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EPPLER 399 AIRFOIL (e399-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 399 AIRFOIL (e399-il)
Reynolds number: 100,000
Max Cl/Cd: 54 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e399-il-100000-n5.txt
Download as CSV file: xf-e399-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 399 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4253   0.07788   0.07308  -0.0785   0.9880   0.0262
 -11.000  -0.4452   0.06748   0.06251  -0.0886   0.9791   0.0259
 -10.750  -0.4596   0.05881   0.05363  -0.0980   0.9677   0.0257
 -10.500  -0.4729   0.05108   0.04557  -0.1072   0.9538   0.0261
 -10.250  -0.4719   0.04613   0.04043  -0.1140   0.9420   0.0268
 -10.000  -0.4638   0.04242   0.03656  -0.1197   0.9302   0.0279
  -9.750  -0.4531   0.03900   0.03285  -0.1240   0.9192   0.0293
  -9.500  -0.4316   0.03573   0.02922  -0.1284   0.9131   0.0314
  -9.250  -0.4153   0.03397   0.02732  -0.1298   0.9029   0.0340
  -9.000  -0.3883   0.03187   0.02500  -0.1328   0.8975   0.0377
  -8.750  -0.3690   0.03026   0.02309  -0.1336   0.8882   0.0421
  -8.500  -0.3403   0.02880   0.02152  -0.1358   0.8826   0.0472
  -8.250  -0.3160   0.02760   0.02020  -0.1369   0.8750   0.0528
  -8.000  -0.2890   0.02641   0.01886  -0.1382   0.8683   0.0595
  -7.750  -0.2564   0.02522   0.01749  -0.1403   0.8639   0.0677
  -7.500  -0.2343   0.02444   0.01655  -0.1402   0.8549   0.0755
  -7.250  -0.2032   0.02355   0.01554  -0.1417   0.8496   0.0852
  -7.000  -0.1763   0.02282   0.01474  -0.1423   0.8429   0.0950
  -6.750  -0.1489   0.02214   0.01398  -0.1430   0.8361   0.1057
  -6.500  -0.1164   0.02143   0.01316  -0.1444   0.8315   0.1186
  -6.250  -0.0917   0.02096   0.01261  -0.1444   0.8238   0.1311
  -6.000  -0.0620   0.02044   0.01201  -0.1452   0.8179   0.1461
  -5.750  -0.0297   0.01995   0.01143  -0.1464   0.8134   0.1630
  -5.500  -0.0055   0.01967   0.01110  -0.1462   0.8059   0.1785
  -5.250   0.0249   0.01931   0.01067  -0.1470   0.8006   0.1968
  -5.000   0.0551   0.01902   0.01029  -0.1476   0.7955   0.2158
  -4.750   0.0808   0.01885   0.01007  -0.1475   0.7886   0.2340
  -4.500   0.1112   0.01863   0.00979  -0.1482   0.7837   0.2533
  -4.250   0.1408   0.01847   0.00957  -0.1487   0.7789   0.2721
  -4.000   0.1663   0.01840   0.00947  -0.1484   0.7723   0.2899
  -3.750   0.1961   0.01827   0.00928  -0.1489   0.7674   0.3085
  -3.500   0.2264   0.01816   0.00909  -0.1494   0.7630   0.3268
  -3.250   0.2510   0.01817   0.00908  -0.1490   0.7566   0.3434
  -3.000   0.2798   0.01811   0.00896  -0.1492   0.7518   0.3607
  -2.750   0.3111   0.01801   0.00878  -0.1498   0.7480   0.3783
  -2.500   0.3352   0.01807   0.00885  -0.1493   0.7417   0.3941
  -2.250   0.3626   0.01807   0.00882  -0.1493   0.7366   0.4106
  -2.000   0.3928   0.01802   0.00871  -0.1497   0.7327   0.4277
  -1.750   0.4194   0.01806   0.00874  -0.1496   0.7278   0.4440
  -1.500   0.4447   0.01813   0.00882  -0.1492   0.7222   0.4603
  -1.250   0.4732   0.01813   0.00880  -0.1493   0.7180   0.4773
  -1.000   0.5038   0.01810   0.00873  -0.1498   0.7146   0.4949
  -0.750   0.5262   0.01827   0.00895  -0.1490   0.7086   0.5114
  -0.500   0.5527   0.01834   0.00904  -0.1487   0.7038   0.5289
  -0.250   0.5818   0.01835   0.00905  -0.1489   0.7001   0.5475
   0.000   0.6088   0.01843   0.00915  -0.1488   0.6959   0.5661
   0.250   0.6316   0.01861   0.00941  -0.1480   0.6904   0.5849
   0.500   0.6584   0.01868   0.00951  -0.1478   0.6860   0.6051
   0.750   0.6879   0.01870   0.00953  -0.1480   0.6826   0.6270
   1.000   0.7111   0.01891   0.00981  -0.1472   0.6776   0.6484
   1.250   0.7341   0.01908   0.01007  -0.1463   0.6725   0.6703
   1.500   0.7607   0.01914   0.01018  -0.1460   0.6685   0.6945
   1.750   0.7895   0.01915   0.01021  -0.1459   0.6654   0.7203
   2.000   0.8071   0.01945   0.01065  -0.1442   0.6595   0.7463
   2.250   0.8285   0.01958   0.01087  -0.1429   0.6547   0.7753
   2.500   0.8525   0.01959   0.01094  -0.1418   0.6510   0.8083
   2.750   0.8734   0.01962   0.01106  -0.1402   0.6470   0.8483
   3.000   0.8859   0.01981   0.01141  -0.1373   0.6411   0.9095
   3.250   0.9163   0.01989   0.01150  -0.1380   0.6366   1.0000
   3.500   0.9499   0.02000   0.01154  -0.1392   0.6331   1.0000
   3.750   0.9711   0.02049   0.01207  -0.1386   0.6272   1.0000
   4.000   0.9963   0.02081   0.01240  -0.1384   0.6219   1.0000
   4.250   1.0274   0.02095   0.01252  -0.1391   0.6179   1.0000
   4.500   1.0520   0.02130   0.01290  -0.1388   0.6128   1.0000
   4.750   1.0728   0.02175   0.01341  -0.1380   0.6066   1.0000
   5.000   1.1025   0.02189   0.01356  -0.1384   0.6021   1.0000
   5.250   1.1278   0.02219   0.01390  -0.1381   0.5969   1.0000
   5.500   1.1464   0.02267   0.01447  -0.1368   0.5901   1.0000
   5.750   1.1767   0.02275   0.01457  -0.1373   0.5853   1.0000
   6.000   1.1959   0.02320   0.01511  -0.1360   0.5786   1.0000
   6.250   1.2175   0.02352   0.01550  -0.1351   0.5718   1.0000
   6.500   1.2511   0.02344   0.01543  -0.1359   0.5668   1.0000
   6.750   1.2597   0.02415   0.01630  -0.1331   0.5578   1.0000
   7.000   1.2914   0.02406   0.01623  -0.1336   0.5517   1.0000
   7.250   1.3000   0.02472   0.01705  -0.1307   0.5425   1.0000
   7.500   1.3301   0.02463   0.01698  -0.1309   0.5355   1.0000
   7.750   1.3351   0.02533   0.01783  -0.1274   0.5257   1.0000
   8.000   1.3605   0.02534   0.01788  -0.1268   0.5175   1.0000
   8.250   1.3655   0.02599   0.01867  -0.1234   0.5072   1.0000
   8.500   1.3769   0.02648   0.01924  -0.1209   0.4969   1.0000
   8.750   1.3970   0.02661   0.01941  -0.1195   0.4866   1.0000
   9.000   1.3997   0.02750   0.02042  -0.1161   0.4743   1.0000
   9.250   1.4061   0.02830   0.02133  -0.1133   0.4616   1.0000
   9.500   1.4144   0.02907   0.02216  -0.1109   0.4482   1.0000
   9.750   1.4220   0.02993   0.02308  -0.1084   0.4338   1.0000
  10.000   1.4279   0.03095   0.02415  -0.1060   0.4183   1.0000
  10.250   1.4325   0.03216   0.02539  -0.1035   0.4016   1.0000
  10.500   1.4362   0.03350   0.02676  -0.1012   0.3836   1.0000
  10.750   1.4393   0.03498   0.02823  -0.0989   0.3644   1.0000
  11.000   1.4414   0.03662   0.02983  -0.0968   0.3445   1.0000
  11.250   1.4405   0.03864   0.03184  -0.0947   0.3238   1.0000
  11.500   1.4390   0.04080   0.03395  -0.0927   0.3028   1.0000
  11.750   1.4365   0.04315   0.03623  -0.0908   0.2822   1.0000
  12.000   1.4331   0.04575   0.03880  -0.0892   0.2617   1.0000
  12.250   1.4290   0.04853   0.04154  -0.0877   0.2419   1.0000
  12.500   1.4243   0.05149   0.04444  -0.0864   0.2233   1.0000
  12.750   1.4197   0.05459   0.04750  -0.0853   0.2058   1.0000
  13.000   1.4156   0.05778   0.05067  -0.0845   0.1887   1.0000
  13.250   1.4116   0.06108   0.05395  -0.0838   0.1728   1.0000
  13.500   1.4077   0.06450   0.05736  -0.0834   0.1578   1.0000
  13.750   1.4038   0.06802   0.06088  -0.0830   0.1438   1.0000
  14.000   1.3998   0.07165   0.06451  -0.0829   0.1311   1.0000
  14.250   1.3956   0.07543   0.06829  -0.0828   0.1195   1.0000
  14.500   1.3924   0.07918   0.07208  -0.0830   0.1085   1.0000
  14.750   1.3899   0.08292   0.07587  -0.0832   0.0985   1.0000
  15.000   1.3868   0.08681   0.07980  -0.0836   0.0898   1.0000
  15.250   1.3821   0.09100   0.08399  -0.0841   0.0825   1.0000
  15.500   1.3802   0.09490   0.08798  -0.0847   0.0750   1.0000
  15.750   1.3772   0.09899   0.09213  -0.0855   0.0689   1.0000
  16.000   1.3732   0.10329   0.09648  -0.0865   0.0635   1.0000
  16.250   1.3713   0.10732   0.10061  -0.0874   0.0583   1.0000
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