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E193 (10.22%) (e193-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E193 (10.22%) (e193-il)
Reynolds number: 100,000
Max Cl/Cd: 58.66 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e193-il-100000.txt
Download as CSV file: xf-e193-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E193  (10.22%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3411   0.09300   0.08834  -0.0363   1.0000   0.1010
  -8.000  -0.3586   0.09119   0.08670  -0.0385   1.0000   0.1034
  -7.750  -0.3809   0.08950   0.08519  -0.0404   1.0000   0.1040
  -7.500  -0.3658   0.08525   0.08095  -0.0364   1.0000   0.1073
  -7.250  -0.3627   0.08303   0.07880  -0.0341   1.0000   0.1112
  -7.000  -0.3768   0.08122   0.07713  -0.0331   1.0000   0.1146
  -6.750  -0.3646   0.07076   0.06722  -0.0362   0.9894   0.1197
  -6.500  -0.3307   0.06677   0.06323  -0.0323   0.9866   0.1254
  -6.250  -0.4367   0.07536   0.07148  -0.0359   0.9969   0.1198
  -6.000  -0.4087   0.07231   0.06850  -0.0337   0.9920   0.1247
  -5.750  -0.3765   0.06602   0.06205  -0.0454   0.9815   0.1362
  -5.500  -0.3422   0.06076   0.05660  -0.0544   0.9725   0.1498
  -5.250  -0.3123   0.05656   0.05222  -0.0602   0.9619   0.1640
  -5.000  -0.2814   0.05307   0.04870  -0.0624   0.9542   0.1727
  -4.750  -0.2325   0.03475   0.02783  -0.0743   0.9457   0.0639
  -4.500  -0.2010   0.03125   0.02401  -0.0758   0.9371   0.0617
  -4.250  -0.1601   0.02814   0.02030  -0.0785   0.9313   0.0614
  -4.000  -0.1257   0.02622   0.01783  -0.0796   0.9228   0.0641
  -3.750  -0.0838   0.02381   0.01525  -0.0822   0.9175   0.0675
  -3.500  -0.0476   0.02233   0.01359  -0.0835   0.9101   0.0729
  -3.250  -0.0098   0.02085   0.01209  -0.0850   0.9035   0.0859
  -3.000   0.0217   0.01937   0.01082  -0.0855   0.8957   0.1287
  -2.750   0.0535   0.01806   0.01013  -0.0865   0.8884   0.2529
  -2.500   0.0787   0.01703   0.00981  -0.0861   0.8797   0.4060
  -2.250   0.1060   0.01601   0.00960  -0.0853   0.8730   0.6151
  -2.000   0.1815   0.01497   0.00917  -0.0915   0.8719   0.9539
  -1.750   0.2423   0.01483   0.00864  -0.0983   0.8648   1.0000
  -1.500   0.2716   0.01482   0.00834  -0.0986   0.8569   1.0000
  -1.250   0.2919   0.01506   0.00836  -0.0975   0.8461   1.0000
  -1.000   0.3171   0.01521   0.00830  -0.0970   0.8377   1.0000
  -0.750   0.3416   0.01537   0.00829  -0.0963   0.8291   1.0000
  -0.500   0.3636   0.01565   0.00842  -0.0954   0.8201   1.0000
  -0.250   0.3905   0.01578   0.00838  -0.0950   0.8130   1.0000
   0.000   0.4114   0.01614   0.00864  -0.0939   0.8037   1.0000
   0.250   0.4392   0.01626   0.00861  -0.0936   0.7975   1.0000
   0.500   0.4594   0.01670   0.00898  -0.0925   0.7882   1.0000
   0.750   0.4876   0.01682   0.00898  -0.0923   0.7823   1.0000
   1.000   0.5076   0.01730   0.00943  -0.0912   0.7730   1.0000
   1.250   0.5360   0.01744   0.00947  -0.0910   0.7675   1.0000
   1.500   0.5559   0.01798   0.01000  -0.0899   0.7582   1.0000
   1.750   0.5843   0.01812   0.01007  -0.0897   0.7528   1.0000
   2.000   0.6041   0.01871   0.01067  -0.0887   0.7437   1.0000
   2.250   0.6326   0.01885   0.01076  -0.0884   0.7382   1.0000
   2.500   0.6522   0.01948   0.01144  -0.0875   0.7291   1.0000
   2.750   0.6810   0.01961   0.01153  -0.0872   0.7235   1.0000
   3.000   0.7004   0.02027   0.01224  -0.0862   0.7142   1.0000
   3.250   0.7297   0.02036   0.01231  -0.0860   0.7086   1.0000
   3.500   0.7489   0.02101   0.01306  -0.0849   0.6989   1.0000
   3.750   0.7794   0.02101   0.01305  -0.0847   0.6933   1.0000
   4.000   0.7984   0.02165   0.01378  -0.0835   0.6828   1.0000
   4.250   0.8233   0.02194   0.01413  -0.0828   0.6747   1.0000
   4.500   0.8497   0.02208   0.01433  -0.0821   0.6661   1.0000
   4.750   0.8715   0.02248   0.01484  -0.0811   0.6558   1.0000
   5.000   0.9022   0.02230   0.01467  -0.0806   0.6481   1.0000
   5.250   0.9251   0.02251   0.01502  -0.0795   0.6368   1.0000
   5.500   0.9485   0.02267   0.01528  -0.0784   0.6251   1.0000
   5.750   0.9744   0.02260   0.01530  -0.0774   0.6136   1.0000
   6.000   1.0026   0.02234   0.01510  -0.0765   0.6021   1.0000
   6.250   1.0313   0.02197   0.01481  -0.0757   0.5897   1.0000
   6.500   1.0571   0.02171   0.01466  -0.0745   0.5753   1.0000
   6.750   1.0798   0.02155   0.01464  -0.0730   0.5588   1.0000
   7.000   1.1024   0.02130   0.01455  -0.0713   0.5403   1.0000
   7.250   1.1267   0.02084   0.01419  -0.0697   0.5201   1.0000
   7.500   1.1473   0.02054   0.01402  -0.0677   0.4959   1.0000
   7.750   1.1657   0.02022   0.01378  -0.0653   0.4642   1.0000
   8.000   1.1790   0.02010   0.01361  -0.0622   0.4173   1.0000
   8.250   1.1845   0.02064   0.01387  -0.0583   0.3469   1.0000
   8.500   1.1833   0.02201   0.01472  -0.0540   0.2701   1.0000
   8.750   1.1793   0.02381   0.01607  -0.0498   0.2090   1.0000
   9.000   1.1711   0.02580   0.01767  -0.0453   0.1588   1.0000
   9.250   1.1589   0.02813   0.01963  -0.0405   0.1178   1.0000
   9.500   1.1461   0.03086   0.02206  -0.0363   0.0875   1.0000
   9.750   1.1380   0.03354   0.02455  -0.0330   0.0717   1.0000
  10.000   1.1396   0.03576   0.02676  -0.0306   0.0619   1.0000
  10.250   1.1464   0.03789   0.02886  -0.0286   0.0558   1.0000
  10.500   1.1564   0.03977   0.03073  -0.0271   0.0503   1.0000
  10.750   1.1836   0.04200   0.03294  -0.0260   0.0468   1.0000
  11.000   1.2127   0.04423   0.03539  -0.0254   0.0446   1.0000
  11.250   1.2412   0.04705   0.03847  -0.0250   0.0429   1.0000
  11.500   1.2613   0.05014   0.04185  -0.0243   0.0420   1.0000
  11.750   1.2723   0.05326   0.04526  -0.0230   0.0414   1.0000
  12.000   1.2774   0.05606   0.04825  -0.0216   0.0401   1.0000
  12.250   1.2804   0.05937   0.05179  -0.0203   0.0392   1.0000
  12.500   1.2793   0.06327   0.05593  -0.0190   0.0387   1.0000
  12.750   1.2706   0.06691   0.05986  -0.0175   0.0387   1.0000
  13.000   1.2574   0.07060   0.06387  -0.0162   0.0389   1.0000
  13.250   1.2394   0.07468   0.06828  -0.0155   0.0393   1.0000
  13.500   1.2153   0.07964   0.07359  -0.0157   0.0399   1.0000
  13.750   1.1824   0.08586   0.08017  -0.0173   0.0406   1.0000
  14.000   1.1505   0.09297   0.08756  -0.0201   0.0413   1.0000
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