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EPPLER 855 AIRFOIL (e855-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 855 AIRFOIL (e855-il)
Reynolds number: 50,000
Max Cl/Cd: 23.02 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e855-il-50000-n5.txt
Download as CSV file: xf-e855-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 855 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3743   0.10243   0.09561  -0.0563   1.0000   0.0461
 -10.500  -0.3866   0.09655   0.08986  -0.0582   1.0000   0.0459
 -10.250  -0.4033   0.09010   0.08351  -0.0605   1.0000   0.0455
 -10.000  -0.4245   0.08376   0.07724  -0.0629   1.0000   0.0445
  -9.750  -0.4555   0.07714   0.07068  -0.0654   1.0000   0.0433
  -9.500  -0.5089   0.07014   0.06363  -0.0676   1.0000   0.0409
  -9.250  -0.5614   0.06625   0.05965  -0.0661   1.0000   0.0396
  -9.000  -0.5871   0.06348   0.05679  -0.0640   1.0000   0.0395
  -8.750  -0.6065   0.06083   0.05400  -0.0618   1.0000   0.0394
  -8.500  -0.6183   0.05834   0.05141  -0.0598   1.0000   0.0398
  -8.250  -0.5952   0.05486   0.04774  -0.0642   0.9907   0.0418
  -8.000  -0.5733   0.05113   0.04362  -0.0681   0.9809   0.0443
  -7.750  -0.5503   0.04717   0.03904  -0.0714   0.9712   0.0471
  -7.500  -0.5250   0.04375   0.03513  -0.0734   0.9617   0.0497
  -7.250  -0.4984   0.04174   0.03303  -0.0750   0.9518   0.0543
  -7.000  -0.4694   0.03943   0.03018  -0.0763   0.9425   0.0599
  -6.750  -0.4377   0.03760   0.02838  -0.0781   0.9345   0.0672
  -6.500  -0.4113   0.03594   0.02654  -0.0784   0.9242   0.0755
  -6.250  -0.3822   0.03446   0.02489  -0.0792   0.9149   0.0871
  -6.000  -0.3514   0.03293   0.02335  -0.0807   0.9065   0.1024
  -5.750  -0.3265   0.03154   0.02196  -0.0813   0.8958   0.1205
  -5.500  -0.2964   0.02994   0.02044  -0.0830   0.8876   0.1492
  -5.250  -0.2688   0.02828   0.01902  -0.0845   0.8782   0.1931
  -5.000  -0.2429   0.02686   0.01822  -0.0856   0.8686   0.2762
  -4.750  -0.2094   0.02668   0.01837  -0.0864   0.8613   0.3833
  -4.500  -0.1825   0.02700   0.01856  -0.0858   0.8508   0.4367
  -4.250  -0.1440   0.02723   0.01852  -0.0870   0.8449   0.4790
  -4.000  -0.1199   0.02756   0.01868  -0.0857   0.8339   0.5049
  -3.750  -0.0891   0.02779   0.01875  -0.0854   0.8260   0.5297
  -3.500  -0.0597   0.02794   0.01873  -0.0851   0.8176   0.5525
  -3.250  -0.0321   0.02799   0.01860  -0.0847   0.8087   0.5722
  -3.000  -0.0003   0.02791   0.01832  -0.0849   0.8014   0.5883
  -2.750   0.0252   0.02788   0.01813  -0.0844   0.7922   0.6009
  -2.500   0.0585   0.02766   0.01774  -0.0851   0.7856   0.6119
  -2.250   0.0838   0.02758   0.01747  -0.0849   0.7763   0.6220
  -2.000   0.1190   0.02730   0.01698  -0.0864   0.7700   0.6326
  -1.750   0.1418   0.02732   0.01690  -0.0856   0.7607   0.6405
  -1.500   0.1769   0.02708   0.01645  -0.0872   0.7546   0.6506
  -1.250   0.1990   0.02716   0.01644  -0.0863   0.7456   0.6583
  -1.000   0.2330   0.02698   0.01609  -0.0876   0.7395   0.6677
  -0.750   0.2553   0.02711   0.01614  -0.0870   0.7311   0.6761
  -0.500   0.2867   0.02703   0.01595  -0.0878   0.7249   0.6851
  -0.250   0.3111   0.02716   0.01598  -0.0876   0.7172   0.6945
   0.000   0.3384   0.02719   0.01596  -0.0876   0.7106   0.7033
   0.250   0.3674   0.02724   0.01592  -0.0881   0.7045   0.7135
   0.500   0.3882   0.02749   0.01615  -0.0873   0.6968   0.7231
   0.750   0.4218   0.02739   0.01599  -0.0882   0.6923   0.7337
   1.000   0.4367   0.02787   0.01649  -0.0867   0.6838   0.7447
   1.250   0.4664   0.02791   0.01648  -0.0870   0.6786   0.7569
   1.500   0.4855   0.02825   0.01686  -0.0859   0.6719   0.7692
   1.750   0.5070   0.02852   0.01716  -0.0851   0.6655   0.7829
   2.000   0.5389   0.02846   0.01711  -0.0856   0.6615   0.7985
   2.250   0.5466   0.02918   0.01794  -0.0830   0.6532   0.8161
   2.500   0.5726   0.02927   0.01809  -0.0826   0.6484   0.8370
   2.750   0.5940   0.02956   0.01846  -0.0818   0.6430   0.8633
   3.000   0.6132   0.03013   0.01919  -0.0811   0.6360   0.9031
   3.250   0.6605   0.03011   0.01920  -0.0851   0.6318   1.0000
   3.500   0.6733   0.03125   0.02031  -0.0844   0.6243   1.0000
   3.750   0.7000   0.03186   0.02088  -0.0852   0.6189   1.0000
   4.000   0.7374   0.03204   0.02100  -0.0871   0.6155   1.0000
   4.250   0.7359   0.03377   0.02275  -0.0843   0.6065   1.0000
   4.500   0.7660   0.03420   0.02318  -0.0851   0.6022   1.0000
   4.750   0.7783   0.03542   0.02441  -0.0838   0.5958   1.0000
   5.000   0.7891   0.03664   0.02566  -0.0823   0.5890   1.0000
   5.250   0.8246   0.03684   0.02588  -0.0835   0.5856   1.0000
   5.750   0.8381   0.03977   0.02891  -0.0796   0.5716   1.0000
   6.250   0.8517   0.04301   0.03226  -0.0762   0.5573   1.0000
   6.500   0.8897   0.04286   0.03220  -0.0772   0.5543   1.0000
   6.750   0.8657   0.04649   0.03588  -0.0733   0.5424   1.0000
   7.000   0.9029   0.04622   0.03571  -0.0739   0.5394   1.0000
   7.250   0.8820   0.05001   0.03955  -0.0710   0.5270   1.0000
   7.500   0.9199   0.04950   0.03915  -0.0713   0.5241   1.0000
   7.750   0.9015   0.05342   0.04314  -0.0691   0.5113   1.0000
   8.000   0.9406   0.05257   0.04243  -0.0692   0.5086   1.0000
   8.250   0.9245   0.05649   0.04642  -0.0675   0.4955   1.0000
   8.500   0.9654   0.05526   0.04534  -0.0672   0.4929   1.0000
   8.750   0.9517   0.05903   0.04919  -0.0658   0.4795   1.0000
   9.250   0.9826   0.06101   0.05146  -0.0640   0.4633   1.0000
   9.750   0.9736   0.06688   0.05753  -0.0620   0.4378   1.0000
  10.000   1.0140   0.06490   0.05575  -0.0609   0.4333   1.0000
  10.250   1.0113   0.06758   0.05856  -0.0600   0.4198   1.0000
  10.500   1.0121   0.06989   0.06100  -0.0591   0.4068   1.0000
  11.000   1.0585   0.06878   0.06026  -0.0565   0.3886   1.0000
  11.250   1.0609   0.07076   0.06237  -0.0556   0.3747   1.0000
  11.750   1.0724   0.07388   0.06582  -0.0539   0.3470   1.0000
  12.250   1.0928   0.07572   0.06796  -0.0519   0.3186   1.0000
  12.500   1.1066   0.07609   0.06849  -0.0509   0.3036   1.0000
  12.750   1.1242   0.07588   0.06841  -0.0496   0.2876   1.0000
  13.000   1.1424   0.07556   0.06816  -0.0482   0.2697   1.0000
  13.250   1.1486   0.07720   0.06987  -0.0475   0.2502   1.0000
  13.500   1.1621   0.07767   0.07026  -0.0463   0.2300   1.0000
  13.750   1.1688   0.07928   0.07177  -0.0456   0.2112   1.0000
  14.000   1.1687   0.08214   0.07458  -0.0454   0.1940   1.0000
  14.250   1.1689   0.08505   0.07744  -0.0453   0.1785   1.0000
  14.500   1.1683   0.08816   0.08050  -0.0453   0.1645   1.0000
  14.750   1.1680   0.09133   0.08364  -0.0455   0.1519   1.0000
  15.000   1.1688   0.09437   0.08661  -0.0457   0.1406   1.0000
  15.250   1.1683   0.09773   0.08999  -0.0462   0.1300   1.0000
  15.500   1.1667   0.10150   0.09386  -0.0469   0.1206   1.0000
  15.750   1.1679   0.10471   0.09711  -0.0475   0.1122   1.0000
  16.000   1.1681   0.10817   0.10062  -0.0483   0.1042   1.0000
  16.250   1.1673   0.11202   0.10460  -0.0492   0.0974   1.0000
  16.500   1.1693   0.11517   0.10776  -0.0500   0.0907   1.0000
  16.750   1.1659   0.11964   0.11240  -0.0516   0.0853   1.0000
  17.000   1.1643   0.12373   0.11663  -0.0531   0.0801   1.0000
  17.250   1.1664   0.12703   0.11993  -0.0541   0.0752   1.0000
  17.500   1.1554   0.13340   0.12661  -0.0572   0.0718   1.0000
  17.750   1.1506   0.13842   0.13177  -0.0596   0.0683   1.0000
  18.000   1.1567   0.14088   0.13415  -0.0605   0.0642   1.0000
  18.250   1.1371   0.14968   0.14327  -0.0655   0.0628   1.0000
  18.500   1.1117   0.16053   0.15436  -0.0720   0.0622   1.0000
  18.750   1.0757   0.17558   0.16953  -0.0811   0.0623   1.0000
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