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E193 (10.22%) (e193-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: E193 (10.22%) (e193-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.53 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e193-il-1000000-n5.txt
Download as CSV file: xf-e193-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3867   0.08730   0.08569  -0.0368   1.0000   0.0059
  -9.250  -0.3840   0.08220   0.08059  -0.0405   0.9857   0.0058
  -8.750  -0.5101   0.02641   0.02339  -0.0853   0.8537   0.0052
  -8.500  -0.5013   0.02313   0.01962  -0.0843   0.8298   0.0053
  -8.250  -0.4859   0.02096   0.01706  -0.0834   0.8099   0.0055
  -8.000  -0.4675   0.01921   0.01496  -0.0826   0.7927   0.0056
  -7.750  -0.4467   0.01786   0.01332  -0.0820   0.7777   0.0058
  -7.500  -0.4242   0.01682   0.01204  -0.0814   0.7637   0.0059
  -7.250  -0.4010   0.01589   0.01089  -0.0809   0.7506   0.0061
  -7.000  -0.3767   0.01515   0.00996  -0.0805   0.7387   0.0062
  -6.750  -0.3519   0.01449   0.00915  -0.0801   0.7280   0.0063
  -6.500  -0.3267   0.01392   0.00841  -0.0798   0.7179   0.0064
  -6.000  -0.2763   0.01264   0.00685  -0.0791   0.6990   0.0065
  -5.750  -0.2517   0.01181   0.00587  -0.0786   0.6909   0.0067
  -5.500  -0.2259   0.01129   0.00525  -0.0783   0.6826   0.0069
  -5.250  -0.1997   0.01087   0.00473  -0.0781   0.6751   0.0071
  -5.000  -0.1730   0.01055   0.00435  -0.0779   0.6678   0.0073
  -4.750  -0.1463   0.01026   0.00400  -0.0777   0.6609   0.0077
  -4.500  -0.1193   0.00998   0.00366  -0.0776   0.6542   0.0080
  -4.000  -0.0652   0.00943   0.00297  -0.0772   0.6419   0.0086
  -3.750  -0.0380   0.00921   0.00268  -0.0771   0.6357   0.0089
  -3.500  -0.0105   0.00903   0.00245  -0.0770   0.6303   0.0092
  -3.250   0.0169   0.00882   0.00219  -0.0769   0.6247   0.0096
  -3.000   0.0443   0.00863   0.00194  -0.0767   0.6192   0.0103
  -2.750   0.0719   0.00849   0.00176  -0.0767   0.6141   0.0111
  -2.500   0.0997   0.00837   0.00160  -0.0766   0.6087   0.0121
  -2.000   0.1546   0.00802   0.00133  -0.0765   0.5989   0.0402
  -1.750   0.1821   0.00786   0.00123  -0.0764   0.5938   0.0629
  -1.250   0.2370   0.00755   0.00109  -0.0764   0.5844   0.1302
  -1.000   0.2643   0.00736   0.00104  -0.0764   0.5793   0.1795
  -0.750   0.2913   0.00718   0.00101  -0.0763   0.5746   0.2391
  -0.500   0.3187   0.00700   0.00099  -0.0763   0.5701   0.2979
  -0.250   0.3459   0.00681   0.00098  -0.0763   0.5651   0.3646
   0.000   0.3729   0.00667   0.00098  -0.0762   0.5603   0.4268
   0.250   0.4003   0.00655   0.00099  -0.0762   0.5558   0.4778
   0.500   0.4274   0.00641   0.00101  -0.0761   0.5507   0.5424
   0.750   0.4539   0.00625   0.00105  -0.0759   0.5458   0.6182
   1.000   0.4803   0.00608   0.00108  -0.0756   0.5413   0.6944
   1.250   0.5057   0.00590   0.00113  -0.0751   0.5359   0.7756
   1.500   0.5290   0.00571   0.00120  -0.0739   0.5304   0.8666
   1.750   0.5611   0.00561   0.00127  -0.0746   0.5238   0.9610
   2.500   0.6700   0.00584   0.00139  -0.0803   0.4981   1.0000
   2.750   0.6956   0.00594   0.00145  -0.0799   0.4890   1.0000
   3.000   0.7213   0.00603   0.00152  -0.0795   0.4796   1.0000
   3.250   0.7468   0.00615   0.00160  -0.0790   0.4688   1.0000
   3.500   0.7723   0.00628   0.00168  -0.0786   0.4570   1.0000
   3.750   0.7980   0.00641   0.00178  -0.0781   0.4444   1.0000
   4.000   0.8235   0.00656   0.00189  -0.0777   0.4303   1.0000
   4.250   0.8484   0.00677   0.00202  -0.0772   0.4084   1.0000
   4.500   0.8715   0.00714   0.00221  -0.0764   0.3696   1.0000
   4.750   0.8946   0.00752   0.00244  -0.0757   0.3324   1.0000
   5.000   0.9151   0.00815   0.00278  -0.0746   0.2745   1.0000
   5.250   0.9337   0.00894   0.00322  -0.0732   0.2066   1.0000
   5.500   0.9539   0.00959   0.00362  -0.0721   0.1579   1.0000
   5.750   0.9747   0.01018   0.00401  -0.0711   0.1190   1.0000
   6.000   0.9961   0.01070   0.00438  -0.0701   0.0884   1.0000
   6.250   1.0180   0.01118   0.00475  -0.0692   0.0662   1.0000
   6.500   1.0382   0.01177   0.00519  -0.0681   0.0400   1.0000
   6.750   1.0590   0.01230   0.00564  -0.0671   0.0231   1.0000
   7.000   1.0789   0.01290   0.00615  -0.0659   0.0091   1.0000
   7.250   1.1013   0.01327   0.00653  -0.0651   0.0079   1.0000
   7.500   1.1232   0.01367   0.00696  -0.0642   0.0067   1.0000
   7.750   1.1451   0.01405   0.00736  -0.0633   0.0064   1.0000
   8.000   1.1667   0.01443   0.00779  -0.0624   0.0061   1.0000
   8.250   1.1877   0.01484   0.00823  -0.0615   0.0058   1.0000
   8.500   1.2077   0.01529   0.00872  -0.0603   0.0055   1.0000
   8.750   1.2272   0.01575   0.00922  -0.0591   0.0053   1.0000
   9.000   1.2455   0.01626   0.00978  -0.0577   0.0052   1.0000
   9.250   1.2627   0.01681   0.01038  -0.0562   0.0050   1.0000
   9.500   1.2771   0.01739   0.01100  -0.0542   0.0048   1.0000
   9.750   1.2889   0.01802   0.01169  -0.0517   0.0047   1.0000
  10.000   1.2986   0.01878   0.01251  -0.0490   0.0045   1.0000
  10.250   1.3060   0.01970   0.01351  -0.0462   0.0044   1.0000
  10.500   1.3148   0.02059   0.01447  -0.0437   0.0043   1.0000
  10.750   1.3254   0.02141   0.01536  -0.0417   0.0042   1.0000
  11.000   1.3342   0.02239   0.01641  -0.0396   0.0042   1.0000
  11.250   1.3440   0.02336   0.01745  -0.0378   0.0041   1.0000
  11.500   1.3542   0.02436   0.01851  -0.0363   0.0040   1.0000
  11.750   1.3585   0.02585   0.02009  -0.0343   0.0040   1.0000
  12.000   1.3689   0.02695   0.02125  -0.0331   0.0039   1.0000
  12.250   1.3759   0.02838   0.02276  -0.0317   0.0038   1.0000
  12.500   1.3803   0.03011   0.02458  -0.0304   0.0037   1.0000
  12.750   1.3864   0.03176   0.02632  -0.0293   0.0036   1.0000
  13.000   1.3902   0.03370   0.02835  -0.0283   0.0036   1.0000
  13.250   1.3947   0.03565   0.03038  -0.0275   0.0035   1.0000
  13.500   1.3962   0.03795   0.03278  -0.0267   0.0035   1.0000
  13.750   1.3992   0.04018   0.03510  -0.0262   0.0034   1.0000
  14.000   1.4002   0.04268   0.03769  -0.0257   0.0033   1.0000
  14.250   1.4004   0.04533   0.04045  -0.0254   0.0034   1.0000
  14.500   1.4034   0.04775   0.04294  -0.0253   0.0033   1.0000
  14.750   1.3998   0.05101   0.04632  -0.0252   0.0033   1.0000
  15.000   1.4026   0.05361   0.04900  -0.0254   0.0032   1.0000
  15.250   1.3995   0.05704   0.05254  -0.0257   0.0032   1.0000
  15.500   1.3980   0.06037   0.05598  -0.0262   0.0032   1.0000
  15.750   1.3941   0.06415   0.05987  -0.0269   0.0031   1.0000
  16.000   1.3887   0.06828   0.06411  -0.0279   0.0031   1.0000
  16.250   1.3845   0.07236   0.06830  -0.0290   0.0031   1.0000
  16.500   1.3818   0.07636   0.07239  -0.0303   0.0030   1.0000
  16.750   1.3747   0.08115   0.07730  -0.0319   0.0030   1.0000
  17.000   1.3664   0.08631   0.08259  -0.0338   0.0031   1.0000
  17.250   1.3605   0.09121   0.08760  -0.0358   0.0030   1.0000
  17.500   1.3538   0.09638   0.09287  -0.0380   0.0030   1.0000
  17.750   1.3403   0.10292   0.09956  -0.0409   0.0030   1.0000
  18.000   1.3333   0.10847   0.10521  -0.0436   0.0030   1.0000
  18.250   1.3224   0.11483   0.11170  -0.0467   0.0030   1.0000
  18.500   1.3111   0.12147   0.11846  -0.0501   0.0030   1.0000
  18.750   1.3014   0.12796   0.12506  -0.0536   0.0029   1.0000
  19.000   1.2900   0.13492   0.13214  -0.0575   0.0029   1.0000
  19.250   1.2795   0.14182   0.13915  -0.0615   0.0029   1.0000
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