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EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 403 AIRFOIL (e403-il)
Reynolds number: 50,000
Max Cl/Cd: 33.3 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e403-il-50000.txt
Download as CSV file: xf-e403-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5810   0.10213   0.09596  -0.0402   1.0000   0.1665
  -8.750  -0.5957   0.09304   0.08692  -0.0427   1.0000   0.1402
  -8.500  -0.6518   0.08828   0.08224  -0.0426   1.0000   0.1389
  -8.250  -0.7033   0.08357   0.07739  -0.0438   1.0000   0.1361
  -8.000  -0.7007   0.07812   0.07194  -0.0431   1.0000   0.1271
  -7.750  -0.7297   0.07224   0.06564  -0.0443   1.0000   0.1198
  -7.500  -0.7300   0.06743   0.06066  -0.0441   1.0000   0.1149
  -7.250  -0.7368   0.06163   0.05390  -0.0458   1.0000   0.1066
  -7.000  -0.7240   0.05746   0.04956  -0.0455   1.0000   0.1039
  -6.750  -0.7099   0.05331   0.04499  -0.0458   1.0000   0.1010
  -6.500  -0.6917   0.04956   0.04072  -0.0462   1.0000   0.0990
  -6.250  -0.6711   0.04653   0.03725  -0.0462   1.0000   0.0995
  -6.000  -0.6490   0.04398   0.03429  -0.0460   1.0000   0.1009
  -5.750  -0.6258   0.04164   0.03156  -0.0455   1.0000   0.1031
  -5.500  -0.6027   0.03968   0.02928  -0.0443   1.0000   0.1047
  -5.250  -0.5801   0.03814   0.02743  -0.0427   1.0000   0.1071
  -5.000  -0.5623   0.03673   0.02620  -0.0396   1.0000   0.1116
  -4.750  -0.5436   0.03585   0.02523  -0.0369   1.0000   0.1207
  -4.500  -0.5275   0.03485   0.02441  -0.0338   1.0000   0.1330
  -4.250  -0.5101   0.03347   0.02325  -0.0317   1.0000   0.1546
  -4.000  -0.4986   0.02988   0.02301  -0.0295   1.0000   0.4492
  -3.750  -0.5120   0.03592   0.02898  -0.0119   1.0000   0.6313
  -3.500  -0.5225   0.03915   0.03217   0.0024   1.0000   0.6762
  -3.250  -0.5286   0.04131   0.03425   0.0148   1.0000   0.7181
  -3.000  -0.5295   0.04266   0.03545   0.0254   1.0000   0.7591
  -2.750  -0.5193   0.04362   0.03621   0.0344   1.0000   0.8036
  -2.500  -0.4802   0.04411   0.03634   0.0366   1.0000   0.8472
  -2.250  -0.4325   0.04382   0.03564   0.0336   1.0000   0.8738
  -2.000  -0.4062   0.04311   0.03468   0.0325   1.0000   0.8887
  -1.750  -0.3828   0.04239   0.03374   0.0316   1.0000   0.9000
  -1.500  -0.3814   0.04151   0.03275   0.0344   1.0000   0.9090
  -1.250  -0.3518   0.04097   0.03198   0.0322   1.0000   0.9175
  -1.000  -0.3417   0.04026   0.03115   0.0332   1.0000   0.9245
  -0.750  -0.3217   0.03975   0.03050   0.0325   1.0000   0.9312
  -0.500  -0.3131   0.03914   0.02978   0.0338   1.0000   0.9371
  -0.250  -0.2878   0.03883   0.02932   0.0321   1.0000   0.9427
   0.000  -0.2840   0.03826   0.02868   0.0341   1.0000   0.9482
   0.250  -0.2513   0.03821   0.02851   0.0309   1.0000   0.9531
   0.500  -0.2322   0.03802   0.02824   0.0301   1.0000   0.9583
   0.750  -0.2100   0.03796   0.02808   0.0287   1.0000   0.9632
   1.000  -0.1810   0.03810   0.02815   0.0259   1.0000   0.9680
   1.250  -0.1606   0.03818   0.02818   0.0247   1.0000   0.9732
   1.500  -0.1280   0.03854   0.02847   0.0211   1.0000   0.9778
   1.750  -0.1021   0.03886   0.02877   0.0187   1.0000   0.9831
   2.000  -0.0747   0.03925   0.02915   0.0158   1.0000   0.9880
   2.250  -0.0504   0.03966   0.02956   0.0135   1.0000   0.9936
   2.500  -0.0301   0.04011   0.03002   0.0118   1.0000   1.0000
   2.750  -0.0305   0.03994   0.02987   0.0138   1.0000   1.0000
   3.000  -0.0306   0.03977   0.02973   0.0157   1.0000   1.0000
   3.250  -0.0300   0.03964   0.02963   0.0175   1.0000   1.0000
   3.500  -0.0259   0.03968   0.02971   0.0184   1.0000   1.0000
   3.750  -0.0164   0.04006   0.03012   0.0183   1.0000   1.0000
   4.000  -0.0003   0.04085   0.03095   0.0169   0.9991   1.0000
   4.250   0.1405   0.04639   0.03649  -0.0048   0.9122   1.0000
   4.500   0.1895   0.04756   0.03770  -0.0102   0.8849   1.0000
   4.750   0.2260   0.04826   0.03847  -0.0137   0.8618   1.0000
   5.000   0.2689   0.04916   0.03946  -0.0180   0.8407   1.0000
   5.250   0.3055   0.04985   0.04024  -0.0212   0.8199   1.0000
   5.500   0.3551   0.05064   0.04118  -0.0261   0.8011   1.0000
   5.750   0.3877   0.05123   0.04189  -0.0286   0.7803   1.0000
   6.000   0.4314   0.05175   0.04255  -0.0323   0.7605   1.0000
   6.250   0.4843   0.05193   0.04294  -0.0367   0.7423   1.0000
   6.500   0.5148   0.05243   0.04360  -0.0385   0.7205   1.0000
   6.750   0.5610   0.05237   0.04374  -0.0415   0.7007   1.0000
   7.000   0.6179   0.05153   0.04317  -0.0450   0.6824   1.0000
   7.250   0.6487   0.05176   0.04361  -0.0461   0.6590   1.0000
   7.500   0.7078   0.04998   0.04216  -0.0487   0.6391   1.0000
   7.750   0.7867   0.04574   0.03832  -0.0511   0.6214   1.0000
   8.000   0.8421   0.04286   0.03580  -0.0518   0.5965   1.0000
   8.250   0.9857   0.03361   0.02703  -0.0582   0.5581   1.0000
   8.500   1.0403   0.03223   0.02564  -0.0596   0.5025   1.0000
   8.750   1.0763   0.03232   0.02551  -0.0595   0.4449   1.0000
   9.000   1.0981   0.03316   0.02609  -0.0581   0.3909   1.0000
   9.250   1.1121   0.03449   0.02712  -0.0561   0.3407   1.0000
   9.500   1.1198   0.03614   0.02851  -0.0535   0.2938   1.0000
   9.750   1.1238   0.03800   0.03005  -0.0507   0.2493   1.0000
  10.000   1.1217   0.04005   0.03192  -0.0476   0.2109   1.0000
  10.250   1.1242   0.04244   0.03397  -0.0453   0.1741   1.0000
  10.500   1.1359   0.04533   0.03675  -0.0440   0.1421   1.0000
  10.750   1.1679   0.04875   0.03997  -0.0450   0.1177   1.0000
  11.000   1.2032   0.05261   0.04398  -0.0465   0.1044   1.0000
  11.250   1.2247   0.05650   0.04832  -0.0463   0.0982   1.0000
  11.500   1.2532   0.06102   0.05293  -0.0477   0.0925   1.0000
  11.750   1.2455   0.06452   0.05697  -0.0446   0.0909   1.0000
  12.000   1.2360   0.06837   0.06126  -0.0419   0.0896   1.0000
  12.250   1.2228   0.07247   0.06576  -0.0394   0.0890   1.0000
  12.500   1.2055   0.07689   0.07053  -0.0372   0.0888   1.0000
  12.750   1.1843   0.08171   0.07568  -0.0356   0.0890   1.0000
  13.000   1.1601   0.08702   0.08128  -0.0348   0.0895   1.0000
  13.250   1.1342   0.09289   0.08741  -0.0349   0.0902   1.0000
  13.500   1.1081   0.09938   0.09410  -0.0363   0.0911   1.0000
  13.750   1.0833   0.10648   0.10136  -0.0387   0.0920   1.0000
  14.000   1.0626   0.11400   0.10899  -0.0419   0.0928   1.0000
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