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EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 68 AIRFOIL (e68-il)
Reynolds number: 50,000
Max Cl/Cd: 33.71 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e68-il-50000.txt
Download as CSV file: xf-e68-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 68 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3829   0.10855   0.10213  -0.0258   1.0000   0.2895
  -8.250  -0.3743   0.10486   0.09847  -0.0239   1.0000   0.2964
  -8.000  -0.3996   0.10437   0.09814  -0.0215   1.0000   0.3048
  -7.750  -0.3996   0.10105   0.09488  -0.0197   1.0000   0.3086
  -7.500  -0.5333   0.08697   0.08115  -0.0359   1.0000   0.1558
  -7.250  -0.5503   0.08007   0.07425  -0.0377   1.0000   0.1397
  -7.000  -0.5742   0.07285   0.06694  -0.0404   1.0000   0.1302
  -6.750  -0.5844   0.06693   0.06080  -0.0418   1.0000   0.1242
  -6.500  -0.5871   0.06158   0.05522  -0.0427   1.0000   0.1208
  -6.250  -0.5894   0.05370   0.04654  -0.0457   1.0000   0.1154
  -6.000  -0.5774   0.05000   0.04254  -0.0457   1.0000   0.1170
  -5.750  -0.5628   0.04689   0.03909  -0.0457   1.0000   0.1215
  -5.500  -0.5443   0.04298   0.03441  -0.0464   1.0000   0.1260
  -5.250  -0.5244   0.04001   0.03112  -0.0463   1.0000   0.1311
  -5.000  -0.5028   0.03766   0.02825  -0.0462   1.0000   0.1426
  -4.750  -0.4823   0.03582   0.02632  -0.0456   1.0000   0.1588
  -4.500  -0.4620   0.03442   0.02491  -0.0449   1.0000   0.1803
  -4.250  -0.4411   0.03306   0.02351  -0.0443   1.0000   0.2077
  -4.000  -0.4201   0.03188   0.02234  -0.0435   1.0000   0.2387
  -3.750  -0.3985   0.03086   0.02125  -0.0429   1.0000   0.2759
  -3.500  -0.3787   0.03006   0.02067  -0.0418   1.0000   0.3153
  -3.250  -0.3588   0.02943   0.02021  -0.0407   1.0000   0.3636
  -3.000  -0.3402   0.02899   0.02002  -0.0392   1.0000   0.4167
  -2.750  -0.3227   0.02871   0.01999  -0.0373   1.0000   0.4768
  -2.500  -0.3070   0.02858   0.02011  -0.0348   1.0000   0.5393
  -2.250  -0.2931   0.02857   0.02030  -0.0317   1.0000   0.6024
  -2.000  -0.2817   0.02863   0.02054  -0.0280   1.0000   0.6631
  -1.750  -0.2734   0.02871   0.02077  -0.0235   1.0000   0.7226
  -1.500  -0.2684   0.02873   0.02091  -0.0183   1.0000   0.7827
  -1.250  -0.2662   0.02860   0.02090  -0.0124   1.0000   0.8489
  -1.000  -0.2303   0.02857   0.02087  -0.0136   1.0000   0.9576
  -0.750  -0.1952   0.02817   0.02012  -0.0196   1.0000   1.0000
  -0.500  -0.1697   0.02844   0.02001  -0.0225   1.0000   1.0000
  -0.250  -0.1453   0.02895   0.02020  -0.0244   1.0000   1.0000
   0.000  -0.1224   0.02957   0.02051  -0.0257   1.0000   1.0000
   0.250  -0.1007   0.03026   0.02095  -0.0266   1.0000   1.0000
   0.500  -0.0798   0.03099   0.02147  -0.0273   1.0000   1.0000
   0.750  -0.0594   0.03178   0.02207  -0.0279   1.0000   1.0000
   1.000  -0.0142   0.03362   0.02366  -0.0331   0.9880   1.0000
   1.250   0.0399   0.03577   0.02558  -0.0396   0.9705   1.0000
   1.500   0.0784   0.03715   0.02679  -0.0433   0.9566   1.0000
   1.750   0.1166   0.03857   0.02808  -0.0467   0.9439   1.0000
   2.000   0.1514   0.03981   0.02921  -0.0495   0.9309   1.0000
   2.250   0.1785   0.04082   0.03014  -0.0509   0.9188   1.0000
   2.500   0.2078   0.04195   0.03120  -0.0527   0.9060   1.0000
   2.750   0.2375   0.04312   0.03231  -0.0544   0.8931   1.0000
   3.000   0.2677   0.04430   0.03345  -0.0562   0.8801   1.0000
   3.250   0.2983   0.04550   0.03462  -0.0579   0.8670   1.0000
   3.500   0.3295   0.04670   0.03581  -0.0596   0.8537   1.0000
   3.750   0.3612   0.04789   0.03699  -0.0614   0.8403   1.0000
   4.000   0.3946   0.04908   0.03819  -0.0632   0.8271   1.0000
   4.250   0.4253   0.05018   0.03933  -0.0646   0.8133   1.0000
   4.500   0.4499   0.05125   0.04043  -0.0652   0.7993   1.0000
   4.750   0.4761   0.05231   0.04154  -0.0659   0.7850   1.0000
   5.000   0.5031   0.05337   0.04265  -0.0666   0.7705   1.0000
   5.250   0.5295   0.05443   0.04380  -0.0672   0.7559   1.0000
   5.500   0.5581   0.05541   0.04486  -0.0679   0.7409   1.0000
   5.750   0.5861   0.05638   0.04591  -0.0685   0.7260   1.0000
   6.000   0.6167   0.05720   0.04686  -0.0691   0.7107   1.0000
   6.250   0.6430   0.05807   0.04784  -0.0692   0.6947   1.0000
   6.500   0.6609   0.05921   0.04907  -0.0686   0.6781   1.0000
   6.750   0.6817   0.06024   0.05023  -0.0682   0.6612   1.0000
   7.000   0.7058   0.06110   0.05124  -0.0679   0.6441   1.0000
   7.250   0.7346   0.06164   0.05194  -0.0677   0.6270   1.0000
   7.500   0.7695   0.06165   0.05214  -0.0676   0.6099   1.0000
   7.750   0.8122   0.06087   0.05160  -0.0675   0.5931   1.0000
   8.000   0.8313   0.06157   0.05246  -0.0662   0.5741   1.0000
   8.250   0.8544   0.06184   0.05291  -0.0649   0.5543   1.0000
   8.500   0.9073   0.05911   0.05049  -0.0638   0.5364   1.0000
   8.750   1.0802   0.04397   0.03616  -0.0658   0.5164   1.0000
   9.000   1.1800   0.03760   0.03003  -0.0685   0.4714   1.0000
   9.250   1.2161   0.03614   0.02846  -0.0668   0.4279   1.0000
   9.500   1.2276   0.03642   0.02864  -0.0631   0.3890   1.0000
   9.750   1.2364   0.03705   0.02905  -0.0593   0.3503   1.0000
  10.000   1.2474   0.03802   0.02964  -0.0560   0.3110   1.0000
  10.250   1.2485   0.03965   0.03112  -0.0521   0.2789   1.0000
  10.500   1.2515   0.04146   0.03275  -0.0486   0.2485   1.0000
  10.750   1.2565   0.04351   0.03461  -0.0456   0.2198   1.0000
  11.000   1.2633   0.04568   0.03655  -0.0431   0.1934   1.0000
  11.250   1.2627   0.04798   0.03888  -0.0400   0.1734   1.0000
  11.500   1.2733   0.05048   0.04118  -0.0382   0.1518   1.0000
  11.750   1.2773   0.05327   0.04406  -0.0359   0.1368   1.0000
  12.000   1.2859   0.05627   0.04712  -0.0342   0.1238   1.0000
  12.250   1.3023   0.05962   0.05045  -0.0334   0.1122   1.0000
  12.500   1.2878   0.06290   0.05422  -0.0300   0.1090   1.0000
  12.750   1.2849   0.06632   0.05791  -0.0279   0.1040   1.0000
  13.000   1.3005   0.07079   0.06243  -0.0275   0.0991   1.0000
  13.250   1.2804   0.07484   0.06686  -0.0250   0.0985   1.0000
  13.500   1.2584   0.07930   0.07167  -0.0232   0.0982   1.0000
  13.750   1.2349   0.08421   0.07688  -0.0222   0.0982   1.0000
  14.000   1.2087   0.08969   0.08263  -0.0221   0.0983   1.0000
  14.250   1.1830   0.09571   0.08888  -0.0228   0.0988   1.0000
  14.500   1.1569   0.10237   0.09571  -0.0245   0.0993   1.0000
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