945   0.05337   0.04829   0.0156   0.0097   1.0000
  11.500   0.9827   0.05726   0.05241   0.0148   0.0096   1.0000
  11.750   0.9683   0.06194   0.05730   0.0131   0.0096   1.0000
  12.000   0.9532   0.06710   0.06265   0.0107   0.0096   1.0000
  12.250   0.9372   0.07287   0.06860   0.0075   0.0096   1.0000
  12.500   0.9198   0.07948   0.07537   0.0035   0.0097   1.0000
  12.750   0.9006   0.08717   0.08318  -0.0014   0.0098   1.0000
  13.000   0.8843   0.09501   0.09113  -0.0064   0.0099   1.0000
  13.250   0.8612   0.10601   0.10225  -0.0137   0.0099   1.0000
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