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EPPLER 395 AIRFOIL (e395-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 395 AIRFOIL (e395-il)
Reynolds number: 50,000
Max Cl/Cd: 28.18 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e395-il-50000-n5.txt
Download as CSV file: xf-e395-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3388   0.11948   0.11300  -0.0466   1.0000   0.0481
  -9.500  -0.3568   0.11465   0.10837  -0.0440   1.0000   0.0481
  -9.250  -0.3670   0.11223   0.10604  -0.0426   1.0000   0.0481
  -9.000  -0.3764   0.11002   0.10392  -0.0411   1.0000   0.0480
  -8.750  -0.3691   0.10476   0.09868  -0.0458   0.9945   0.0480
  -8.500  -0.3543   0.10201   0.09593  -0.0478   0.9891   0.0498
  -8.250  -0.3433   0.09843   0.09234  -0.0513   0.9834   0.0522
  -8.000  -0.3411   0.09407   0.08801  -0.0548   0.9757   0.0534
  -7.750  -0.3425   0.08936   0.08335  -0.0588   0.9678   0.0543
  -7.500  -0.3451   0.08394   0.07798  -0.0637   0.9594   0.0547
  -7.250  -0.3489   0.07719   0.07127  -0.0702   0.9495   0.0549
  -7.000  -0.3504   0.06700   0.06103  -0.0821   0.9399   0.0547
  -6.750  -0.3433   0.05519   0.04868  -0.0974   0.9319   0.0557
  -6.500  -0.3259   0.04743   0.04012  -0.1062   0.9246   0.0595
  -6.250  -0.2977   0.04490   0.03732  -0.1094   0.9196   0.0657
  -6.000  -0.2618   0.04125   0.03311  -0.1146   0.9163   0.0743
  -5.750  -0.2361   0.03856   0.02980  -0.1168   0.9101   0.0836
  -5.500  -0.2047   0.03710   0.02811  -0.1189   0.9054   0.0944
  -5.250  -0.1684   0.03561   0.02633  -0.1216   0.9021   0.1074
  -5.000  -0.1438   0.03465   0.02520  -0.1220   0.8960   0.1191
  -4.750  -0.1125   0.03369   0.02402  -0.1235   0.8912   0.1344
  -4.500  -0.0757   0.03275   0.02278  -0.1259   0.8877   0.1537
  -4.250  -0.0501   0.03224   0.02214  -0.1262   0.8819   0.1704
  -4.000  -0.0214   0.03182   0.02168  -0.1269   0.8766   0.1895
  -3.750   0.0140   0.03135   0.02102  -0.1287   0.8728   0.2142
  -3.500   0.0387   0.03118   0.02082  -0.1287   0.8669   0.2348
  -3.250   0.0674   0.03098   0.02049  -0.1294   0.8615   0.2592
  -3.000   0.1023   0.03073   0.02019  -0.1309   0.8577   0.2863
  -2.750   0.1263   0.03074   0.02012  -0.1307   0.8516   0.3108
  -2.500   0.1548   0.03070   0.01999  -0.1312   0.8461   0.3373
  -2.250   0.1899   0.03054   0.01978  -0.1326   0.8424   0.3671
  -2.000   0.2114   0.03072   0.01994  -0.1319   0.8358   0.3924
  -1.750   0.2401   0.03074   0.01992  -0.1323   0.8305   0.4218
  -1.500   0.2752   0.03062   0.01978  -0.1336   0.8270   0.4548
  -1.250   0.2934   0.03096   0.02012  -0.1324   0.8195   0.4826
  -1.000   0.3226   0.03098   0.02016  -0.1327   0.8145   0.5159
  -0.750   0.3571   0.03085   0.02007  -0.1336   0.8113   0.5540
  -0.500   0.3704   0.03134   0.02063  -0.1316   0.8028   0.5852
  -0.250   0.3996   0.03130   0.02066  -0.1316   0.7983   0.6274
   0.000   0.4215   0.03146   0.02091  -0.1305   0.7927   0.6712
   0.250   0.4378   0.03171   0.02128  -0.1284   0.7856   0.7187
   0.500   0.4622   0.03144   0.02115  -0.1269   0.7817   0.7851
   1.000   0.5019   0.03182   0.02152  -0.1246   0.7678   1.0000
   1.250   0.5272   0.03246   0.02199  -0.1251   0.7609   1.0000
   1.500   0.5549   0.03297   0.02235  -0.1257   0.7546   1.0000
   1.750   0.5930   0.03307   0.02231  -0.1275   0.7511   1.0000
   2.000   0.6062   0.03413   0.02329  -0.1262   0.7414   1.0000
   2.250   0.6410   0.03430   0.02337  -0.1274   0.7371   1.0000
   2.500   0.6572   0.03526   0.02429  -0.1265   0.7283   1.0000
   2.750   0.6881   0.03556   0.02454  -0.1271   0.7230   1.0000
   3.250   0.7347   0.03684   0.02576  -0.1267   0.7087   1.0000
   3.500   0.7721   0.03676   0.02569  -0.1278   0.7053   1.0000
   3.750   0.7808   0.03811   0.02707  -0.1260   0.6941   1.0000
   4.000   0.8179   0.03798   0.02695  -0.1270   0.6904   1.0000
   4.250   0.8267   0.03936   0.02839  -0.1253   0.6791   1.0000
   4.500   0.8639   0.03914   0.02821  -0.1261   0.6753   1.0000
   4.750   0.8726   0.04054   0.02966  -0.1243   0.6637   1.0000
   5.000   0.9106   0.04017   0.02939  -0.1251   0.6600   1.0000
   5.250   0.9188   0.04160   0.03089  -0.1233   0.6479   1.0000
   5.500   0.9587   0.04100   0.03039  -0.1241   0.6444   1.0000
   5.750   0.9660   0.04246   0.03194  -0.1221   0.6318   1.0000
   6.000   0.9783   0.04365   0.03324  -0.1207   0.6203   1.0000
   6.250   1.0158   0.04297   0.03270  -0.1209   0.6156   1.0000
   6.500   1.0258   0.04424   0.03408  -0.1192   0.6031   1.0000
   7.000   1.0782   0.04423   0.03439  -0.1178   0.5860   1.0000
   7.250   1.0899   0.04529   0.03559  -0.1161   0.5732   1.0000
   7.500   1.1061   0.04596   0.03641  -0.1147   0.5612   1.0000
   7.750   1.1488   0.04438   0.03506  -0.1146   0.5551   1.0000
   8.000   1.1620   0.04514   0.03599  -0.1128   0.5415   1.0000
   8.250   1.1778   0.04568   0.03670  -0.1112   0.5279   1.0000
   8.500   1.1958   0.04597   0.03718  -0.1096   0.5143   1.0000
   8.750   1.2158   0.04605   0.03747  -0.1081   0.5003   1.0000
   9.000   1.2365   0.04599   0.03760  -0.1065   0.4853   1.0000
   9.250   1.2573   0.04586   0.03765  -0.1049   0.4689   1.0000
   9.500   1.2806   0.04544   0.03741  -0.1032   0.4510   1.0000
   9.750   1.2926   0.04612   0.03823  -0.1012   0.4304   1.0000
  10.000   1.3061   0.04666   0.03888  -0.0992   0.4078   1.0000
  10.250   1.3172   0.04747   0.03976  -0.0972   0.3834   1.0000
  10.500   1.3285   0.04827   0.04056  -0.0952   0.3571   1.0000
  10.750   1.3350   0.04964   0.04191  -0.0931   0.3301   1.0000
  11.000   1.3367   0.05163   0.04391  -0.0912   0.3030   1.0000
  11.250   1.3372   0.05388   0.04610  -0.0894   0.2768   1.0000
  11.500   1.3360   0.05640   0.04853  -0.0877   0.2518   1.0000
  11.750   1.3330   0.05926   0.05134  -0.0863   0.2282   1.0000
  12.000   1.3294   0.06238   0.05441  -0.0851   0.2061   1.0000
  12.250   1.3250   0.06572   0.05770  -0.0842   0.1858   1.0000
  12.500   1.3203   0.06922   0.06111  -0.0834   0.1678   1.0000
  12.750   1.3163   0.07288   0.06478  -0.0829   0.1503   1.0000
  13.000   1.3122   0.07664   0.06855  -0.0826   0.1348   1.0000
  13.250   1.3083   0.08050   0.07241  -0.0825   0.1211   1.0000
  13.500   1.3050   0.08439   0.07633  -0.0825   0.1091   1.0000
  13.750   1.3017   0.08834   0.08023  -0.0826   0.0988   1.0000
  14.000   1.3002   0.09222   0.08421  -0.0828   0.0891   1.0000
  14.250   1.2993   0.09609   0.08820  -0.0831   0.0806   1.0000
  14.500   1.2986   0.09982   0.09189  -0.0835   0.0740   1.0000
  14.750   1.2987   0.10377   0.09607  -0.0840   0.0672   1.0000
  15.000   1.2994   0.10741   0.09970  -0.0845   0.0621   1.0000
  15.250   1.2992   0.11159   0.10418  -0.0853   0.0572   1.0000
  15.500   1.3001   0.11519   0.10776  -0.0862   0.0532   1.0000
  15.750   1.2990   0.11973   0.11258  -0.0874   0.0499   1.0000
  16.000   1.2960   0.12463   0.11775  -0.0891   0.0470   1.0000
  16.250   1.2948   0.12892   0.12213  -0.0908   0.0445   1.0000
  16.500   1.2949   0.13307   0.12637  -0.0924   0.0423   1.0000
  16.750   1.2849   0.13990   0.13355  -0.0959   0.0412   1.0000
  17.000   1.2731   0.14737   0.14132  -0.1001   0.0405   1.0000
  17.250   1.2584   0.15593   0.15012  -0.1054   0.0401   1.0000
  17.500   1.2404   0.16598   0.16040  -0.1120   0.0402   1.0000
  17.750   1.2199   0.17777   0.17234  -0.1198   0.0407   1.0000
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