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E205 (10.48%) (e205-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E205 (10.48%) (e205-il)
Reynolds number: 200,000
Max Cl/Cd: 74.02 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e205-il-200000-n5.txt
Download as CSV file: xf-e205-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E205  (10.48%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4235   0.08575   0.08227  -0.0308   1.0000   0.0189
  -9.000  -0.4255   0.08170   0.07826  -0.0326   1.0000   0.0186
  -8.750  -0.4298   0.07729   0.07390  -0.0347   1.0000   0.0184
  -8.500  -0.4375   0.07261   0.06930  -0.0373   1.0000   0.0182
  -8.250  -0.4504   0.06785   0.06461  -0.0403   1.0000   0.0180
  -8.000  -0.4610   0.06184   0.05861  -0.0442   1.0000   0.0178
  -7.750  -0.4703   0.05574   0.05243  -0.0465   1.0000   0.0175
  -7.500  -0.4814   0.04928   0.04580  -0.0471   1.0000   0.0173
  -7.250  -0.4775   0.04120   0.03727  -0.0503   0.9897   0.0171
  -7.000  -0.4603   0.03444   0.02987  -0.0533   0.9749   0.0171
  -6.750  -0.4383   0.03008   0.02493  -0.0547   0.9593   0.0175
  -6.500  -0.4121   0.02709   0.02138  -0.0557   0.9431   0.0184
  -6.250  -0.3839   0.02467   0.01847  -0.0565   0.9253   0.0188
  -6.000  -0.3545   0.02250   0.01587  -0.0573   0.9061   0.0189
  -5.750  -0.3245   0.02078   0.01376  -0.0579   0.8860   0.0190
  -5.500  -0.2966   0.01942   0.01209  -0.0578   0.8641   0.0192
  -5.250  -0.2703   0.01817   0.01060  -0.0574   0.8426   0.0195
  -5.000  -0.2460   0.01696   0.00919  -0.0567   0.8217   0.0201
  -4.750  -0.2219   0.01610   0.00817  -0.0559   0.8021   0.0207
  -4.500  -0.1976   0.01545   0.00737  -0.0551   0.7842   0.0215
  -4.250  -0.1730   0.01491   0.00667  -0.0543   0.7675   0.0225
  -4.000  -0.1480   0.01451   0.00613  -0.0537   0.7519   0.0242
  -3.750  -0.1228   0.01414   0.00561  -0.0530   0.7377   0.0262
  -3.500  -0.0978   0.01370   0.00502  -0.0524   0.7246   0.0279
  -3.250  -0.0724   0.01334   0.00456  -0.0518   0.7122   0.0308
  -3.000  -0.0466   0.01301   0.00413  -0.0512   0.7004   0.0376
  -2.750  -0.0213   0.01262   0.00378  -0.0507   0.6896   0.0638
  -2.500   0.0041   0.01228   0.00354  -0.0502   0.6796   0.1048
  -2.250   0.0290   0.01191   0.00335  -0.0498   0.6699   0.1671
  -2.000   0.0536   0.01150   0.00320  -0.0494   0.6606   0.2474
  -1.500   0.1005   0.01062   0.00301  -0.0479   0.6437   0.4623
  -1.250   0.1223   0.01017   0.00295  -0.0466   0.6361   0.5854
  -1.000   0.1434   0.00968   0.00295  -0.0448   0.6285   0.7320
  -0.750   0.1902   0.00946   0.00302  -0.0478   0.6206   0.8827
  -0.500   0.2441   0.00955   0.00298  -0.0529   0.6127   0.9475
  -0.250   0.2846   0.00964   0.00296  -0.0554   0.6050   0.9748
   0.000   0.3287   0.00970   0.00287  -0.0589   0.5978   0.9911
   0.250   0.3691   0.00973   0.00280  -0.0617   0.5904   1.0000
   0.500   0.3934   0.00982   0.00278  -0.0610   0.5840   1.0000
   0.750   0.4180   0.00989   0.00279  -0.0604   0.5775   1.0000
   1.000   0.4426   0.00998   0.00281  -0.0597   0.5712   1.0000
   1.250   0.4673   0.01008   0.00284  -0.0591   0.5653   1.0000
   1.500   0.4920   0.01017   0.00289  -0.0585   0.5587   1.0000
   1.750   0.5167   0.01030   0.00294  -0.0578   0.5533   1.0000
   2.000   0.5417   0.01039   0.00303  -0.0573   0.5466   1.0000
   2.250   0.5665   0.01052   0.00311  -0.0567   0.5408   1.0000
   2.500   0.5914   0.01064   0.00323  -0.0561   0.5348   1.0000
   2.750   0.6163   0.01076   0.00334  -0.0555   0.5285   1.0000
   3.000   0.6412   0.01090   0.00345  -0.0549   0.5227   1.0000
   3.250   0.6661   0.01102   0.00359  -0.0543   0.5158   1.0000
   3.500   0.6909   0.01118   0.00373  -0.0537   0.5099   1.0000
   3.750   0.7157   0.01130   0.00390  -0.0531   0.5022   1.0000
   4.000   0.7402   0.01145   0.00404  -0.0524   0.4951   1.0000
   4.250   0.7648   0.01159   0.00421  -0.0518   0.4862   1.0000
   4.500   0.7892   0.01173   0.00440  -0.0511   0.4776   1.0000
   4.750   0.8134   0.01189   0.00456  -0.0504   0.4687   1.0000
   5.000   0.8377   0.01204   0.00476  -0.0497   0.4584   1.0000
   5.250   0.8618   0.01220   0.00496  -0.0490   0.4482   1.0000
   5.500   0.8856   0.01238   0.00516  -0.0482   0.4375   1.0000
   5.750   0.9092   0.01257   0.00539  -0.0474   0.4253   1.0000
   6.000   0.9327   0.01277   0.00563  -0.0466   0.4118   1.0000
   6.250   0.9558   0.01299   0.00588  -0.0458   0.3966   1.0000
   6.500   0.9787   0.01323   0.00616  -0.0449   0.3794   1.0000
   6.750   1.0008   0.01352   0.00646  -0.0439   0.3586   1.0000
   7.000   1.0218   0.01388   0.00682  -0.0428   0.3325   1.0000
   7.250   1.0412   0.01436   0.00721  -0.0415   0.3000   1.0000
   7.500   1.0582   0.01503   0.00772  -0.0399   0.2587   1.0000
   7.750   1.0719   0.01596   0.00840  -0.0380   0.2098   1.0000
   8.000   1.0845   0.01701   0.00920  -0.0360   0.1656   1.0000
   8.250   1.0978   0.01798   0.01003  -0.0341   0.1326   1.0000
   8.500   1.1099   0.01901   0.01089  -0.0321   0.1014   1.0000
   8.750   1.1225   0.01996   0.01174  -0.0302   0.0795   1.0000
   9.000   1.1341   0.02092   0.01262  -0.0281   0.0608   1.0000
   9.250   1.1448   0.02190   0.01355  -0.0259   0.0466   1.0000
   9.500   1.1535   0.02287   0.01451  -0.0235   0.0353   1.0000
   9.750   1.1580   0.02397   0.01561  -0.0204   0.0255   1.0000
  10.000   1.1615   0.02522   0.01686  -0.0176   0.0194   1.0000
  10.250   1.1647   0.02658   0.01827  -0.0150   0.0154   1.0000
  10.500   1.1688   0.02800   0.01979  -0.0129   0.0141   1.0000
  10.750   1.1740   0.02944   0.02134  -0.0112   0.0124   1.0000
  11.000   1.1776   0.03111   0.02312  -0.0097   0.0116   1.0000
  11.250   1.1799   0.03303   0.02514  -0.0084   0.0110   1.0000
  11.500   1.1790   0.03536   0.02760  -0.0074   0.0104   1.0000
  11.750   1.1807   0.03758   0.02994  -0.0066   0.0102   1.0000
  12.000   1.1814   0.04001   0.03251  -0.0061   0.0099   1.0000
  12.250   1.1820   0.04254   0.03518  -0.0057   0.0097   1.0000
  12.500   1.1819   0.04522   0.03799  -0.0055   0.0095   1.0000
  12.750   1.1808   0.04810   0.04101  -0.0055   0.0093   1.0000
  13.000   1.1797   0.05103   0.04407  -0.0055   0.0092   1.0000
  13.250   1.1779   0.05412   0.04728  -0.0057   0.0090   1.0000
  13.500   1.1760   0.05728   0.05058  -0.0059   0.0088   1.0000
  13.750   1.1736   0.06057   0.05402  -0.0063   0.0087   1.0000
  14.000   1.1720   0.06386   0.05744  -0.0067   0.0086   1.0000
  14.250   1.1694   0.06737   0.06108  -0.0074   0.0085   1.0000
  14.500   1.1669   0.07099   0.06483  -0.0081   0.0083   1.0000
  14.750   1.1645   0.07471   0.06869  -0.0089   0.0083   1.0000
  15.000   1.1616   0.07858   0.07270  -0.0100   0.0082   1.0000
  15.250   1.1583   0.08263   0.07689  -0.0112   0.0081   1.0000
  15.500   1.1534   0.08710   0.08149  -0.0128   0.0079   1.0000
  15.750   1.1485   0.09167   0.08622  -0.0144   0.0079   1.0000
  16.000   1.1429   0.09651   0.09120  -0.0164   0.0078   1.0000
  16.250   1.1366   0.10160   0.09642  -0.0187   0.0077   1.0000
  16.500   1.1290   0.10709   0.10207  -0.0212   0.0076   1.0000
  16.750   1.1211   0.11277   0.10791  -0.0240   0.0076   1.0000
  17.000   1.1122   0.11879   0.11404  -0.0271   0.0074   1.0000
  17.250   1.1027   0.12528   0.12073  -0.0306   0.0075   1.0000
  17.500   1.0932   0.13184   0.12741  -0.0343   0.0073   1.0000
  17.750   1.0826   0.13894   0.13466  -0.0384   0.0073   1.0000
  18.000   1.0707   0.14658   0.14245  -0.0429   0.0073   1.0000
  18.250   1.0574   0.15505   0.15109  -0.0480   0.0073   1.0000
  18.500   1.0271   0.16953   0.16587  -0.0565   0.0078   1.0000
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