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EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 403 AIRFOIL (e403-il)
Reynolds number: 100,000
Max Cl/Cd: 47.39 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e403-il-100000.txt
Download as CSV file: xf-e403-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 403 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5231   0.10842   0.10402  -0.0316   1.0000   0.1556
  -9.000  -0.5245   0.10589   0.10152  -0.0304   1.0000   0.1616
  -7.250  -0.7529   0.05596   0.04986  -0.0448   1.0000   0.0811
  -7.000  -0.7343   0.04967   0.04304  -0.0442   1.0000   0.0631
  -6.750  -0.7166   0.04500   0.03784  -0.0445   1.0000   0.0585
  -6.500  -0.6947   0.04147   0.03361  -0.0448   1.0000   0.0566
  -6.250  -0.6722   0.03898   0.03070  -0.0446   1.0000   0.0563
  -6.000  -0.6487   0.03706   0.02841  -0.0441   1.0000   0.0554
  -5.750  -0.6254   0.03522   0.02627  -0.0434   1.0000   0.0550
  -5.500  -0.6032   0.03351   0.02440  -0.0425   1.0000   0.0551
  -5.250  -0.5820   0.03191   0.02275  -0.0413   1.0000   0.0558
  -5.000  -0.5612   0.03063   0.02149  -0.0402   1.0000   0.0573
  -4.750  -0.5400   0.02963   0.02052  -0.0391   1.0000   0.0593
  -4.500  -0.5180   0.02884   0.01971  -0.0384   1.0000   0.0632
  -4.250  -0.4951   0.02788   0.01882  -0.0381   1.0000   0.0696
  -4.000  -0.4694   0.02710   0.01806  -0.0385   1.0000   0.0781
  -3.750  -0.4195   0.02382   0.01775  -0.0456   1.0000   0.5470
  -3.500  -0.4109   0.02560   0.01947  -0.0400   1.0000   0.5981
  -3.250  -0.4054   0.02734   0.02120  -0.0337   1.0000   0.6261
  -3.000  -0.4054   0.02933   0.02323  -0.0257   1.0000   0.6543
  -2.750  -0.4100   0.03094   0.02491  -0.0165   1.0000   0.6731
  -2.500  -0.4079   0.03200   0.02596  -0.0096   1.0000   0.6908
  -2.250  -0.4030   0.03274   0.02665  -0.0039   1.0000   0.7078
  -2.000  -0.3967   0.03330   0.02715   0.0012   1.0000   0.7254
  -1.750  -0.3884   0.03362   0.02740   0.0054   1.0000   0.7409
  -1.500  -0.3749   0.03366   0.02735   0.0078   1.0000   0.7516
  -1.250  -0.3478   0.03365   0.02716   0.0059   1.0000   0.7609
  -1.000  -0.3351   0.03353   0.02697   0.0082   1.0000   0.7664
  -0.750  -0.3106   0.03355   0.02687   0.0070   1.0000   0.7729
  -0.500  -0.2875   0.03354   0.02675   0.0061   1.0000   0.7779
  -0.250  -0.2648   0.03373   0.02685   0.0057   0.9985   0.7824
   0.000  -0.1727   0.03595   0.02881  -0.0076   0.9628   0.7876
   0.250  -0.1144   0.03651   0.02921  -0.0143   0.9409   0.7919
   0.500  -0.0746   0.03679   0.02941  -0.0171   0.9285   0.7954
   0.750  -0.0361   0.03693   0.02947  -0.0201   0.9174   0.7995
   1.000   0.0010   0.03696   0.02944  -0.0232   0.9054   0.8033
   1.250   0.0392   0.03706   0.02949  -0.0264   0.8945   0.8067
   1.500   0.0820   0.03727   0.02967  -0.0294   0.8869   0.8102
   1.750   0.1106   0.03713   0.02952  -0.0305   0.8749   0.8137
   2.000   0.1457   0.03715   0.02953  -0.0330   0.8642   0.8171
   2.250   0.1985   0.03730   0.02965  -0.0383   0.8579   0.8209
   2.500   0.2231   0.03706   0.02945  -0.0383   0.8458   0.8240
   2.750   0.2538   0.03696   0.02938  -0.0395   0.8348   0.8271
   3.000   0.3036   0.03678   0.02923  -0.0436   0.8293   0.8310
   3.250   0.3367   0.03666   0.02915  -0.0456   0.8172   0.8347
   3.500   0.3667   0.03642   0.02898  -0.0464   0.8058   0.8376
   3.750   0.4142   0.03580   0.02843  -0.0494   0.8005   0.8410
   4.000   0.4441   0.03548   0.02819  -0.0502   0.7880   0.8449
   4.250   0.4795   0.03514   0.02794  -0.0519   0.7762   0.8487
   4.500   0.5276   0.03417   0.02707  -0.0548   0.7698   0.8519
   4.750   0.5606   0.03343   0.02644  -0.0553   0.7584   0.8553
   5.000   0.5937   0.03274   0.02589  -0.0560   0.7461   0.8593
   5.250   0.6461   0.03128   0.02458  -0.0591   0.7405   0.8635
   5.500   0.6816   0.03022   0.02368  -0.0596   0.7289   0.8671
   5.750   0.7156   0.02905   0.02265  -0.0597   0.7166   0.8708
   6.000   0.7703   0.02682   0.02061  -0.0622   0.7110   0.8751
   6.250   0.8186   0.02513   0.01910  -0.0644   0.6972   0.8795
   6.500   0.8509   0.02395   0.01806  -0.0638   0.6767   0.8838
   6.750   0.9011   0.02236   0.01659  -0.0661   0.6528   0.8880
   7.000   0.9470   0.02147   0.01573  -0.0682   0.6182   0.8921
   7.250   0.9819   0.02112   0.01531  -0.0687   0.5771   0.8966
   7.500   1.0061   0.02123   0.01531  -0.0678   0.5343   0.9018
   7.750   1.0269   0.02167   0.01560  -0.0666   0.4900   0.9072
   8.000   1.0407   0.02218   0.01593  -0.0643   0.4497   0.9126
   8.250   1.0516   0.02287   0.01652  -0.0619   0.4097   0.9186
   8.500   1.0605   0.02364   0.01712  -0.0592   0.3715   0.9252
   8.750   1.0656   0.02447   0.01787  -0.0561   0.3328   0.9333
   9.000   1.0685   0.02538   0.01862  -0.0528   0.2951   0.9422
   9.250   1.0709   0.02641   0.01952  -0.0498   0.2549   0.9531
   9.500   1.0760   0.02763   0.02060  -0.0476   0.2147   0.9687
   9.750   1.0822   0.02918   0.02195  -0.0461   0.1754   1.0000
  10.000   1.0876   0.03149   0.02398  -0.0448   0.1299   1.0000
  10.250   1.0876   0.03449   0.02659  -0.0429   0.0937   1.0000
  10.500   1.0964   0.03705   0.02907  -0.0419   0.0730   1.0000
  10.750   1.1112   0.03937   0.03138  -0.0415   0.0631   1.0000
  11.000   1.1362   0.04179   0.03360  -0.0420   0.0568   1.0000
  11.250   1.1688   0.04387   0.03591  -0.0430   0.0529   1.0000
  11.500   1.2019   0.04618   0.03833  -0.0444   0.0496   1.0000
  11.750   1.2449   0.04968   0.04184  -0.0471   0.0461   1.0000
  12.000   1.2606   0.05245   0.04502  -0.0467   0.0448   1.0000
  12.250   1.2754   0.05592   0.04889  -0.0463   0.0441   1.0000
  12.500   1.2819   0.05967   0.05304  -0.0453   0.0438   1.0000
  12.750   1.2808   0.06364   0.05740  -0.0438   0.0437   1.0000
  13.000   1.2738   0.06784   0.06197  -0.0422   0.0438   1.0000
  13.250   1.2624   0.07232   0.06680  -0.0408   0.0440   1.0000
  13.500   1.2475   0.07709   0.07190  -0.0398   0.0443   1.0000
  13.750   1.2299   0.08222   0.07732  -0.0393   0.0446   1.0000
  14.000   1.2101   0.08773   0.08310  -0.0395   0.0449   1.0000
  14.250   1.1890   0.09369   0.08930  -0.0405   0.0452   1.0000
  14.500   1.1675   0.10011   0.09594  -0.0424   0.0456   1.0000
  14.750   1.1464   0.10707   0.10309  -0.0453   0.0460   1.0000
  15.000   1.1295   0.11444   0.11059  -0.0486   0.0464   1.0000
  15.250   1.1046   0.12223   0.11863  -0.0539   0.0470   1.0000
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