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EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il)
Reynolds number: 50,000
Max Cl/Cd: 34.87 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ec863914-il-50000.txt
Download as CSV file: xf-ec863914-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4542   0.12214   0.11581  -0.0360   1.0000   0.0984
  -9.500  -0.4571   0.11777   0.11149  -0.0359   1.0000   0.0939
  -9.250  -0.4879   0.10916   0.10303  -0.0403   1.0000   0.0862
  -9.000  -0.4914   0.10536   0.09929  -0.0399   1.0000   0.0843
  -8.750  -0.5042   0.10026   0.09429  -0.0406   1.0000   0.0820
  -8.250  -0.6394   0.07938   0.07338  -0.0528   1.0000   0.0743
  -8.000  -0.6475   0.07483   0.06881  -0.0533   1.0000   0.0735
  -7.750  -0.6553   0.07017   0.06403  -0.0545   1.0000   0.0726
  -7.500  -0.6614   0.06466   0.05829  -0.0565   1.0000   0.0715
  -7.250  -0.6594   0.05916   0.05241  -0.0590   1.0000   0.0702
  -7.000  -0.6485   0.05356   0.04627  -0.0620   1.0000   0.0690
  -6.750  -0.6295   0.04885   0.04095  -0.0644   1.0000   0.0681
  -6.500  -0.6067   0.04523   0.03681  -0.0658   1.0000   0.0680
  -6.250  -0.5830   0.04244   0.03361  -0.0662   1.0000   0.0687
  -6.000  -0.5599   0.04030   0.03115  -0.0658   1.0000   0.0700
  -5.750  -0.5372   0.03862   0.02919  -0.0650   1.0000   0.0728
  -5.500  -0.5157   0.03709   0.02760  -0.0640   1.0000   0.0767
  -5.250  -0.4927   0.03578   0.02627  -0.0636   1.0000   0.0840
  -5.000  -0.4675   0.03435   0.02482  -0.0637   1.0000   0.0954
  -4.750  -0.4355   0.03250   0.02349  -0.0657   1.0000   0.1320
  -4.500  -0.3737   0.03252   0.02404  -0.0764   1.0000   0.3453
  -4.250  -0.3538   0.03305   0.02476  -0.0751   1.0000   0.3914
  -4.000  -0.3323   0.03292   0.02457  -0.0741   1.0000   0.4123
  -3.750  -0.3121   0.03292   0.02459  -0.0727   1.0000   0.4400
  -3.500  -0.2898   0.03282   0.02442  -0.0720   1.0000   0.4653
  -3.250  -0.2734   0.03298   0.02466  -0.0696   1.0000   0.4907
  -3.000  -0.2570   0.03312   0.02487  -0.0673   1.0000   0.5110
  -2.750  -0.2401   0.03328   0.02506  -0.0651   1.0000   0.5286
  -2.500  -0.2226   0.03351   0.02529  -0.0632   1.0000   0.5477
  -2.250  -0.2086   0.03394   0.02576  -0.0603   1.0000   0.5679
  -2.000  -0.1985   0.03457   0.02642  -0.0564   1.0000   0.5888
  -1.750  -0.1880   0.03524   0.02708  -0.0526   1.0000   0.6137
  -1.500  -0.1788   0.03595   0.02779  -0.0485   1.0000   0.6434
  -1.250  -0.1695   0.03667   0.02849  -0.0445   1.0000   0.6818
  -1.000  -0.1690   0.03724   0.02906  -0.0383   1.0000   0.7167
  -0.750  -0.1691   0.03755   0.02935  -0.0322   1.0000   0.7573
  -0.500  -0.1714   0.03759   0.02935  -0.0257   1.0000   0.7980
  -0.250  -0.1755   0.03733   0.02903  -0.0191   1.0000   0.8364
   0.000  -0.1797   0.03679   0.02839  -0.0128   1.0000   0.8725
   0.250  -0.1805   0.03615   0.02766  -0.0077   1.0000   0.9083
   0.500  -0.1777   0.03535   0.02679  -0.0036   1.0000   0.9416
   0.750  -0.1525   0.03494   0.02629  -0.0046   1.0000   0.9739
   1.000  -0.1255   0.03438   0.02568  -0.0072   1.0000   1.0000
   1.250  -0.1078   0.03471   0.02589  -0.0083   1.0000   1.0000
   1.500  -0.0868   0.03530   0.02634  -0.0099   1.0000   1.0000
   1.750  -0.0642   0.03608   0.02703  -0.0119   1.0000   1.0000
   2.000  -0.0407   0.03702   0.02788  -0.0140   1.0000   1.0000
   2.250  -0.0170   0.03809   0.02887  -0.0162   1.0000   1.0000
   2.500   0.0069   0.03929   0.03002  -0.0185   1.0000   1.0000
   2.750   0.0438   0.04147   0.03213  -0.0233   0.9948   1.0000
   3.000   0.1695   0.04566   0.03610  -0.0408   0.9130   1.0000
   3.250   0.2204   0.04668   0.03707  -0.0459   0.8858   1.0000
   3.500   0.2753   0.04767   0.03804  -0.0515   0.8632   1.0000
   3.750   0.3145   0.04811   0.03849  -0.0545   0.8396   1.0000
   4.000   0.3610   0.04855   0.03896  -0.0583   0.8179   1.0000
   4.250   0.4114   0.04876   0.03920  -0.0624   0.7969   1.0000
   4.500   0.4550   0.04880   0.03930  -0.0652   0.7749   1.0000
   4.750   0.5083   0.04837   0.03896  -0.0688   0.7548   1.0000
   5.000   0.5513   0.04797   0.03865  -0.0709   0.7329   1.0000
   5.250   0.6029   0.04701   0.03784  -0.0735   0.7129   1.0000
   5.500   0.6631   0.04525   0.03621  -0.0763   0.6956   1.0000
   5.750   0.7013   0.04447   0.03560  -0.0771   0.6719   1.0000
   6.000   0.7627   0.04180   0.03310  -0.0790   0.6550   1.0000
   6.250   0.8353   0.03815   0.02966  -0.0817   0.6387   1.0000
   6.500   0.8976   0.03556   0.02722  -0.0839   0.6141   1.0000
   6.750   0.9785   0.03261   0.02435  -0.0886   0.5837   1.0000
   7.000   1.0514   0.03144   0.02308  -0.0937   0.5478   1.0000
   7.250   1.0987   0.03201   0.02361  -0.0966   0.5163   1.0000
   7.500   1.1477   0.03291   0.02449  -0.1000   0.4892   1.0000
   7.750   1.1800   0.03427   0.02595  -0.1012   0.4679   1.0000
   8.000   1.2211   0.03562   0.02736  -0.1038   0.4495   1.0000
   8.250   1.2580   0.03711   0.02894  -0.1058   0.4335   1.0000
   8.500   1.2831   0.03887   0.03092  -0.1062   0.4202   1.0000
   8.750   1.3031   0.04089   0.03329  -0.1059   0.4091   1.0000
   9.000   1.3268   0.04287   0.03551  -0.1061   0.3982   1.0000
   9.250   1.3588   0.04475   0.03758  -0.1075   0.3874   1.0000
   9.500   1.3658   0.04722   0.04043  -0.1055   0.3788   1.0000
   9.750   1.3799   0.04968   0.04318  -0.1046   0.3701   1.0000
  10.000   1.4144   0.05158   0.04529  -0.1060   0.3591   1.0000
  10.250   1.3895   0.05520   0.04935  -0.1005   0.3536   1.0000
  10.500   1.4101   0.05721   0.05161  -0.1001   0.3419   1.0000
  10.750   1.4269   0.05883   0.05346  -0.0989   0.3279   1.0000
  11.000   1.3891   0.06334   0.05829  -0.0929   0.3247   1.0000
  11.250   1.3320   0.07027   0.06542  -0.0873   0.3256   1.0000
  11.500   1.2501   0.08146   0.07664  -0.0841   0.3294   1.0000
  11.750   1.3173   0.07708   0.07263  -0.0833   0.3043   1.0000
  12.000   1.2841   0.08416   0.07982  -0.0819   0.3005   1.0000
  12.250   1.3713   0.05710   0.05137  -0.0719   0.1721   1.0000
  12.500   1.3436   0.06134   0.05574  -0.0690   0.1490   1.0000
  12.750   1.3194   0.06614   0.06045  -0.0674   0.1268   1.0000
  13.000   1.3007   0.07122   0.06543  -0.0668   0.1094   1.0000
  13.250   1.2872   0.07638   0.07049  -0.0670   0.0966   1.0000
  13.500   1.2780   0.08150   0.07560  -0.0675   0.0869   1.0000
  13.750   1.2737   0.08609   0.08008  -0.0679   0.0796   1.0000
  14.000   1.2732   0.09073   0.08495  -0.0683   0.0740   1.0000
  14.250   1.2824   0.09398   0.08806  -0.0679   0.0684   1.0000
  14.500   1.2783   0.09943   0.09390  -0.0692   0.0661   1.0000
  14.750   1.2719   0.10521   0.10000  -0.0711   0.0642   1.0000
  15.000   1.2632   0.11149   0.10656  -0.0737   0.0628   1.0000
  15.250   1.2506   0.11864   0.11399  -0.0773   0.0622   1.0000
  15.500   1.2282   0.12823   0.12393  -0.0831   0.0634   1.0000
  15.750   1.1974   0.14049   0.13650  -0.0913   0.0662   1.0000
  16.000   1.1737   0.15209   0.14825  -0.0991   0.0681   1.0000
  16.250   1.1559   0.16308   0.15929  -0.1063   0.0692   1.0000
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