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EPPLER 49 AIRFOIL (e49-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 49 AIRFOIL (e49-il)
Reynolds number: 100,000
Max Cl/Cd: 56.58 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e49-il-100000.txt
Download as CSV file: xf-e49-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 49 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
  ------ -------- --------- --------- -------- -------- --------
  -6.000  -0.4053   0.10420   0.10019  -0.0175   1.0000   0.0431
  -5.750  -0.4052   0.10066   0.09668  -0.0138   1.0000   0.0445
  -5.500  -0.3990   0.09756   0.09360  -0.0139   1.0000   0.0462
  -5.250  -0.3892   0.09449   0.09053  -0.0157   1.0000   0.0480
  -5.000  -0.3750   0.09122   0.08726  -0.0190   1.0000   0.0504
  -4.750  -0.3487   0.08776   0.08376  -0.0263   1.0000   0.0539
  -4.500  -0.2919   0.08288   0.07872  -0.0439   1.0000   0.0566
  -4.250  -0.3040   0.07978   0.07573  -0.0362   1.0000   0.0591
  -4.000  -0.2871   0.07691   0.07285  -0.0379   1.0000   0.0637
  -3.750  -0.2277   0.07192   0.06766  -0.0533   1.0000   0.0715
  -3.500  -0.2202   0.06929   0.06504  -0.0514   1.0000   0.0749
  -3.250  -0.1625   0.06513   0.06063  -0.0642   1.0000   0.0856
  -3.000  -0.1513   0.06275   0.05830  -0.0630   1.0000   0.0910
  -2.750  -0.0788   0.06018   0.05520  -0.0782   1.0000   0.1125
  -2.500  -0.0740   0.05689   0.05216  -0.0755   1.0000   0.1162
  -2.250  -0.0395   0.05478   0.04994  -0.0798   0.9991   0.1323
  -1.750   0.0426   0.05169   0.04656  -0.0903   0.9947   0.2005
  -0.750   0.2680   0.04331   0.03561  -0.1153   0.9864   0.0950
  -0.500   0.3093   0.04286   0.03462  -0.1176   0.9846   0.0793
  -0.250   0.3460   0.04254   0.03382  -0.1192   0.9776   0.0713
   0.000   0.3884   0.04329   0.03431  -0.1219   0.9736   0.0703
   0.250   0.4333   0.04256   0.03362  -0.1255   0.9570   0.0771
   0.500   0.4900   0.04238   0.03331  -0.1305   0.9414   0.0811
   0.750   0.5335   0.04233   0.03314  -0.1335   0.9301   0.0938
   1.000   0.5699   0.04066   0.03338  -0.1353   0.9211   1.0000
   1.250   0.6050   0.04099   0.03334  -0.1369   0.9106   1.0000
   1.500   0.6418   0.04130   0.03344  -0.1389   0.9013   1.0000
   1.750   0.6810   0.04151   0.03351  -0.1413   0.8927   1.0000
   2.000   0.7123   0.04156   0.03347  -0.1424   0.8816   1.0000
   2.250   0.7445   0.04157   0.03345  -0.1435   0.8708   1.0000
   2.500   0.7784   0.04156   0.03341  -0.1449   0.8611   1.0000
   2.750   0.8219   0.04135   0.03318  -0.1477   0.8545   1.0000
   3.000   0.8511   0.04125   0.03310  -0.1482   0.8434   1.0000
   3.250   0.8829   0.04105   0.03299  -0.1491   0.8330   1.0000
   3.500   0.9303   0.04030   0.03231  -0.1522   0.8277   1.0000
   3.750   0.9604   0.03985   0.03194  -0.1525   0.8159   1.0000
   4.000   0.9930   0.03918   0.03139  -0.1530   0.8042   1.0000
   4.250   1.0287   0.03819   0.03059  -0.1537   0.7925   1.0000
   4.500   1.0675   0.03688   0.02944  -0.1546   0.7813   1.0000
   4.750   1.1166   0.03490   0.02768  -0.1569   0.7745   1.0000
   5.000   1.1508   0.03360   0.02659  -0.1570   0.7619   1.0000
   5.250   1.1862   0.03210   0.02539  -0.1570   0.7496   1.0000
   5.500   1.2259   0.03026   0.02383  -0.1575   0.7364   1.0000
   5.750   1.2778   0.02751   0.02138  -0.1594   0.7181   1.0000
   6.000   1.3384   0.02401   0.01781  -0.1614   0.6334   1.0000
   6.250   1.3619   0.02407   0.01726  -0.1591   0.5102   1.0000
   6.500   1.3561   0.02600   0.01817  -0.1528   0.3776   1.0000
   6.750   1.3475   0.02838   0.01972  -0.1469   0.2621   1.0000
   7.000   1.3333   0.03212   0.02196  -0.1410   0.0810   1.0000
   7.250   1.3340   0.03495   0.02435  -0.1369   0.0455   1.0000
   7.500   1.3419   0.03680   0.02640  -0.1338   0.0393   1.0000
   7.750   1.3444   0.03909   0.02883  -0.1302   0.0362   1.0000
   8.000   1.3485   0.04125   0.03117  -0.1268   0.0347   1.0000
   8.250   1.3561   0.04332   0.03342  -0.1239   0.0335   1.0000
   8.500   1.3697   0.04549   0.03571  -0.1218   0.0326   1.0000
   8.750   1.3995   0.04782   0.03823  -0.1217   0.0318   1.0000
   9.000   1.4594   0.05130   0.04197  -0.1254   0.0319   1.0000
   9.250   1.4971   0.05519   0.04631  -0.1265   0.0314   1.0000
   9.500   1.5125   0.05868   0.05024  -0.1247   0.0307   1.0000
   9.750   1.5191   0.06237   0.05438  -0.1218   0.0305   1.0000
  10.000   1.5191   0.06655   0.05904  -0.1182   0.0313   1.0000
  10.250   1.5143   0.07099   0.06391  -0.1143   0.0324   1.0000
  10.500   1.5055   0.07555   0.06884  -0.1105   0.0333   1.0000
  10.750   1.4949   0.08056   0.07416  -0.1071   0.0342   1.0000
  11.000   1.5027   0.08498   0.07884  -0.1052   0.0368   1.0000
  11.250   1.4717   0.08835   0.08268  -0.0999   0.0377   1.0000
  11.500   1.4398   0.09305   0.08780  -0.0961   0.0385   1.0000
  11.750   1.4105   0.09843   0.09353  -0.0939   0.0393   1.0000
  12.000   1.3834   0.10420   0.09958  -0.0932   0.0399   1.0000
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