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EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 68 AIRFOIL (e68-il)
Reynolds number: 100,000
Max Cl/Cd: 56.84 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e68-il-100000.txt
Download as CSV file: xf-e68-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3736   0.11266   0.10786  -0.0408   1.0000   0.1220
  -9.750  -0.4005   0.11078   0.10611  -0.0416   1.0000   0.1265
  -9.500  -0.4458   0.10936   0.10488  -0.0433   1.0000   0.1276
  -9.250  -0.4229   0.10484   0.10034  -0.0397   1.0000   0.1292
  -9.000  -0.4166   0.10234   0.09786  -0.0370   1.0000   0.1310
  -8.750  -0.4204   0.10012   0.09569  -0.0350   1.0000   0.1330
  -8.500  -0.4308   0.09788   0.09352  -0.0334   1.0000   0.1354
  -8.250  -0.4489   0.09561   0.09134  -0.0322   1.0000   0.1380
  -8.000  -0.4605   0.07533   0.07152  -0.0363   1.0000   0.0822
  -7.500  -0.6223   0.06402   0.05956  -0.0460   1.0000   0.0704
  -7.250  -0.6529   0.05228   0.04678  -0.0483   1.0000   0.0611
  -7.000  -0.6440   0.04880   0.04296  -0.0476   1.0000   0.0596
  -6.750  -0.6346   0.04462   0.03844  -0.0473   1.0000   0.0589
  -6.500  -0.6215   0.04089   0.03426  -0.0471   1.0000   0.0584
  -6.250  -0.6052   0.03763   0.03047  -0.0467   1.0000   0.0585
  -6.000  -0.5799   0.03500   0.02718  -0.0474   0.9983   0.0597
  -5.750  -0.5447   0.03247   0.02443  -0.0502   0.9940   0.0636
  -5.500  -0.5100   0.03095   0.02265  -0.0521   0.9886   0.0687
  -5.250  -0.4718   0.02915   0.02048  -0.0542   0.9843   0.0740
  -5.000  -0.4399   0.02793   0.01920  -0.0554   0.9787   0.0842
  -4.750  -0.4048   0.02680   0.01818  -0.0575   0.9736   0.1068
  -4.500  -0.3717   0.02608   0.01750  -0.0592   0.9680   0.1386
  -4.250  -0.3392   0.02557   0.01711  -0.0609   0.9619   0.1756
  -4.000  -0.3030   0.02510   0.01675  -0.0631   0.9570   0.2177
  -3.750  -0.2752   0.02459   0.01642  -0.0638   0.9501   0.2616
  -3.500  -0.2374   0.02428   0.01636  -0.0662   0.9453   0.3216
  -3.250  -0.2126   0.02399   0.01633  -0.0662   0.9378   0.3777
  -3.000  -0.1777   0.02391   0.01648  -0.0678   0.9323   0.4461
  -2.750  -0.1518   0.02390   0.01665  -0.0677   0.9251   0.5050
  -2.500  -0.1203   0.02398   0.01687  -0.0683   0.9189   0.5640
  -2.250  -0.0934   0.02411   0.01713  -0.0680   0.9122   0.6142
  -2.000  -0.0664   0.02424   0.01736  -0.0675   0.9050   0.6611
  -1.750  -0.0381   0.02445   0.01763  -0.0672   0.8989   0.7063
  -1.500  -0.0172   0.02460   0.01784  -0.0655   0.8908   0.7469
  -1.250   0.0115   0.02478   0.01805  -0.0648   0.8854   0.7880
  -1.000   0.0253   0.02490   0.01821  -0.0618   0.8762   0.8266
  -0.750   0.0530   0.02497   0.01829  -0.0606   0.8710   0.8707
  -0.500   0.0687   0.02502   0.01837  -0.0580   0.8617   0.9180
  -0.250   0.1395   0.02513   0.01839  -0.0660   0.8586   0.9697
   0.000   0.1796   0.02529   0.01840  -0.0701   0.8499   1.0000
   0.250   0.2196   0.02529   0.01824  -0.0732   0.8443   1.0000
   0.500   0.2409   0.02560   0.01842  -0.0733   0.8346   1.0000
   0.750   0.2837   0.02561   0.01831  -0.0763   0.8295   1.0000
   1.000   0.3048   0.02600   0.01861  -0.0759   0.8197   1.0000
   1.250   0.3479   0.02595   0.01847  -0.0787   0.8149   1.0000
   1.500   0.3682   0.02638   0.01884  -0.0780   0.8047   1.0000
   1.750   0.4121   0.02623   0.01863  -0.0807   0.8002   1.0000
   2.000   0.4315   0.02670   0.01905  -0.0798   0.7897   1.0000
   2.250   0.4766   0.02639   0.01873  -0.0824   0.7855   1.0000
   2.500   0.4961   0.02685   0.01916  -0.0814   0.7748   1.0000
   2.750   0.5428   0.02636   0.01868  -0.0841   0.7709   1.0000
   3.000   0.5629   0.02676   0.01908  -0.0831   0.7600   1.0000
   3.250   0.6123   0.02602   0.01836  -0.0859   0.7565   1.0000
   3.500   0.6696   0.02506   0.01747  -0.0900   0.7543   1.0000
   3.750   0.6856   0.02544   0.01787  -0.0880   0.7421   1.0000
   4.000   0.7088   0.02561   0.01807  -0.0872   0.7315   1.0000
   4.250   0.7624   0.02459   0.01714  -0.0904   0.7273   1.0000
   4.500   0.7881   0.02459   0.01719  -0.0898   0.7166   1.0000
   4.750   0.8427   0.02341   0.01609  -0.0931   0.7116   1.0000
   5.000   0.8683   0.02335   0.01611  -0.0923   0.6997   1.0000
   5.250   0.9025   0.02295   0.01578  -0.0927   0.6892   1.0000
   5.500   0.9553   0.02184   0.01473  -0.0957   0.6810   1.0000
   5.750   0.9840   0.02159   0.01458  -0.0952   0.6672   1.0000
   6.000   1.0147   0.02127   0.01432  -0.0949   0.6529   1.0000
   6.250   1.0463   0.02093   0.01403  -0.0948   0.6376   1.0000
   6.500   1.0758   0.02067   0.01383  -0.0944   0.6208   1.0000
   6.750   1.0962   0.02069   0.01392  -0.0925   0.6016   1.0000
   7.000   1.1211   0.02056   0.01383  -0.0914   0.5814   1.0000
   7.250   1.1451   0.02050   0.01377  -0.0900   0.5598   1.0000
   7.500   1.1640   0.02058   0.01387  -0.0879   0.5358   1.0000
   7.750   1.1800   0.02076   0.01409  -0.0854   0.5100   1.0000
   8.000   1.1945   0.02102   0.01432  -0.0827   0.4824   1.0000
   8.250   1.2057   0.02139   0.01464  -0.0795   0.4525   1.0000
   8.500   1.2138   0.02189   0.01507  -0.0759   0.4213   1.0000
   8.750   1.2183   0.02251   0.01559  -0.0718   0.3899   1.0000
   9.000   1.2208   0.02332   0.01625  -0.0676   0.3576   1.0000
   9.250   1.2221   0.02433   0.01711  -0.0635   0.3253   1.0000
   9.500   1.2220   0.02551   0.01815  -0.0595   0.2929   1.0000
   9.750   1.2214   0.02687   0.01936  -0.0557   0.2618   1.0000
  10.000   1.2202   0.02841   0.02072  -0.0521   0.2325   1.0000
  10.250   1.2183   0.03008   0.02223  -0.0488   0.2055   1.0000
  10.500   1.2163   0.03190   0.02385  -0.0457   0.1816   1.0000
  10.750   1.2147   0.03376   0.02567  -0.0430   0.1578   1.0000
  11.000   1.2133   0.03584   0.02758  -0.0405   0.1382   1.0000
  11.250   1.2130   0.03796   0.02968  -0.0382   0.1196   1.0000
  11.500   1.2124   0.04026   0.03190  -0.0361   0.1036   1.0000
  11.750   1.2132   0.04267   0.03427  -0.0342   0.0897   1.0000
  12.000   1.2175   0.04508   0.03664  -0.0325   0.0780   1.0000
  12.250   1.2255   0.04743   0.03901  -0.0311   0.0687   1.0000
  12.500   1.2384   0.04967   0.04112  -0.0300   0.0616   1.0000
  12.750   1.2517   0.05190   0.04358  -0.0289   0.0568   1.0000
  13.000   1.2753   0.05410   0.04571  -0.0284   0.0527   1.0000
  13.250   1.2931   0.05715   0.04902  -0.0277   0.0501   1.0000
  13.500   1.2961   0.06002   0.05221  -0.0263   0.0482   1.0000
  13.750   1.2985   0.06297   0.05543  -0.0252   0.0464   1.0000
  14.000   1.2988   0.06600   0.05867  -0.0243   0.0448   1.0000
  14.250   1.2985   0.06948   0.06237  -0.0235   0.0439   1.0000
  14.500   1.2958   0.07333   0.06644  -0.0229   0.0433   1.0000
  14.750   1.2888   0.07761   0.07096  -0.0225   0.0429   1.0000
  15.000   1.2757   0.08232   0.07595  -0.0224   0.0428   1.0000
  15.250   1.2582   0.08746   0.08137  -0.0229   0.0428   1.0000
  15.500   1.2357   0.09327   0.08749  -0.0241   0.0430   1.0000
  15.750   1.2077   0.10011   0.09466  -0.0265   0.0434   1.0000
  16.000   1.1655   0.10974   0.10467  -0.0314   0.0444   1.0000
  16.250   1.1109   0.12330   0.11858  -0.0400   0.0462   1.0000
  16.500   1.0600   0.13903   0.13453  -0.0506   0.0483   1.0000
  16.750   1.0257   0.15337   0.14891  -0.0597   0.0503   1.0000
  17.000   1.0098   0.16374   0.15927  -0.0654   0.0513   1.0000
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