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E195 (11.82%) (e195-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E195 (11.82%) (e195-il)
Reynolds number: 50,000
Max Cl/Cd: 32.84 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e195-il-50000.txt
Download as CSV file: xf-e195-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E195  (11.82%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2643   0.11050   0.10419  -0.0313   1.0000   0.2356
  -9.750  -0.2529   0.10686   0.10057  -0.0308   1.0000   0.2444
  -9.500  -0.2608   0.10434   0.09814  -0.0313   1.0000   0.2505
  -9.250  -0.2505   0.10081   0.09462  -0.0307   1.0000   0.2599
  -9.000  -0.2541   0.09784   0.09175  -0.0306   1.0000   0.2663
  -8.750  -0.2543   0.09524   0.08922  -0.0300   1.0000   0.2766
  -8.500  -0.3491   0.10175   0.09528  -0.0273   1.0000   0.2780
  -8.250  -0.3277   0.09694   0.09045  -0.0263   1.0000   0.2863
  -8.000  -0.3378   0.09502   0.08867  -0.0259   1.0000   0.2955
  -7.750  -0.3449   0.09330   0.08709  -0.0248   1.0000   0.3075
  -7.500  -0.3290   0.08937   0.08319  -0.0234   1.0000   0.3184
  -7.250  -0.3305   0.08693   0.08087  -0.0217   1.0000   0.3296
  -7.000  -0.3727   0.08786   0.08211  -0.0181   1.0000   0.3381
  -6.750  -0.3670   0.08503   0.07937  -0.0153   1.0000   0.3521
  -6.500  -0.3594   0.08199   0.07640  -0.0127   1.0000   0.3612
  -6.250  -0.4104   0.08372   0.07841  -0.0056   1.0000   0.3671
  -5.750  -0.5102   0.06138   0.05538  -0.0353   1.0000   0.1447
  -5.500  -0.5057   0.05554   0.04909  -0.0367   1.0000   0.1299
  -5.250  -0.4965   0.05207   0.04551  -0.0361   1.0000   0.1256
  -5.000  -0.4835   0.04662   0.03898  -0.0377   1.0000   0.1162
  -4.750  -0.4677   0.04352   0.03552  -0.0374   1.0000   0.1154
  -4.500  -0.4499   0.04086   0.03229  -0.0372   1.0000   0.1161
  -4.250  -0.4319   0.03846   0.02967  -0.0368   1.0000   0.1191
  -4.000  -0.4126   0.03654   0.02748  -0.0362   1.0000   0.1222
  -3.750  -0.3916   0.03464   0.02516  -0.0356   1.0000   0.1257
  -3.500  -0.3694   0.03304   0.02299  -0.0348   1.0000   0.1313
  -3.250  -0.3446   0.03174   0.02157  -0.0349   0.9983   0.1457
  -3.000  -0.3062   0.03026   0.02018  -0.0371   0.9914   0.1765
  -2.750  -0.2691   0.02895   0.01929  -0.0392   0.9846   0.2627
  -2.500  -0.2393   0.02764   0.01892  -0.0396   0.9781   0.4114
  -2.250  -0.2139   0.02697   0.01927  -0.0378   0.9716   0.6049
  -2.000  -0.2022   0.02651   0.01944  -0.0328   0.9644   0.7520
  -1.750  -0.1094   0.02672   0.01942  -0.0445   0.9572   1.0000
  -1.500  -0.0845   0.02703   0.01920  -0.0464   0.9484   1.0000
  -1.250  -0.0496   0.02772   0.01939  -0.0494   0.9408   1.0000
  -1.000  -0.0226   0.02831   0.01962  -0.0507   0.9328   1.0000
  -0.750   0.0084   0.02906   0.02002  -0.0526   0.9254   1.0000
  -0.500   0.0345   0.02974   0.02042  -0.0536   0.9178   1.0000
  -0.250   0.0634   0.03054   0.02094  -0.0551   0.9107   1.0000
   0.000   0.0877   0.03128   0.02146  -0.0557   0.9032   1.0000
   0.250   0.1161   0.03215   0.02212  -0.0570   0.8965   1.0000
   0.500   0.1369   0.03293   0.02272  -0.0571   0.8891   1.0000
   0.750   0.1673   0.03389   0.02351  -0.0586   0.8824   1.0000
   1.000   0.1833   0.03472   0.02421  -0.0580   0.8755   1.0000
   1.250   0.2177   0.03577   0.02512  -0.0601   0.8686   1.0000
   1.500   0.2280   0.03664   0.02589  -0.0587   0.8621   1.0000
   1.750   0.2609   0.03773   0.02688  -0.0606   0.8551   1.0000
   2.000   0.2718   0.03872   0.02780  -0.0593   0.8488   1.0000
   2.250   0.2975   0.03982   0.02884  -0.0602   0.8419   1.0000
   2.500   0.3149   0.04095   0.02991  -0.0599   0.8353   1.0000
   2.750   0.3345   0.04210   0.03102  -0.0599   0.8286   1.0000
   3.000   0.3569   0.04334   0.03223  -0.0603   0.8214   1.0000
   3.250   0.3719   0.04455   0.03343  -0.0599   0.8148   1.0000
   3.500   0.3965   0.04587   0.03473  -0.0606   0.8067   1.0000
   3.750   0.4107   0.04716   0.03603  -0.0600   0.7996   1.0000
   4.000   0.4330   0.04854   0.03742  -0.0604   0.7912   1.0000
   4.250   0.4541   0.04989   0.03882  -0.0607   0.7824   1.0000
   4.500   0.4674   0.05133   0.04028  -0.0601   0.7739   1.0000
   4.750   0.4970   0.05276   0.04176  -0.0612   0.7632   1.0000
   5.000   0.5090   0.05423   0.04328  -0.0605   0.7537   1.0000
   5.250   0.5250   0.05573   0.04484  -0.0602   0.7426   1.0000
   5.500   0.5475   0.05720   0.04640  -0.0604   0.7302   1.0000
   5.750   0.5712   0.05861   0.04790  -0.0606   0.7165   1.0000
   6.000   0.5943   0.06003   0.04941  -0.0607   0.7023   1.0000
   6.250   0.6157   0.06144   0.05093  -0.0606   0.6874   1.0000
   6.500   0.6351   0.06283   0.05246  -0.0601   0.6715   1.0000
   6.750   0.6545   0.06422   0.05397  -0.0597   0.6550   1.0000
   7.000   0.6756   0.06554   0.05542  -0.0592   0.6380   1.0000
   7.250   0.7046   0.06648   0.05652  -0.0590   0.6197   1.0000
   7.500   0.7448   0.06677   0.05707  -0.0590   0.6009   1.0000
   7.750   0.7491   0.06857   0.05898  -0.0574   0.5822   1.0000
   8.000   0.7737   0.06926   0.05986  -0.0564   0.5622   1.0000
   8.250   0.8201   0.06826   0.05918  -0.0554   0.5417   1.0000
   8.500   0.8256   0.06987   0.06093  -0.0537   0.5204   1.0000
   8.750   0.8926   0.06590   0.05739  -0.0516   0.4984   1.0000
   9.000   0.9029   0.06664   0.05834  -0.0493   0.4749   1.0000
   9.250   1.1543   0.03742   0.03038  -0.0432   0.4098   1.0000
   9.500   1.1697   0.03562   0.02826  -0.0381   0.3513   1.0000
   9.750   1.1700   0.03623   0.02826  -0.0331   0.2977   1.0000
  10.000   1.1645   0.03820   0.02978  -0.0286   0.2539   1.0000
  10.250   1.1592   0.04063   0.03188  -0.0249   0.2167   1.0000
  10.500   1.1566   0.04317   0.03399  -0.0219   0.1832   1.0000
  10.750   1.1537   0.04585   0.03642  -0.0193   0.1554   1.0000
  11.000   1.1605   0.04874   0.03904  -0.0174   0.1288   1.0000
  11.250   1.1751   0.05193   0.04236  -0.0160   0.1109   1.0000
  11.500   1.1942   0.05528   0.04581  -0.0150   0.0982   1.0000
  11.750   1.2246   0.05927   0.04982  -0.0152   0.0894   1.0000
  12.000   1.2208   0.06291   0.05394  -0.0131   0.0875   1.0000
  12.250   1.2146   0.06678   0.05820  -0.0113   0.0863   1.0000
  12.500   1.2027   0.07085   0.06261  -0.0098   0.0854   1.0000
  12.750   1.1872   0.07521   0.06729  -0.0089   0.0853   1.0000
  13.000   1.1670   0.07998   0.07234  -0.0086   0.0854   1.0000
  13.250   1.1440   0.08533   0.07796  -0.0092   0.0860   1.0000
  13.500   1.1188   0.09131   0.08416  -0.0107   0.0868   1.0000
  13.750   1.0922   0.09802   0.09105  -0.0130   0.0877   1.0000
  14.000   1.0687   0.10509   0.09826  -0.0160   0.0888   1.0000
  14.250   1.0459   0.11275   0.10602  -0.0195   0.0897   1.0000
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