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E193 (10.22%) (e193-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E193 (10.22%) (e193-il)
Reynolds number: 100,000
Max Cl/Cd: 58.85 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e193-il-100000-n5.txt
Download as CSV file: xf-e193-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3820   0.07812   0.07357  -0.0450   1.0000   0.0290
  -7.750  -0.3864   0.07570   0.07124  -0.0442   1.0000   0.0287
  -7.500  -0.3926   0.07269   0.06833  -0.0444   1.0000   0.0283
  -7.250  -0.4017   0.06971   0.06543  -0.0443   1.0000   0.0280
  -7.000  -0.3819   0.06284   0.05847  -0.0533   0.9880   0.0272
  -6.750  -0.3599   0.05485   0.05026  -0.0627   0.9742   0.0262
  -6.500  -0.3395   0.04651   0.04150  -0.0703   0.9600   0.0252
  -6.250  -0.3181   0.03953   0.03389  -0.0750   0.9465   0.0245
  -6.000  -0.2945   0.03430   0.02795  -0.0774   0.9336   0.0241
  -5.750  -0.2679   0.03063   0.02368  -0.0789   0.9218   0.0242
  -5.500  -0.2387   0.02783   0.02033  -0.0800   0.9113   0.0245
  -5.250  -0.2080   0.02565   0.01772  -0.0810   0.9014   0.0253
  -5.000  -0.1789   0.02404   0.01576  -0.0815   0.8897   0.0272
  -4.750  -0.1488   0.02256   0.01385  -0.0817   0.8788   0.0290
  -4.500  -0.1195   0.02102   0.01216  -0.0821   0.8688   0.0302
  -4.250  -0.0914   0.01992   0.01092  -0.0821   0.8578   0.0319
  -4.000  -0.0642   0.01900   0.00985  -0.0819   0.8464   0.0341
  -3.750  -0.0367   0.01819   0.00885  -0.0816   0.8360   0.0376
  -3.500  -0.0091   0.01744   0.00799  -0.0815   0.8265   0.0464
  -3.250   0.0165   0.01664   0.00721  -0.0810   0.8155   0.0650
  -3.000   0.0426   0.01594   0.00667  -0.0808   0.8060   0.1156
  -2.750   0.0685   0.01527   0.00639  -0.0807   0.7972   0.2063
  -2.500   0.0938   0.01483   0.00612  -0.0803   0.7874   0.2799
  -2.250   0.1198   0.01440   0.00590  -0.0799   0.7793   0.3676
  -2.000   0.1448   0.01398   0.00576  -0.0793   0.7704   0.4722
  -1.750   0.1683   0.01355   0.00567  -0.0782   0.7624   0.5916
  -1.500   0.1913   0.01313   0.00561  -0.0763   0.7547   0.7292
  -1.250   0.2395   0.01280   0.00546  -0.0792   0.7478   0.9053
  -1.000   0.2974   0.01272   0.00514  -0.0852   0.7405   0.9965
  -0.750   0.3239   0.01282   0.00504  -0.0851   0.7331   1.0000
  -0.500   0.3483   0.01293   0.00497  -0.0845   0.7255   1.0000
  -0.250   0.3729   0.01306   0.00493  -0.0839   0.7185   1.0000
   0.000   0.3976   0.01320   0.00493  -0.0833   0.7112   1.0000
   0.250   0.4228   0.01334   0.00493  -0.0828   0.7047   1.0000
   0.500   0.4475   0.01350   0.00499  -0.0822   0.6975   1.0000
   0.750   0.4734   0.01364   0.00500  -0.0818   0.6918   1.0000
   1.000   0.4980   0.01383   0.00514  -0.0812   0.6843   1.0000
   1.250   0.5240   0.01399   0.00519  -0.0808   0.6786   1.0000
   1.500   0.5488   0.01419   0.00536  -0.0803   0.6717   1.0000
   1.750   0.5745   0.01436   0.00548  -0.0799   0.6655   1.0000
   2.000   0.6000   0.01456   0.00564  -0.0795   0.6594   1.0000
   2.250   0.6252   0.01477   0.00585  -0.0791   0.6527   1.0000
   2.500   0.6517   0.01495   0.00598  -0.0787   0.6475   1.0000
   2.750   0.6762   0.01520   0.00627  -0.0782   0.6402   1.0000
   3.000   0.7024   0.01539   0.00644  -0.0778   0.6344   1.0000
   3.250   0.7272   0.01564   0.00675  -0.0774   0.6275   1.0000
   3.500   0.7529   0.01584   0.00698  -0.0769   0.6210   1.0000
   3.750   0.7780   0.01608   0.00725  -0.0765   0.6140   1.0000
   4.000   0.8032   0.01628   0.00753  -0.0760   0.6065   1.0000
   4.250   0.8281   0.01651   0.00781  -0.0754   0.5986   1.0000
   4.500   0.8535   0.01668   0.00803  -0.0749   0.5905   1.0000
   4.750   0.8774   0.01690   0.00835  -0.0741   0.5809   1.0000
   5.000   0.9027   0.01705   0.00857  -0.0735   0.5718   1.0000
   5.250   0.9269   0.01721   0.00882  -0.0727   0.5611   1.0000
   5.500   0.9503   0.01739   0.00911  -0.0719   0.5492   1.0000
   5.750   0.9738   0.01754   0.00937  -0.0710   0.5367   1.0000
   6.000   0.9971   0.01770   0.00966  -0.0700   0.5232   1.0000
   6.250   1.0199   0.01785   0.00992  -0.0690   0.5082   1.0000
   6.500   1.0422   0.01802   0.01020  -0.0679   0.4913   1.0000
   6.750   1.0641   0.01819   0.01045  -0.0666   0.4726   1.0000
   7.000   1.0843   0.01845   0.01085  -0.0652   0.4492   1.0000
   7.250   1.1034   0.01875   0.01120  -0.0636   0.4207   1.0000
   7.500   1.1205   0.01917   0.01159  -0.0618   0.3841   1.0000
   7.750   1.1325   0.01990   0.01208  -0.0592   0.3289   1.0000
   8.000   1.1383   0.02111   0.01289  -0.0561   0.2640   1.0000
   8.250   1.1404   0.02265   0.01405  -0.0528   0.2043   1.0000
   8.500   1.1421   0.02426   0.01530  -0.0496   0.1535   1.0000
   8.750   1.1436   0.02576   0.01654  -0.0465   0.1155   1.0000
   9.000   1.1459   0.02721   0.01783  -0.0435   0.0873   1.0000
   9.250   1.1486   0.02872   0.01926  -0.0407   0.0660   1.0000
   9.500   1.1495   0.03047   0.02092  -0.0380   0.0488   1.0000
   9.750   1.1506   0.03233   0.02277  -0.0356   0.0392   1.0000
  10.000   1.1517   0.03431   0.02481  -0.0335   0.0330   1.0000
  10.250   1.1531   0.03634   0.02689  -0.0318   0.0296   1.0000
  10.500   1.1550   0.03845   0.02914  -0.0302   0.0268   1.0000
  10.750   1.1581   0.04052   0.03134  -0.0290   0.0248   1.0000
  11.000   1.1601   0.04278   0.03371  -0.0279   0.0233   1.0000
  11.250   1.1606   0.04527   0.03631  -0.0269   0.0225   1.0000
  11.500   1.1611   0.04786   0.03899  -0.0260   0.0218   1.0000
  11.750   1.1643   0.05027   0.04158  -0.0252   0.0211   1.0000
  12.000   1.1681   0.05269   0.04416  -0.0244   0.0205   1.0000
  12.250   1.1725   0.05514   0.04676  -0.0236   0.0200   1.0000
  12.500   1.1775   0.05763   0.04940  -0.0229   0.0194   1.0000
  12.750   1.1826   0.06017   0.05212  -0.0223   0.0190   1.0000
  13.000   1.1874   0.06285   0.05496  -0.0217   0.0185   1.0000
  13.250   1.1907   0.06571   0.05797  -0.0215   0.0181   1.0000
  13.500   1.1927   0.06874   0.06114  -0.0214   0.0177   1.0000
  13.750   1.1929   0.07198   0.06449  -0.0215   0.0172   1.0000
  14.000   1.1918   0.07563   0.06829  -0.0218   0.0168   1.0000
  14.250   1.1891   0.07957   0.07248  -0.0223   0.0167   1.0000
  14.500   1.1808   0.08431   0.07753  -0.0236   0.0163   1.0000
  14.750   1.1727   0.08927   0.08274  -0.0250   0.0162   1.0000
  15.000   1.1619   0.09477   0.08851  -0.0271   0.0161   1.0000
  15.250   1.1493   0.10084   0.09482  -0.0297   0.0160   1.0000
  15.500   1.1361   0.10730   0.10150  -0.0329   0.0160   1.0000
  15.750   1.1207   0.11454   0.10897  -0.0368   0.0160   1.0000
  16.000   1.1040   0.12249   0.11713  -0.0414   0.0161   1.0000
  16.250   1.0867   0.13110   0.12593  -0.0467   0.0162   1.0000
  16.500   1.0682   0.14072   0.13571  -0.0528   0.0163   1.0000
  16.750   1.0505   0.15085   0.14597  -0.0592   0.0165   1.0000
  17.000   1.0359   0.16070   0.15589  -0.0653   0.0168   1.0000
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