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EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il)
Reynolds number: 50,000
Max Cl/Cd: 32.31 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ec863914-il-50000-n5.txt
Download as CSV file: xf-ec863914-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER EC 86(-3)-914 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4710   0.10998   0.10349  -0.0432   1.0000   0.0264
 -10.000  -0.4842   0.10418   0.09774  -0.0447   1.0000   0.0260
  -9.750  -0.5002   0.09802   0.09160  -0.0466   1.0000   0.0255
  -9.500  -0.5194   0.09156   0.08514  -0.0489   1.0000   0.0251
  -9.250  -0.5408   0.08535   0.07888  -0.0512   1.0000   0.0248
  -9.000  -0.5637   0.07985   0.07332  -0.0530   1.0000   0.0244
  -8.750  -0.5887   0.07527   0.06866  -0.0535   1.0000   0.0242
  -8.500  -0.6161   0.07151   0.06484  -0.0527   1.0000   0.0240
  -8.250  -0.6380   0.06762   0.06082  -0.0527   1.0000   0.0239
  -8.000  -0.6505   0.06350   0.05649  -0.0538   1.0000   0.0237
  -7.750  -0.6541   0.05962   0.05231  -0.0550   1.0000   0.0236
  -7.500  -0.6507   0.05609   0.04846  -0.0559   1.0000   0.0235
  -7.250  -0.6417   0.05292   0.04495  -0.0566   1.0000   0.0235
  -7.000  -0.6286   0.05018   0.04188  -0.0570   1.0000   0.0236
  -6.750  -0.6128   0.04778   0.03919  -0.0572   1.0000   0.0238
  -6.500  -0.5953   0.04572   0.03686  -0.0572   1.0000   0.0239
  -6.250  -0.5765   0.04391   0.03482  -0.0572   1.0000   0.0243
  -6.000  -0.5564   0.04229   0.03294  -0.0573   1.0000   0.0245
  -5.750  -0.5348   0.04076   0.03118  -0.0577   1.0000   0.0251
  -5.500  -0.5118   0.03944   0.02964  -0.0583   1.0000   0.0256
  -5.250  -0.4812   0.03826   0.02819  -0.0603   0.9980   0.0266
  -5.000  -0.4456   0.03736   0.02696  -0.0632   0.9947   0.0284
  -4.750  -0.4096   0.03605   0.02545  -0.0665   0.9914   0.0311
  -4.500  -0.3733   0.03520   0.02430  -0.0694   0.9882   0.0359
  -4.250  -0.3367   0.03440   0.02336  -0.0720   0.9850   0.0441
  -4.000  -0.2970   0.03279   0.02287  -0.0770   0.9821   0.2103
  -3.750  -0.2574   0.03277   0.02290  -0.0808   0.9782   0.2751
  -3.500  -0.2199   0.03296   0.02298  -0.0835   0.9746   0.3010
  -3.250  -0.1883   0.03298   0.02288  -0.0848   0.9697   0.3172
  -3.000  -0.1533   0.03306   0.02290  -0.0871   0.9652   0.3458
  -2.750  -0.1143   0.03321   0.02322  -0.0901   0.9616   0.3921
  -2.500  -0.0849   0.03314   0.02347  -0.0911   0.9560   0.4468
  -2.250  -0.0590   0.03352   0.02417  -0.0903   0.9507   0.4926
  -2.000  -0.0446   0.03400   0.02489  -0.0868   0.9435   0.5283
  -1.750  -0.0250   0.03480   0.02576  -0.0841   0.9372   0.5702
  -1.500  -0.0021   0.03538   0.02618  -0.0830   0.9297   0.6152
  -1.250   0.0322   0.03614   0.02673  -0.0843   0.9240   0.6565
  -1.000   0.0570   0.03668   0.02711  -0.0838   0.9163   0.6841
  -0.750   0.0838   0.03731   0.02760  -0.0830   0.9104   0.7055
  -0.500   0.1044   0.03764   0.02783  -0.0816   0.9017   0.7249
  -0.250   0.1293   0.03801   0.02806  -0.0810   0.8940   0.7434
   0.000   0.1560   0.03833   0.02829  -0.0804   0.8875   0.7594
   0.250   0.1764   0.03850   0.02839  -0.0790   0.8783   0.7740
   0.500   0.1978   0.03862   0.02844  -0.0777   0.8696   0.7881
   0.750   0.2222   0.03870   0.02844  -0.0768   0.8619   0.8018
   1.000   0.2441   0.03869   0.02840  -0.0754   0.8531   0.8178
   1.250   0.2594   0.03857   0.02828  -0.0727   0.8428   0.8355
   1.500   0.2727   0.03830   0.02799  -0.0694   0.8325   0.8541
   1.750   0.2921   0.03796   0.02764  -0.0673   0.8233   0.8732
   2.000   0.3156   0.03759   0.02725  -0.0662   0.8137   0.8888
   2.250   0.3361   0.03726   0.02692  -0.0649   0.8018   0.9000
   2.500   0.3600   0.03692   0.02658  -0.0643   0.7901   0.9088
   2.750   0.3907   0.03657   0.02623  -0.0649   0.7795   0.9159
   3.000   0.4265   0.03613   0.02581  -0.0662   0.7696   0.9210
   3.250   0.4561   0.03591   0.02561  -0.0668   0.7563   0.9255
   3.500   0.4861   0.03558   0.02532  -0.0673   0.7431   0.9295
   3.750   0.5187   0.03519   0.02497  -0.0682   0.7298   0.9333
   4.000   0.5530   0.03471   0.02457  -0.0691   0.7164   0.9370
   4.250   0.5866   0.03408   0.02401  -0.0697   0.7027   0.9406
   4.500   0.6207   0.03345   0.02348  -0.0703   0.6883   0.9441
   4.750   0.6542   0.03288   0.02300  -0.0709   0.6725   0.9478
   5.000   0.6873   0.03230   0.02253  -0.0713   0.6555   0.9517
   5.250   0.7225   0.03163   0.02194  -0.0720   0.6375   0.9557
   5.500   0.7584   0.03102   0.02140  -0.0727   0.6175   0.9596
   5.750   0.7923   0.03060   0.02107  -0.0733   0.5937   0.9642
   6.000   0.8284   0.03012   0.02063  -0.0742   0.5681   0.9700
   6.500   0.8974   0.02957   0.02002  -0.0756   0.5114   1.0000
   6.750   0.9303   0.02985   0.02021  -0.0765   0.4825   1.0000
   7.000   0.9601   0.03039   0.02069  -0.0772   0.4550   1.0000
   7.250   0.9880   0.03111   0.02141  -0.0778   0.4301   1.0000
   7.500   1.0175   0.03184   0.02207  -0.0785   0.4085   1.0000
   7.750   1.0451   0.03272   0.02298  -0.0792   0.3885   1.0000
   8.000   1.0744   0.03360   0.02390  -0.0801   0.3713   1.0000
   8.250   1.1051   0.03450   0.02486  -0.0813   0.3560   1.0000
   8.500   1.1366   0.03541   0.02589  -0.0825   0.3422   1.0000
   8.750   1.1700   0.03632   0.02690  -0.0840   0.3299   1.0000
   9.000   1.2047   0.03728   0.02799  -0.0856   0.3191   1.0000
   9.250   1.2343   0.03842   0.02938  -0.0867   0.3087   1.0000
   9.500   1.2670   0.03952   0.03070  -0.0881   0.2994   1.0000
   9.750   1.2979   0.04073   0.03215  -0.0893   0.2907   1.0000
  10.000   1.3267   0.04209   0.03380  -0.0902   0.2828   1.0000
  10.250   1.3566   0.04336   0.03530  -0.0912   0.2748   1.0000
  10.500   1.3769   0.04496   0.03727  -0.0910   0.2671   1.0000
  10.750   1.4057   0.04620   0.03872  -0.0918   0.2588   1.0000
  11.000   1.4071   0.04787   0.04075  -0.0892   0.2486   1.0000
  11.250   1.4063   0.04930   0.04238  -0.0864   0.2365   1.0000
  11.500   1.3984   0.05086   0.04416  -0.0832   0.2231   1.0000
  11.750   1.3842   0.05285   0.04628  -0.0798   0.2085   1.0000
  12.000   1.3673   0.05541   0.04897  -0.0769   0.1932   1.0000
  12.250   1.3501   0.05858   0.05227  -0.0749   0.1764   1.0000
  12.500   1.3342   0.06229   0.05607  -0.0738   0.1581   1.0000
  12.750   1.3235   0.06641   0.06044  -0.0736   0.1366   1.0000
  13.000   1.3139   0.07097   0.06518  -0.0741   0.1088   1.0000
  13.250   1.2986   0.07651   0.07060  -0.0750   0.0809   1.0000
  13.500   1.2804   0.08298   0.07695  -0.0767   0.0656   1.0000
  13.750   1.2625   0.08993   0.08392  -0.0789   0.0566   1.0000
  14.000   1.2450   0.09722   0.09129  -0.0818   0.0516   1.0000
  14.250   1.2290   0.10460   0.09882  -0.0851   0.0474   1.0000
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