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E186 (10.27%) (e186-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E186 (10.27%) (e186-il)
Reynolds number: 50,000
Max Cl/Cd: 31.16 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e186-il-50000-n5.txt
Download as CSV file: xf-e186-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E186  (10.27%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.6356   0.09647   0.09045   0.0131   1.0000   0.0481
  -9.250  -0.6434   0.08972   0.08377   0.0079   1.0000   0.0470
  -9.000  -0.6597   0.08187   0.07595   0.0013   1.0000   0.0457
  -8.750  -0.6832   0.07538   0.06937  -0.0017   1.0000   0.0444
  -8.500  -0.7048   0.06953   0.06322  -0.0030   1.0000   0.0433
  -8.000  -0.7092   0.06081   0.05391  -0.0024   1.0000   0.0427
  -7.750  -0.7057   0.05661   0.04939  -0.0018   1.0000   0.0427
  -7.500  -0.6994   0.05256   0.04497  -0.0009   1.0000   0.0427
  -7.250  -0.6900   0.04874   0.04072   0.0002   1.0000   0.0427
  -7.000  -0.6775   0.04509   0.03667   0.0012   1.0000   0.0430
  -6.750  -0.6619   0.04171   0.03299   0.0020   1.0000   0.0439
  -6.500  -0.6435   0.03926   0.03036   0.0025   1.0000   0.0462
  -6.250  -0.6229   0.03700   0.02783   0.0030   1.0000   0.0491
  -6.000  -0.5999   0.03449   0.02484   0.0035   1.0000   0.0515
  -5.750  -0.5738   0.03205   0.02201   0.0038   1.0000   0.0530
  -5.500  -0.5453   0.02991   0.01951   0.0038   1.0000   0.0548
  -5.250  -0.5174   0.02796   0.01751   0.0035   1.0000   0.0575
  -5.000  -0.4905   0.02643   0.01593   0.0033   1.0000   0.0617
  -4.750  -0.4595   0.02507   0.01436   0.0025   0.9741   0.0686
  -4.500  -0.4203   0.02362   0.01287  -0.0003   0.9404   0.0898
  -4.250  -0.3863   0.02193   0.01146  -0.0019   0.9154   0.1433
  -4.000  -0.3634   0.02023   0.01075  -0.0020   0.8929   0.2983
  -3.750  -0.3474   0.01905   0.01037   0.0003   0.8739   0.4623
  -3.500  -0.3201   0.01817   0.01032   0.0023   0.8589   0.6583
  -3.250  -0.2522   0.01838   0.01049  -0.0020   0.8468   0.8177
  -3.000  -0.2011   0.01891   0.01059  -0.0044   0.8332   0.8823
  -2.750  -0.1542   0.01932   0.01058  -0.0070   0.8199   0.9267
  -2.500  -0.1041   0.01953   0.01035  -0.0109   0.8070   0.9619
  -2.250  -0.0495   0.01940   0.00984  -0.0164   0.7949   0.9910
  -2.000  -0.0164   0.01922   0.00937  -0.0181   0.7829   1.0000
  -1.750   0.0042   0.01919   0.00909  -0.0174   0.7716   1.0000
  -1.500   0.0252   0.01918   0.00888  -0.0166   0.7612   1.0000
  -1.250   0.0479   0.01921   0.00873  -0.0161   0.7505   1.0000
  -1.000   0.0705   0.01926   0.00862  -0.0156   0.7408   1.0000
  -0.750   0.0923   0.01933   0.00851  -0.0147   0.7322   1.0000
  -0.500   0.1164   0.01944   0.00851  -0.0145   0.7224   1.0000
  -0.250   0.1397   0.01957   0.00853  -0.0141   0.7139   1.0000
   0.000   0.1627   0.01971   0.00857  -0.0134   0.7057   1.0000
   0.250   0.1870   0.01990   0.00869  -0.0132   0.6968   1.0000
   0.500   0.2096   0.02007   0.00877  -0.0123   0.6899   1.0000
   0.750   0.2345   0.02032   0.00900  -0.0123   0.6808   1.0000
   1.000   0.2578   0.02055   0.00919  -0.0116   0.6735   1.0000
   1.250   0.2820   0.02082   0.00945  -0.0113   0.6653   1.0000
   1.500   0.3058   0.02111   0.00973  -0.0108   0.6577   1.0000
   1.750   0.3293   0.02140   0.01003  -0.0103   0.6502   1.0000
   2.000   0.3534   0.02175   0.01043  -0.0100   0.6421   1.0000
   2.250   0.3767   0.02205   0.01075  -0.0092   0.6351   1.0000
   2.500   0.4010   0.02247   0.01124  -0.0091   0.6266   1.0000
   2.750   0.4239   0.02277   0.01156  -0.0081   0.6199   1.0000
   3.000   0.4481   0.02325   0.01219  -0.0080   0.6108   1.0000
   3.250   0.4709   0.02356   0.01254  -0.0070   0.6039   1.0000
   3.500   0.4946   0.02404   0.01316  -0.0067   0.5944   1.0000
   3.750   0.5177   0.02449   0.01372  -0.0061   0.5854   1.0000
   4.000   0.5403   0.02475   0.01407  -0.0049   0.5774   1.0000
   4.250   0.5632   0.02524   0.01478  -0.0044   0.5663   1.0000
   4.500   0.5857   0.02563   0.01532  -0.0035   0.5556   1.0000
   4.750   0.6080   0.02588   0.01569  -0.0022   0.5451   1.0000
   5.000   0.6303   0.02598   0.01592  -0.0007   0.5343   1.0000
   5.250   0.6524   0.02621   0.01633   0.0005   0.5208   1.0000
   5.500   0.6745   0.02630   0.01666   0.0019   0.5066   1.0000
   5.750   0.6964   0.02636   0.01692   0.0033   0.4905   1.0000
   6.000   0.7178   0.02645   0.01724   0.0047   0.4714   1.0000
   6.250   0.7397   0.02618   0.01715   0.0066   0.4517   1.0000
   6.500   0.7608   0.02611   0.01731   0.0081   0.4267   1.0000
   6.750   0.7816   0.02595   0.01733   0.0099   0.3970   1.0000
   7.000   0.8011   0.02597   0.01756   0.0115   0.3572   1.0000
   7.250   0.8182   0.02626   0.01780   0.0133   0.3036   1.0000
   7.500   0.8300   0.02731   0.01847   0.0151   0.2418   1.0000
   7.750   0.8364   0.02925   0.02003   0.0167   0.1887   1.0000
   8.000   0.8395   0.03150   0.02201   0.0182   0.1494   1.0000
   8.250   0.8399   0.03387   0.02415   0.0199   0.1206   1.0000
   8.500   0.8389   0.03625   0.02637   0.0216   0.0968   1.0000
   8.750   0.8365   0.03860   0.02857   0.0232   0.0804   1.0000
   9.000   0.8335   0.04092   0.03084   0.0249   0.0683   1.0000
   9.250   0.8321   0.04319   0.03314   0.0267   0.0590   1.0000
   9.500   0.8327   0.04547   0.03537   0.0282   0.0532   1.0000
   9.750   0.8382   0.04754   0.03767   0.0295   0.0476   1.0000
  10.000   0.8400   0.04992   0.03994   0.0305   0.0432   1.0000
  10.250   0.8529   0.05197   0.04233   0.0324   0.0399   1.0000
  10.500   0.8647   0.05429   0.04492   0.0340   0.0377   1.0000
  10.750   0.8720   0.05704   0.04790   0.0350   0.0359   1.0000
  11.000   0.8753   0.06007   0.05114   0.0355   0.0349   1.0000
  11.250   0.8753   0.06342   0.05467   0.0356   0.0341   1.0000
  11.500   0.8722   0.06710   0.05851   0.0353   0.0334   1.0000
  11.750   0.8664   0.07119   0.06276   0.0346   0.0329   1.0000
  12.000   0.8574   0.07575   0.06750   0.0332   0.0326   1.0000
  12.500   0.8293   0.08677   0.07888   0.0283   0.0326   1.0000
  12.750   0.8040   0.09497   0.08736   0.0232   0.0336   1.0000
  13.000   0.7719   0.10607   0.09866   0.0163   0.0350   1.0000
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