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E475 (15.01%) (e475-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E475 (15.01%) (e475-il)
Reynolds number: 100,000
Max Cl/Cd: 30.54 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e475-il-100000.txt
Download as CSV file: xf-e475-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E475  (15.01%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.8180   0.06658   0.06037  -0.0421   1.0000   0.1913
 -11.500  -0.8647   0.05995   0.05368  -0.0420   1.0000   0.1930
 -11.250  -0.8963   0.05613   0.04979  -0.0391   1.0000   0.1952
 -11.000  -0.9609   0.05127   0.04475  -0.0316   1.0000   0.1958
 -10.750  -0.9802   0.04885   0.04218  -0.0269   1.0000   0.1990
 -10.500  -1.0117   0.04564   0.03865  -0.0207   1.0000   0.2021
 -10.250  -1.0416   0.04255   0.03511  -0.0139   1.0000   0.2054
 -10.000  -1.0038   0.04278   0.03559  -0.0147   1.0000   0.2098
  -9.750  -0.9919   0.04199   0.03475  -0.0123   1.0000   0.2144
  -9.500  -1.0036   0.03980   0.03220  -0.0073   1.0000   0.2191
  -9.250  -0.9987   0.03817   0.03041  -0.0042   1.0000   0.2231
  -9.000  -0.9752   0.03786   0.03021  -0.0033   1.0000   0.2275
  -8.750  -0.9668   0.03671   0.02890  -0.0004   1.0000   0.2325
  -8.500  -0.9708   0.03492   0.02664   0.0040   1.0000   0.2375
  -8.250  -0.9472   0.03418   0.02606   0.0048   1.0000   0.2417
  -8.000  -0.9297   0.03350   0.02536   0.0065   1.0000   0.2467
  -7.750  -0.9225   0.03223   0.02378   0.0096   1.0000   0.2522
  -7.500  -0.9068   0.03113   0.02261   0.0114   1.0000   0.2567
  -7.250  -0.8869   0.03050   0.02200   0.0128   1.0000   0.2615
  -7.000  -0.8725   0.02961   0.02094   0.0150   1.0000   0.2672
  -6.750  -0.8583   0.02855   0.01969   0.0171   1.0000   0.2724
  -6.500  -0.8376   0.02791   0.01911   0.0183   1.0000   0.2771
  -6.250  -0.8198   0.02720   0.01829   0.0200   1.0000   0.2827
  -6.000  -0.8043   0.02635   0.01721   0.0220   1.0000   0.2885
  -5.750  -0.7828   0.02572   0.01668   0.0231   1.0000   0.2934
  -5.500  -0.7637   0.02512   0.01600   0.0246   1.0000   0.2993
  -5.250  -0.7462   0.02443   0.01511   0.0263   1.0000   0.3052
  -5.000  -0.7245   0.02387   0.01466   0.0273   1.0000   0.3106
  -4.750  -0.7049   0.02338   0.01409   0.0287   1.0000   0.3170
  -4.500  -0.6855   0.02281   0.01341   0.0301   1.0000   0.3231
  -4.250  -0.6640   0.02235   0.01305   0.0311   1.0000   0.3287
  -4.000  -0.6443   0.02197   0.01258   0.0324   1.0000   0.3360
  -3.750  -0.6236   0.02152   0.01216   0.0335   1.0000   0.3425
  -3.500  -0.6032   0.02118   0.01186   0.0347   1.0000   0.3495
  -3.250  -0.5836   0.02084   0.01144   0.0360   1.0000   0.3569
  -3.000  -0.5632   0.02050   0.01124   0.0370   1.0000   0.3640
  -2.750  -0.5445   0.02029   0.01095   0.0383   1.0000   0.3729
  -2.500  -0.5249   0.01998   0.01082   0.0394   1.0000   0.3806
  -2.250  -0.5031   0.01985   0.01065   0.0399   0.9988   0.3906
  -2.000  -0.4424   0.01990   0.01086   0.0332   0.9840   0.4069
  -1.750  -0.3834   0.01977   0.01090   0.0270   0.9692   0.4253
  -1.500  -0.3265   0.01940   0.01078   0.0215   0.9540   0.4459
  -1.250  -0.2719   0.01886   0.01051   0.0167   0.9381   0.4721
  -1.000  -0.2248   0.01815   0.01010   0.0136   0.9190   0.5029
  -0.750  -0.1799   0.01733   0.00964   0.0112   0.8984   0.5456
  -0.500  -0.1332   0.01631   0.00915   0.0090   0.8771   0.6078
  -0.250  -0.0869   0.01533   0.00878   0.0075   0.8498   0.6999
   0.000   0.0000   0.01497   0.00887   0.0000   0.8041   0.8042
   0.250   0.0869   0.01533   0.00878  -0.0075   0.6998   0.8499
   0.500   0.1333   0.01632   0.00915  -0.0090   0.6076   0.8772
   0.750   0.1799   0.01734   0.00964  -0.0112   0.5454   0.8985
   1.000   0.2248   0.01816   0.01011  -0.0136   0.5029   0.9191
   1.250   0.2719   0.01886   0.01051  -0.0166   0.4721   0.9381
   1.500   0.3263   0.01939   0.01078  -0.0214   0.4459   0.9540
   1.750   0.3832   0.01977   0.01090  -0.0270   0.4254   0.9692
   2.000   0.4423   0.01990   0.01086  -0.0332   0.4070   0.9840
   2.250   0.5032   0.01984   0.01064  -0.0399   0.3906   0.9989
   2.500   0.5247   0.01997   0.01082  -0.0394   0.3806   1.0000
   2.750   0.5444   0.02029   0.01095  -0.0383   0.3730   1.0000
   3.000   0.5630   0.02050   0.01124  -0.0370   0.3640   1.0000
   3.250   0.5835   0.02084   0.01144  -0.0359   0.3569   1.0000
   3.500   0.6031   0.02118   0.01186  -0.0347   0.3494   1.0000
   3.750   0.6235   0.02151   0.01216  -0.0335   0.3425   1.0000
   4.000   0.6442   0.02197   0.01257  -0.0324   0.3359   1.0000
   4.250   0.6639   0.02235   0.01305  -0.0311   0.3288   1.0000
   4.500   0.6853   0.02281   0.01341  -0.0300   0.3231   1.0000
   4.750   0.7048   0.02338   0.01409  -0.0287   0.3171   1.0000
   5.000   0.7244   0.02386   0.01465  -0.0273   0.3105   1.0000
   5.250   0.7461   0.02443   0.01510  -0.0262   0.3052   1.0000
   5.500   0.7636   0.02512   0.01600  -0.0246   0.2993   1.0000
   5.750   0.7827   0.02572   0.01668  -0.0231   0.2935   1.0000
   6.000   0.8041   0.02634   0.01720  -0.0220   0.2885   1.0000
   6.250   0.8197   0.02719   0.01828  -0.0200   0.2828   1.0000
   6.500   0.8375   0.02791   0.01910  -0.0183   0.2771   1.0000
   6.750   0.8582   0.02854   0.01968  -0.0171   0.2723   1.0000
   7.000   0.8724   0.02960   0.02093  -0.0150   0.2672   1.0000
   7.250   0.8867   0.03049   0.02200  -0.0128   0.2615   1.0000
   7.500   0.9067   0.03112   0.02260  -0.0114   0.2567   1.0000
   7.750   0.9225   0.03222   0.02377  -0.0096   0.2522   1.0000
   8.000   0.9296   0.03349   0.02535  -0.0065   0.2467   1.0000
   8.250   0.9471   0.03417   0.02605  -0.0048   0.2418   1.0000
   8.500   0.9706   0.03492   0.02664  -0.0040   0.2375   1.0000
   8.750   0.9668   0.03671   0.02890   0.0004   0.2326   1.0000
   9.000   0.9750   0.03787   0.03021   0.0033   0.2276   1.0000
   9.250   0.9987   0.03816   0.03040   0.0042   0.2231   1.0000
   9.500   1.0033   0.03979   0.03220   0.0073   0.2190   1.0000
   9.750   0.9919   0.04198   0.03475   0.0123   0.2145   1.0000
  10.000   1.0041   0.04275   0.03556   0.0146   0.2098   1.0000
  10.250   1.0424   0.04251   0.03505   0.0138   0.2053   1.0000
  10.500   1.0119   0.04560   0.03861   0.0207   0.2021   1.0000
  10.750   0.9805   0.04884   0.04216   0.0269   0.1990   1.0000
  11.000   0.9614   0.05125   0.04473   0.0315   0.1957   1.0000
  11.250   0.8887   0.05662   0.05029   0.0394   0.1954   1.0000
  11.500   0.8649   0.05999   0.05372   0.0419   0.1930   1.0000
  11.750   0.8209   0.06637   0.06016   0.0421   0.1913   1.0000
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