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EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EH 0.0/9.0 (eh0009-il)
Reynolds number: 500,000
Max Cl/Cd: 54.98 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh0009-il-500000-n5.txt
Download as CSV file: xf-eh0009-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 0.0/9.0                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.8680   0.08047   0.07816  -0.0028   1.0000   0.0029
 -12.500  -0.8940   0.06909   0.06665  -0.0104   1.0000   0.0028
 -12.250  -0.9198   0.05876   0.05614  -0.0184   1.0000   0.0027
 -12.000  -0.9403   0.05129   0.04847  -0.0241   1.0000   0.0027
 -11.750  -0.9611   0.04543   0.04240  -0.0274   1.0000   0.0027
 -11.500  -0.9805   0.04096   0.03770  -0.0280   1.0000   0.0026
 -11.250  -0.9944   0.03782   0.03434  -0.0265   1.0000   0.0026
 -11.000  -1.0040   0.03540   0.03171  -0.0237   1.0000   0.0028
 -10.750  -1.0096   0.03274   0.02878  -0.0209   1.0000   0.0028
 -10.500  -1.0073   0.03025   0.02601  -0.0188   1.0000   0.0028
 -10.250  -1.0001   0.02807   0.02355  -0.0170   1.0000   0.0029
 -10.000  -0.9883   0.02626   0.02149  -0.0154   1.0000   0.0032
  -9.750  -0.9753   0.02446   0.01945  -0.0139   1.0000   0.0033
  -9.500  -0.9595   0.02297   0.01775  -0.0126   1.0000   0.0035
  -9.250  -0.9424   0.02162   0.01619  -0.0114   1.0000   0.0036
  -9.000  -0.9223   0.02071   0.01513  -0.0104   1.0000   0.0038
  -8.750  -0.9061   0.01913   0.01336  -0.0090   1.0000   0.0041
  -8.500  -0.8871   0.01800   0.01207  -0.0079   1.0000   0.0044
  -8.250  -0.8654   0.01728   0.01127  -0.0071   1.0000   0.0048
  -8.000  -0.8435   0.01659   0.01049  -0.0063   1.0000   0.0052
  -7.750  -0.8208   0.01600   0.00984  -0.0056   1.0000   0.0059
  -7.500  -0.7976   0.01552   0.00928  -0.0050   1.0000   0.0065
  -7.250  -0.7761   0.01476   0.00843  -0.0040   1.0000   0.0073
  -7.000  -0.7544   0.01406   0.00767  -0.0031   1.0000   0.0084
  -6.750  -0.7316   0.01353   0.00709  -0.0022   1.0000   0.0093
  -6.500  -0.7087   0.01306   0.00652  -0.0014   1.0000   0.0104
  -6.250  -0.6853   0.01273   0.00614  -0.0006   1.0000   0.0116
  -6.000  -0.6639   0.01207   0.00543   0.0005   1.0000   0.0145
  -5.750  -0.6412   0.01167   0.00499   0.0015   1.0000   0.0171
  -5.500  -0.6182   0.01133   0.00460   0.0024   1.0000   0.0199
  -5.250  -0.5959   0.01094   0.00421   0.0034   1.0000   0.0258
  -5.000  -0.5718   0.01056   0.00387   0.0040   0.9993   0.0367
  -4.750  -0.5391   0.01009   0.00350   0.0026   0.9951   0.0599
  -4.500  -0.5074   0.00965   0.00319   0.0015   0.9904   0.0900
  -4.250  -0.4748   0.00926   0.00291   0.0002   0.9854   0.1200
  -4.000  -0.4418   0.00884   0.00265  -0.0012   0.9801   0.1607
  -3.750  -0.4103   0.00848   0.00243  -0.0022   0.9722   0.1994
  -3.500  -0.3785   0.00811   0.00221  -0.0033   0.9639   0.2441
  -3.250  -0.3465   0.00777   0.00203  -0.0044   0.9547   0.2928
  -3.000  -0.3162   0.00749   0.00188  -0.0050   0.9426   0.3313
  -2.750  -0.2872   0.00723   0.00174  -0.0053   0.9287   0.3723
  -2.500  -0.2596   0.00702   0.00160  -0.0052   0.9136   0.4084
  -2.250  -0.2332   0.00685   0.00149  -0.0048   0.8972   0.4422
  -2.000  -0.2073   0.00668   0.00140  -0.0043   0.8793   0.4769
  -1.750  -0.1815   0.00656   0.00132  -0.0037   0.8603   0.5093
  -1.500  -0.1557   0.00645   0.00124  -0.0032   0.8409   0.5391
  -1.250  -0.1298   0.00636   0.00117  -0.0026   0.8208   0.5685
  -1.000  -0.1040   0.00628   0.00112  -0.0021   0.8007   0.5991
  -0.750  -0.0781   0.00621   0.00109  -0.0015   0.7790   0.6290
  -0.500  -0.0521   0.00617   0.00106  -0.0010   0.7562   0.6565
  -0.250  -0.0261   0.00616   0.00104  -0.0005   0.7323   0.6823
   0.000   0.0000   0.00615   0.00103   0.0000   0.7075   0.7074
   0.250   0.0260   0.00616   0.00104   0.0005   0.6823   0.7323
   0.500   0.0520   0.00617   0.00106   0.0010   0.6565   0.7562
   0.750   0.0780   0.00621   0.00109   0.0016   0.6291   0.7789
   1.000   0.1039   0.00628   0.00112   0.0021   0.5993   0.8007
   1.250   0.1297   0.00636   0.00117   0.0026   0.5684   0.8208
   1.500   0.1556   0.00645   0.00124   0.0032   0.5390   0.8410
   1.750   0.1815   0.00656   0.00132   0.0037   0.5094   0.8604
   2.000   0.2072   0.00668   0.00140   0.0043   0.4772   0.8793
   2.250   0.2331   0.00685   0.00149   0.0048   0.4422   0.8971
   2.500   0.2596   0.00702   0.00160   0.0052   0.4084   0.9137
   2.750   0.2871   0.00723   0.00174   0.0053   0.3723   0.9288
   3.000   0.3162   0.00749   0.00188   0.0050   0.3316   0.9426
   3.250   0.3465   0.00777   0.00203   0.0044   0.2921   0.9548
   3.500   0.3786   0.00810   0.00221   0.0033   0.2462   0.9640
   3.750   0.4104   0.00848   0.00243   0.0022   0.2002   0.9723
   4.000   0.4419   0.00885   0.00266   0.0012   0.1598   0.9803
   4.250   0.4750   0.00926   0.00291  -0.0002   0.1199   0.9855
   4.500   0.5076   0.00965   0.00319  -0.0015   0.0900   0.9906
   4.750   0.5394   0.01009   0.00350  -0.0027   0.0601   0.9953
   5.000   0.5720   0.01056   0.00387  -0.0040   0.0367   0.9995
   5.250   0.5956   0.01094   0.00421  -0.0033   0.0258   1.0000
   5.500   0.6179   0.01133   0.00460  -0.0023   0.0199   1.0000
   5.750   0.6409   0.01166   0.00498  -0.0014   0.0172   1.0000
   6.000   0.6636   0.01207   0.00542  -0.0005   0.0145   1.0000
   6.250   0.6850   0.01273   0.00614   0.0007   0.0116   1.0000
   6.500   0.7085   0.01307   0.00653   0.0014   0.0104   1.0000
   6.750   0.7315   0.01353   0.00709   0.0023   0.0093   1.0000
   7.000   0.7543   0.01406   0.00767   0.0031   0.0084   1.0000
   7.250   0.7761   0.01477   0.00844   0.0040   0.0073   1.0000
   7.500   0.7979   0.01550   0.00925   0.0049   0.0065   1.0000
   7.750   0.8211   0.01599   0.00982   0.0056   0.0058   1.0000
   8.000   0.8434   0.01663   0.01054   0.0063   0.0053   1.0000
   8.250   0.8654   0.01732   0.01131   0.0071   0.0048   1.0000
   8.500   0.8872   0.01804   0.01211   0.0079   0.0045   1.0000
   8.750   0.9065   0.01912   0.01335   0.0089   0.0041   1.0000
   9.000   0.9231   0.02064   0.01505   0.0103   0.0038   1.0000
   9.250   0.9423   0.02172   0.01630   0.0113   0.0037   1.0000
   9.500   0.9597   0.02302   0.01780   0.0125   0.0035   1.0000
   9.750   0.9757   0.02448   0.01947   0.0138   0.0033   1.0000
  10.000   0.9893   0.02619   0.02142   0.0153   0.0031   1.0000
  10.250   1.0004   0.02811   0.02359   0.0169   0.0030   1.0000
  10.500   1.0081   0.03025   0.02601   0.0187   0.0028   1.0000
  10.750   1.0100   0.03280   0.02884   0.0208   0.0028   1.0000
  11.000   1.0057   0.03535   0.03166   0.0235   0.0027   1.0000
  11.250   0.9931   0.03807   0.03461   0.0265   0.0027   1.0000
  11.500   0.9800   0.04115   0.03790   0.0278   0.0027   1.0000
  11.750   0.9603   0.04569   0.04267   0.0271   0.0027   1.0000
  12.000   0.9422   0.05119   0.04837   0.0240   0.0027   1.0000
  12.250   0.9204   0.05892   0.05630   0.0181   0.0027   1.0000
  12.500   0.8972   0.06869   0.06624   0.0105   0.0028   1.0000
  12.750   0.8677   0.08098   0.07867   0.0022   0.0029   1.0000
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