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E193 (10.22%) (e193-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E193 (10.22%) (e193-il)
Reynolds number: 50,000
Max Cl/Cd: 35.75 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e193-il-50000.txt
Download as CSV file: xf-e193-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3434   0.10442   0.09780  -0.0279   1.0000   0.2198
  -8.250  -0.3347   0.10065   0.09409  -0.0273   1.0000   0.2266
  -8.000  -0.3503   0.10000   0.09361  -0.0277   1.0000   0.2358
  -7.750  -0.3332   0.09566   0.08928  -0.0262   1.0000   0.2474
  -7.500  -0.3370   0.09320   0.08696  -0.0255   1.0000   0.2550
  -7.250  -0.3532   0.09242   0.08637  -0.0241   1.0000   0.2654
  -7.000  -0.3449   0.08909   0.08311  -0.0222   1.0000   0.2787
  -6.750  -0.3427   0.08631   0.08043  -0.0201   1.0000   0.2891
  -6.500  -0.3812   0.08703   0.08144  -0.0177   1.0000   0.2960
  -6.250  -0.3736   0.08391   0.07840  -0.0143   1.0000   0.3090
  -6.000  -0.3783   0.08173   0.07634  -0.0109   1.0000   0.3181
  -5.750  -0.4228   0.08295   0.07777  -0.0084   1.0000   0.3264
  -5.500  -0.4162   0.07996   0.07484  -0.0038   1.0000   0.3388
  -5.250  -0.4232   0.07806   0.07301  -0.0003   1.0000   0.3489
  -5.000  -0.4350   0.07649   0.07154   0.0027   1.0000   0.3626
  -4.000  -0.3697   0.04777   0.04075  -0.0404   1.0000   0.1316
  -3.750  -0.3449   0.04314   0.03544  -0.0422   1.0000   0.1204
  -3.500  -0.3222   0.04022   0.03203  -0.0426   1.0000   0.1165
  -3.250  -0.2995   0.03763   0.02895  -0.0429   1.0000   0.1153
  -3.000  -0.2756   0.03558   0.02626  -0.0429   1.0000   0.1179
  -2.750  -0.2546   0.03384   0.02435  -0.0427   1.0000   0.1230
  -2.500  -0.2266   0.03227   0.02239  -0.0431   0.9982   0.1293
  -2.250  -0.1844   0.03086   0.02057  -0.0458   0.9908   0.1482
  -2.000  -0.1435   0.02956   0.01941  -0.0484   0.9837   0.1962
  -1.750  -0.1061   0.02822   0.01852  -0.0502   0.9765   0.3085
  -1.500  -0.0744   0.02582   0.01813  -0.0496   0.9713   0.6283
  -1.250  -0.0258   0.02525   0.01751  -0.0531   0.9621   1.0000
  -1.000   0.0092   0.02599   0.01768  -0.0556   0.9535   1.0000
  -0.750   0.0478   0.02682   0.01803  -0.0586   0.9450   1.0000
  -0.500   0.0746   0.02748   0.01833  -0.0596   0.9361   1.0000
  -0.250   0.1114   0.02835   0.01885  -0.0623   0.9282   1.0000
   0.000   0.1372   0.02906   0.01930  -0.0631   0.9193   1.0000
   0.250   0.1671   0.02989   0.01988  -0.0646   0.9115   1.0000
   0.500   0.1958   0.03070   0.02049  -0.0658   0.9033   1.0000
   0.750   0.2205   0.03155   0.02116  -0.0664   0.8953   1.0000
   1.000   0.2519   0.03245   0.02189  -0.0681   0.8875   1.0000
   1.250   0.2717   0.03333   0.02264  -0.0679   0.8794   1.0000
   1.500   0.3052   0.03431   0.02349  -0.0699   0.8719   1.0000
   1.750   0.3203   0.03524   0.02434  -0.0691   0.8638   1.0000
   2.000   0.3565   0.03629   0.02530  -0.0713   0.8564   1.0000
   2.250   0.3667   0.03730   0.02626  -0.0699   0.8483   1.0000
   2.500   0.4012   0.03839   0.02730  -0.0719   0.8406   1.0000
   2.750   0.4118   0.03949   0.02837  -0.0705   0.8324   1.0000
   3.000   0.4403   0.04065   0.02951  -0.0716   0.8243   1.0000
   3.250   0.4573   0.04181   0.03067  -0.0713   0.8157   1.0000
   3.500   0.4779   0.04306   0.03192  -0.0713   0.8073   1.0000
   3.750   0.5082   0.04423   0.03311  -0.0726   0.7980   1.0000
   4.000   0.5178   0.04558   0.03450  -0.0713   0.7886   1.0000
   4.250   0.5434   0.04685   0.03581  -0.0719   0.7786   1.0000
   4.500   0.5744   0.04804   0.03707  -0.0730   0.7679   1.0000
   4.750   0.5821   0.04953   0.03860  -0.0716   0.7572   1.0000
   5.000   0.6016   0.05091   0.04005  -0.0715   0.7456   1.0000
   5.250   0.6257   0.05223   0.04149  -0.0717   0.7332   1.0000
   5.500   0.6514   0.05348   0.04285  -0.0719   0.7199   1.0000
   5.750   0.6759   0.05470   0.04420  -0.0719   0.7056   1.0000
   6.000   0.6981   0.05596   0.04558  -0.0716   0.6907   1.0000
   6.250   0.7180   0.05724   0.04702  -0.0710   0.6750   1.0000
   6.500   0.7373   0.05851   0.04844  -0.0703   0.6583   1.0000
   6.750   0.7608   0.05955   0.04964  -0.0697   0.6404   1.0000
   7.000   0.7971   0.05984   0.05016  -0.0694   0.6219   1.0000
   7.250   0.8267   0.06024   0.05082  -0.0685   0.6026   1.0000
   7.500   0.8424   0.06126   0.05202  -0.0669   0.5818   1.0000
   7.750   0.9185   0.05749   0.04878  -0.0662   0.5609   1.0000
   8.000   0.9157   0.05952   0.05092  -0.0636   0.5375   1.0000
   8.250   1.0020   0.05237   0.04442  -0.0604   0.5123   1.0000
   8.500   1.1577   0.03587   0.02876  -0.0576   0.4589   1.0000
   8.750   1.1785   0.03321   0.02603  -0.0524   0.3999   1.0000
   9.000   1.1805   0.03302   0.02535  -0.0466   0.3328   1.0000
   9.250   1.1737   0.03470   0.02632  -0.0414   0.2731   1.0000
   9.500   1.1628   0.03706   0.02821  -0.0366   0.2276   1.0000
   9.750   1.1527   0.03962   0.03025  -0.0326   0.1892   1.0000
  10.000   1.1468   0.04247   0.03291  -0.0294   0.1559   1.0000
  10.250   1.1585   0.04551   0.03563  -0.0274   0.1247   1.0000
  10.500   1.1933   0.04907   0.03913  -0.0272   0.1024   1.0000
  10.750   1.2263   0.05295   0.04320  -0.0276   0.0919   1.0000
  11.000   1.2449   0.05681   0.04747  -0.0267   0.0877   1.0000
  11.250   1.2659   0.06103   0.05187  -0.0264   0.0842   1.0000
  11.500   1.2742   0.06571   0.05679  -0.0254   0.0823   1.0000
  11.750   1.2629   0.06908   0.06055  -0.0224   0.0819   1.0000
  12.000   1.2478   0.07269   0.06449  -0.0197   0.0816   1.0000
  12.250   1.2313   0.07659   0.06869  -0.0178   0.0816   1.0000
  12.500   1.2130   0.08090   0.07326  -0.0167   0.0817   1.0000
  12.750   1.1936   0.08556   0.07815  -0.0164   0.0819   1.0000
  13.000   1.1744   0.09077   0.08356  -0.0168   0.0823   1.0000
  13.250   1.1568   0.09642   0.08937  -0.0179   0.0827   1.0000
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