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E193 (10.22%) (e193-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: E193 (10.22%) (e193-il)
Reynolds number: 1,000,000
Max Cl/Cd: 138.85 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e193-il-1000000.txt
Download as CSV file: xf-e193-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3841   0.11650   0.11480  -0.0282   1.0000   0.0099
 -11.000  -0.3878   0.11131   0.10963  -0.0296   1.0000   0.0102
 -10.750  -0.3841   0.10815   0.10648  -0.0305   1.0000   0.0103
 -10.500  -0.3764   0.10627   0.10461  -0.0307   1.0000   0.0106
 -10.250  -0.3733   0.10294   0.10128  -0.0318   1.0000   0.0107
 -10.000  -0.3703   0.09962   0.09798  -0.0330   1.0000   0.0108
  -9.750  -0.3666   0.09665   0.09503  -0.0339   1.0000   0.0111
  -6.750  -0.3061   0.02784   0.02483  -0.0871   0.8468   0.0149
  -6.500  -0.2894   0.02573   0.02242  -0.0864   0.8260   0.0155
  -6.250  -0.2878   0.01550   0.01069  -0.0827   0.8092   0.0105
  -6.000  -0.2645   0.01421   0.00912  -0.0819   0.7938   0.0105
  -5.750  -0.2405   0.01326   0.00801  -0.0813   0.7794   0.0109
  -5.500  -0.2156   0.01255   0.00715  -0.0809   0.7661   0.0112
  -5.250  -0.1901   0.01195   0.00641  -0.0804   0.7537   0.0115
  -5.000  -0.1644   0.01138   0.00574  -0.0800   0.7423   0.0118
  -4.750  -0.1385   0.01085   0.00510  -0.0796   0.7318   0.0121
  -4.500  -0.1126   0.01037   0.00450  -0.0792   0.7220   0.0123
  -4.250  -0.0862   0.00994   0.00398  -0.0789   0.7126   0.0125
  -4.000  -0.0595   0.00963   0.00359  -0.0786   0.7041   0.0130
  -3.750  -0.0326   0.00939   0.00326  -0.0784   0.6957   0.0134
  -3.500  -0.0061   0.00893   0.00271  -0.0781   0.6882   0.0139
  -3.250   0.0207   0.00860   0.00229  -0.0778   0.6807   0.0150
  -3.000   0.0481   0.00839   0.00203  -0.0777   0.6738   0.0165
  -2.750   0.0756   0.00825   0.00182  -0.0776   0.6669   0.0179
  -2.500   0.1027   0.00795   0.00158  -0.0774   0.6608   0.0388
  -2.250   0.1295   0.00763   0.00144  -0.0773   0.6543   0.0890
  -2.000   0.1562   0.00739   0.00135  -0.0771   0.6484   0.1416
  -1.750   0.1836   0.00719   0.00127  -0.0771   0.6426   0.1883
  -1.500   0.2106   0.00699   0.00121  -0.0771   0.6369   0.2441
  -1.250   0.2377   0.00679   0.00118  -0.0770   0.6315   0.3080
  -1.000   0.2643   0.00649   0.00115  -0.0769   0.6259   0.4038
  -0.750   0.2907   0.00628   0.00114  -0.0767   0.6207   0.4899
  -0.500   0.3175   0.00607   0.00114  -0.0766   0.6155   0.5666
  -0.250   0.3425   0.00574   0.00117  -0.0760   0.6102   0.6894
   0.000   0.3659   0.00547   0.00120  -0.0750   0.6052   0.8054
   0.250   0.3888   0.00520   0.00127  -0.0735   0.6004   0.9218
   0.500   0.4305   0.00522   0.00129  -0.0764   0.5949   0.9758
   0.750   0.4739   0.00529   0.00129  -0.0798   0.5896   0.9912
   1.000   0.5166   0.00531   0.00128  -0.0831   0.5841   0.9987
   1.250   0.5462   0.00536   0.00129  -0.0835   0.5787   1.0000
   1.500   0.5717   0.00543   0.00132  -0.0830   0.5732   1.0000
   1.750   0.5974   0.00547   0.00135  -0.0826   0.5670   1.0000
   2.000   0.6227   0.00557   0.00138  -0.0820   0.5607   1.0000
   2.250   0.6488   0.00560   0.00143  -0.0816   0.5540   1.0000
   2.500   0.6743   0.00569   0.00147  -0.0811   0.5471   1.0000
   2.750   0.7004   0.00575   0.00152  -0.0808   0.5403   1.0000
   3.000   0.7260   0.00584   0.00158  -0.0803   0.5330   1.0000
   3.250   0.7522   0.00591   0.00165  -0.0800   0.5252   1.0000
   3.500   0.7778   0.00602   0.00172  -0.0795   0.5173   1.0000
   3.750   0.8042   0.00608   0.00179  -0.0792   0.5090   1.0000
   4.000   0.8302   0.00619   0.00188  -0.0789   0.5004   1.0000
   4.250   0.8562   0.00630   0.00198  -0.0785   0.4906   1.0000
   4.500   0.8825   0.00640   0.00208  -0.0783   0.4808   1.0000
   4.750   0.9081   0.00654   0.00219  -0.0779   0.4656   1.0000
   5.000   0.9330   0.00675   0.00232  -0.0773   0.4430   1.0000
   5.250   0.9573   0.00702   0.00248  -0.0768   0.4144   1.0000
   5.500   0.9810   0.00735   0.00268  -0.0761   0.3811   1.0000
   5.750   1.0020   0.00790   0.00299  -0.0751   0.3280   1.0000
   6.000   1.0220   0.00857   0.00339  -0.0739   0.2724   1.0000
   6.250   1.0408   0.00932   0.00385  -0.0726   0.2149   1.0000
   6.500   1.0605   0.00999   0.00429  -0.0714   0.1691   1.0000
   6.750   1.0799   0.01067   0.00476  -0.0702   0.1285   1.0000
   7.000   1.0979   0.01143   0.00529  -0.0688   0.0871   1.0000
   7.250   1.1146   0.01229   0.00590  -0.0671   0.0484   1.0000
   7.500   1.1297   0.01323   0.00662  -0.0652   0.0164   1.0000
   7.750   1.1495   0.01379   0.00717  -0.0640   0.0114   1.0000
   8.000   1.1698   0.01428   0.00770  -0.0628   0.0102   1.0000
   8.250   1.1884   0.01488   0.00835  -0.0614   0.0092   1.0000
   8.500   1.2075   0.01540   0.00893  -0.0601   0.0089   1.0000
   8.750   1.2262   0.01592   0.00950  -0.0587   0.0086   1.0000
   9.000   1.2433   0.01651   0.01015  -0.0571   0.0084   1.0000
   9.250   1.2591   0.01712   0.01082  -0.0553   0.0080   1.0000
   9.500   1.2711   0.01776   0.01152  -0.0528   0.0078   1.0000
   9.750   1.2812   0.01848   0.01231  -0.0501   0.0076   1.0000
  10.000   1.2904   0.01928   0.01316  -0.0474   0.0073   1.0000
  10.250   1.2984   0.02018   0.01414  -0.0447   0.0072   1.0000
  10.500   1.3036   0.02130   0.01533  -0.0419   0.0070   1.0000
  10.750   1.3038   0.02282   0.01694  -0.0388   0.0068   1.0000
  11.000   1.2995   0.02479   0.01903  -0.0357   0.0065   1.0000
  11.250   1.3006   0.02657   0.02091  -0.0334   0.0064   1.0000
  11.500   1.3065   0.02809   0.02251  -0.0318   0.0064   1.0000
  11.750   1.3110   0.02980   0.02430  -0.0302   0.0064   1.0000
  12.000   1.3196   0.03123   0.02581  -0.0291   0.0063   1.0000
  12.250   1.3262   0.03289   0.02755  -0.0281   0.0062   1.0000
  12.500   1.3293   0.03496   0.02972  -0.0269   0.0062   1.0000
  12.750   1.3346   0.03686   0.03170  -0.0260   0.0061   1.0000
  13.000   1.3363   0.03921   0.03415  -0.0249   0.0061   1.0000
  13.250   1.3406   0.04133   0.03637  -0.0242   0.0060   1.0000
  13.500   1.3427   0.04376   0.03891  -0.0235   0.0060   1.0000
  13.750   1.3455   0.04617   0.04141  -0.0230   0.0060   1.0000
  14.000   1.3465   0.04882   0.04419  -0.0225   0.0060   1.0000
  14.250   1.3471   0.05161   0.04710  -0.0222   0.0059   1.0000
  14.500   1.3479   0.05443   0.05004  -0.0223   0.0058   1.0000
  14.750   1.3475   0.05747   0.05320  -0.0224   0.0057   1.0000
  15.000   1.3442   0.06104   0.05690  -0.0226   0.0056   1.0000
  15.250   1.3408   0.06473   0.06072  -0.0231   0.0056   1.0000
  15.500   1.3349   0.06889   0.06504  -0.0239   0.0057   1.0000
  15.750   1.3283   0.07331   0.06961  -0.0250   0.0056   1.0000
  16.000   1.3215   0.07792   0.07436  -0.0264   0.0056   1.0000
  16.250   1.3104   0.08341   0.08002  -0.0282   0.0057   1.0000
  16.500   1.3014   0.08875   0.08550  -0.0304   0.0056   1.0000
  16.750   1.2948   0.09388   0.09073  -0.0328   0.0054   1.0000
  17.000   1.2774   0.10119   0.09825  -0.0360   0.0055   1.0000
  17.250   1.2598   0.10887   0.10610  -0.0398   0.0056   1.0000
  17.500   1.2443   0.11647   0.11387  -0.0439   0.0056   1.0000
  17.750   1.2276   0.12465   0.12220  -0.0485   0.0057   1.0000
  18.000   1.2142   0.13242   0.13011  -0.0532   0.0055   1.0000
  18.250   1.1933   0.14229   0.14015  -0.0592   0.0057   1.0000
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