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E182 (8.47%) (e182-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E182 (8.47%) (e182-il)
Reynolds number: 500,000
Max Cl/Cd: 81.91 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e182-il-500000.txt
Download as CSV file: xf-e182-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6000   0.08449   0.08256   0.0088   1.0000   0.0178
  -8.250  -0.6035   0.08001   0.07812   0.0056   1.0000   0.0179
  -8.000  -0.6115   0.07492   0.07307   0.0010   1.0000   0.0179
  -7.750  -0.6102   0.06973   0.06786  -0.0037   1.0000   0.0183
  -7.500  -0.6064   0.06427   0.06233  -0.0079   1.0000   0.0190
  -7.250  -0.6002   0.05847   0.05644  -0.0115   1.0000   0.0195
  -7.000  -0.5906   0.05218   0.04997  -0.0145   1.0000   0.0210
  -6.750  -0.5718   0.04774   0.04499  -0.0154   0.9162   0.0228
  -6.500  -0.5661   0.02725   0.02416  -0.0113   0.8467   0.0236
  -6.250  -0.5535   0.02360   0.02041  -0.0112   0.8340   0.0244
  -6.000  -0.5363   0.02127   0.01793  -0.0109   0.8222   0.0253
  -5.750  -0.5178   0.01912   0.01560  -0.0106   0.8116   0.0273
  -5.500  -0.4900   0.01961   0.01568  -0.0094   0.8009   0.0316
  -5.250  -0.4817   0.01265   0.00823  -0.0092   0.7934   0.0337
  -5.000  -0.4597   0.01098   0.00645  -0.0089   0.7851   0.0350
  -4.750  -0.4417   0.01769   0.01157  -0.0066   0.7953   0.0166
  -4.500  -0.4160   0.01621   0.00991  -0.0059   0.7865   0.0159
  -4.250  -0.3907   0.01458   0.00805  -0.0052   0.7777   0.0158
  -4.000  -0.3648   0.01352   0.00684  -0.0046   0.7694   0.0159
  -3.750  -0.3387   0.01281   0.00599  -0.0040   0.7617   0.0162
  -3.500  -0.3140   0.01165   0.00472  -0.0033   0.7538   0.0169
  -3.250  -0.2883   0.01101   0.00396  -0.0028   0.7468   0.0182
  -3.000  -0.2613   0.01062   0.00353  -0.0025   0.7394   0.0201
  -2.750  -0.2344   0.01028   0.00307  -0.0022   0.7329   0.0216
  -2.500  -0.2070   0.00992   0.00265  -0.0019   0.7259   0.0260
  -2.250  -0.1816   0.00923   0.00226  -0.0015   0.7196   0.1061
  -2.000  -0.1559   0.00869   0.00208  -0.0013   0.7133   0.2022
  -1.750  -0.1309   0.00809   0.00193  -0.0010   0.7069   0.3303
  -1.500  -0.1068   0.00749   0.00181  -0.0004   0.7012   0.4738
  -1.250  -0.0857   0.00672   0.00172   0.0008   0.6950   0.6612
  -1.000  -0.0648   0.00598   0.00174   0.0030   0.6897   0.8795
  -0.750   0.0008   0.00606   0.00186  -0.0045   0.6835   0.9669
  -0.500   0.0430   0.00617   0.00186  -0.0074   0.6775   0.9848
  -0.250   0.0919   0.00623   0.00182  -0.0119   0.6717   0.9952
   0.000   0.1323   0.00622   0.00174  -0.0147   0.6653   1.0000
   0.250   0.1580   0.00625   0.00168  -0.0143   0.6599   1.0000
   0.500   0.1842   0.00624   0.00165  -0.0140   0.6533   1.0000
   0.750   0.2101   0.00627   0.00161  -0.0135   0.6472   1.0000
   1.000   0.2363   0.00629   0.00160  -0.0132   0.6401   1.0000
   1.250   0.2624   0.00632   0.00158  -0.0128   0.6330   1.0000
   1.500   0.2888   0.00634   0.00159  -0.0125   0.6253   1.0000
   1.750   0.3149   0.00638   0.00158  -0.0121   0.6179   1.0000
   2.000   0.3415   0.00640   0.00161  -0.0118   0.6092   1.0000
   2.250   0.3678   0.00645   0.00163  -0.0114   0.6013   1.0000
   2.500   0.3943   0.00648   0.00166  -0.0111   0.5920   1.0000
   2.750   0.4208   0.00652   0.00171  -0.0108   0.5830   1.0000
   3.000   0.4473   0.00658   0.00174  -0.0105   0.5731   1.0000
   3.250   0.4739   0.00663   0.00181  -0.0102   0.5618   1.0000
   3.500   0.5005   0.00668   0.00188  -0.0099   0.5501   1.0000
   3.750   0.5269   0.00676   0.00193  -0.0096   0.5325   1.0000
   4.000   0.5531   0.00687   0.00198  -0.0092   0.5006   1.0000
   4.250   0.5791   0.00707   0.00208  -0.0089   0.4598   1.0000
   4.500   0.6045   0.00747   0.00224  -0.0087   0.3931   1.0000
   4.750   0.6288   0.00823   0.00258  -0.0086   0.2963   1.0000
   5.000   0.6523   0.00915   0.00306  -0.0085   0.1995   1.0000
   5.250   0.6748   0.01026   0.00367  -0.0083   0.0984   1.0000
   5.500   0.6964   0.01151   0.00445  -0.0079   0.0206   1.0000
   5.750   0.7211   0.01197   0.00495  -0.0074   0.0172   1.0000
   6.000   0.7452   0.01255   0.00560  -0.0068   0.0153   1.0000
   6.250   0.7683   0.01329   0.00646  -0.0061   0.0143   1.0000
   6.500   0.7913   0.01398   0.00723  -0.0054   0.0138   1.0000
   6.750   0.8132   0.01480   0.00815  -0.0046   0.0135   1.0000
   7.000   0.8341   0.01575   0.00919  -0.0037   0.0132   1.0000
   7.250   0.8542   0.01681   0.01035  -0.0026   0.0131   1.0000
   7.500   0.8735   0.01805   0.01169  -0.0014   0.0132   1.0000
   7.750   0.8931   0.01929   0.01304  -0.0003   0.0131   1.0000
   8.000   0.9135   0.02039   0.01423   0.0007   0.0126   1.0000
   8.250   0.9333   0.02182   0.01577   0.0018   0.0125   1.0000
   8.500   0.9525   0.02364   0.01776   0.0030   0.0127   1.0000
   8.750   0.9708   0.02594   0.02029   0.0043   0.0129   1.0000
   9.000   0.9863   0.02897   0.02362   0.0057   0.0135   1.0000
  13.750   0.7755   0.14606   0.14370  -0.0291   0.0206   1.0000
  14.000   0.7752   0.15245   0.15007  -0.0322   0.0205   1.0000
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