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EPPLER 395 AIRFOIL (e395-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 395 AIRFOIL (e395-il)
Reynolds number: 100,000
Max Cl/Cd: 61.37 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e395-il-100000-n5.txt
Download as CSV file: xf-e395-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 395 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2791   0.09330   0.08863  -0.0688   0.9752   0.0244
  -9.250  -0.2810   0.08597   0.08133  -0.0746   0.9685   0.0248
  -8.750  -0.3650   0.05468   0.04993  -0.1004   0.9382   0.0209
  -8.500  -0.3672   0.04330   0.03793  -0.1183   0.9248   0.0204
  -8.250  -0.3452   0.03982   0.03422  -0.1240   0.9188   0.0218
  -8.000  -0.3241   0.03640   0.03038  -0.1283   0.9123   0.0236
  -7.750  -0.3007   0.03251   0.02585  -0.1320   0.9061   0.0259
  -7.500  -0.2679   0.03058   0.02375  -0.1353   0.9030   0.0287
  -7.250  -0.2412   0.02869   0.02153  -0.1371   0.8975   0.0332
  -7.000  -0.2124   0.02714   0.01971  -0.1387   0.8922   0.0383
  -6.750  -0.1780   0.02578   0.01818  -0.1412   0.8890   0.0454
  -6.500  -0.1416   0.02451   0.01672  -0.1439   0.8865   0.0541
  -6.250  -0.1189   0.02369   0.01575  -0.1437   0.8791   0.0619
  -6.000  -0.0857   0.02277   0.01465  -0.1454   0.8752   0.0723
  -5.750  -0.0497   0.02192   0.01363  -0.1474   0.8724   0.0844
  -5.500  -0.0231   0.02139   0.01297  -0.1477   0.8664   0.0957
  -5.250   0.0075   0.02080   0.01231  -0.1487   0.8617   0.1088
  -5.000   0.0423   0.02021   0.01159  -0.1503   0.8584   0.1248
  -4.750   0.0743   0.01974   0.01109  -0.1515   0.8543   0.1416
  -4.500   0.1004   0.01945   0.01077  -0.1515   0.8481   0.1580
  -4.250   0.1337   0.01908   0.01034  -0.1528   0.8443   0.1781
  -4.000   0.1693   0.01870   0.00987  -0.1544   0.8414   0.2006
  -3.750   0.1924   0.01861   0.00978  -0.1538   0.8344   0.2188
  -3.500   0.2238   0.01839   0.00952  -0.1546   0.8300   0.2410
  -3.250   0.2583   0.01812   0.00919  -0.1559   0.8268   0.2645
  -3.000   0.2828   0.01809   0.00916  -0.1555   0.8205   0.2846
  -2.750   0.3125   0.01797   0.00899  -0.1559   0.8157   0.3080
  -2.500   0.3457   0.01776   0.00877  -0.1569   0.8122   0.3313
  -2.250   0.3714   0.01776   0.00876  -0.1567   0.8065   0.3537
  -2.000   0.3989   0.01771   0.00873  -0.1567   0.8012   0.3768
  -1.750   0.4311   0.01757   0.00856  -0.1575   0.7974   0.4030
  -1.500   0.4574   0.01757   0.00861  -0.1572   0.7921   0.4270
  -1.250   0.4838   0.01759   0.00866  -0.1570   0.7864   0.4527
  -1.000   0.5151   0.01748   0.00856  -0.1576   0.7825   0.4817
  -0.750   0.5416   0.01750   0.00864  -0.1573   0.7774   0.5097
  -0.500   0.5666   0.01756   0.00877  -0.1568   0.7715   0.5392
  -0.250   0.5970   0.01748   0.00872  -0.1571   0.7674   0.5725
   0.000   0.6228   0.01753   0.00884  -0.1567   0.7622   0.6063
   0.250   0.6466   0.01760   0.00901  -0.1558   0.7561   0.6414
   0.500   0.6752   0.01752   0.00900  -0.1557   0.7521   0.6808
   0.750   0.6972   0.01759   0.00918  -0.1544   0.7462   0.7215
   1.000   0.7182   0.01762   0.00933  -0.1528   0.7403   0.7670
   1.250   0.7420   0.01745   0.00926  -0.1514   0.7362   0.8224
   1.500   0.7558   0.01747   0.00942  -0.1483   0.7294   0.9078
   1.750   0.7867   0.01750   0.00940  -0.1490   0.7239   1.0000
   2.000   0.8213   0.01752   0.00933  -0.1503   0.7201   1.0000
   2.250   0.8424   0.01791   0.00974  -0.1494   0.7123   1.0000
   2.500   0.8734   0.01800   0.00978  -0.1501   0.7073   1.0000
   2.750   0.9004   0.01822   0.00999  -0.1500   0.7014   1.0000
   3.000   0.9260   0.01846   0.01024  -0.1498   0.6946   1.0000
   3.250   0.9590   0.01847   0.01022  -0.1506   0.6901   1.0000
   3.500   0.9792   0.01887   0.01067  -0.1495   0.6818   1.0000
   3.750   1.0100   0.01892   0.01073  -0.1499   0.6762   1.0000
   4.000   1.0323   0.01923   0.01110  -0.1491   0.6682   1.0000
   4.250   1.0613   0.01931   0.01120  -0.1492   0.6617   1.0000
   4.500   1.0841   0.01959   0.01154  -0.1484   0.6534   1.0000
   4.750   1.1130   0.01965   0.01164  -0.1484   0.6461   1.0000
   5.000   1.1341   0.01994   0.01202  -0.1473   0.6367   1.0000
   5.250   1.1651   0.01990   0.01200  -0.1476   0.6292   1.0000
   5.500   1.1839   0.02023   0.01245  -0.1460   0.6183   1.0000
   5.750   1.2065   0.02043   0.01273  -0.1450   0.6080   1.0000
   6.000   1.2332   0.02048   0.01283  -0.1446   0.5981   1.0000
   6.250   1.2544   0.02070   0.01316  -0.1433   0.5861   1.0000
   6.500   1.2741   0.02097   0.01352  -0.1418   0.5733   1.0000
   6.750   1.2943   0.02121   0.01385  -0.1404   0.5599   1.0000
   7.000   1.3141   0.02146   0.01417  -0.1389   0.5453   1.0000
   7.250   1.3330   0.02172   0.01452  -0.1372   0.5295   1.0000
   7.500   1.3506   0.02202   0.01486  -0.1353   0.5122   1.0000
   7.750   1.3656   0.02238   0.01524  -0.1329   0.4934   1.0000
   8.000   1.3766   0.02290   0.01581  -0.1301   0.4726   1.0000
   8.250   1.3886   0.02345   0.01633  -0.1274   0.4499   1.0000
   8.500   1.3971   0.02417   0.01708  -0.1243   0.4249   1.0000
   8.750   1.4043   0.02503   0.01788  -0.1212   0.3980   1.0000
   9.000   1.4094   0.02606   0.01885  -0.1180   0.3697   1.0000
   9.250   1.4123   0.02731   0.02000  -0.1147   0.3404   1.0000
   9.500   1.4134   0.02877   0.02135  -0.1115   0.3110   1.0000
   9.750   1.4133   0.03043   0.02290  -0.1084   0.2823   1.0000
  10.000   1.4122   0.03229   0.02465  -0.1054   0.2549   1.0000
  10.250   1.4113   0.03428   0.02657  -0.1028   0.2281   1.0000
  10.500   1.4104   0.03640   0.02862  -0.1004   0.2031   1.0000
  10.750   1.4090   0.03869   0.03082  -0.0982   0.1800   1.0000
  11.000   1.4081   0.04104   0.03312  -0.0963   0.1580   1.0000
  11.250   1.4069   0.04355   0.03556  -0.0945   0.1386   1.0000
  11.500   1.4066   0.04607   0.03806  -0.0929   0.1203   1.0000
  11.750   1.4057   0.04874   0.04071  -0.0915   0.1045   1.0000
  12.000   1.4046   0.05154   0.04350  -0.0903   0.0908   1.0000
  12.250   1.4036   0.05443   0.04643  -0.0891   0.0790   1.0000
  12.500   1.4022   0.05746   0.04949  -0.0882   0.0690   1.0000
  12.750   1.3999   0.06071   0.05277  -0.0874   0.0609   1.0000
  13.000   1.3976   0.06406   0.05617  -0.0868   0.0538   1.0000
  13.250   1.3962   0.06741   0.05961  -0.0863   0.0477   1.0000
  13.500   1.3918   0.07123   0.06348  -0.0860   0.0433   1.0000
  13.750   1.3908   0.07473   0.06713  -0.0858   0.0387   1.0000
  14.000   1.3871   0.07868   0.07116  -0.0859   0.0355   1.0000
  14.250   1.3840   0.08265   0.07525  -0.0861   0.0326   1.0000
  14.500   1.3820   0.08656   0.07931  -0.0864   0.0298   1.0000
  14.750   1.3772   0.09094   0.08377  -0.0871   0.0279   1.0000
  15.000   1.3749   0.09502   0.08800  -0.0876   0.0260   1.0000
  15.250   1.3731   0.09912   0.09229  -0.0884   0.0241   1.0000
  15.500   1.3698   0.10351   0.09679  -0.0895   0.0226   1.0000
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