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E193 (10.22%) (e193-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E193 (10.22%) (e193-il)
Reynolds number: 50,000
Max Cl/Cd: 35.91 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e193-il-50000-n5.txt
Download as CSV file: xf-e193-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3705   0.08879   0.08219  -0.0439   1.0000   0.0481
  -8.000  -0.3741   0.08570   0.07921  -0.0440   1.0000   0.0478
  -7.750  -0.3777   0.08261   0.07623  -0.0442   1.0000   0.0475
  -7.500  -0.3819   0.07921   0.07293  -0.0451   1.0000   0.0472
  -7.250  -0.3870   0.07577   0.06959  -0.0458   1.0000   0.0470
  -7.000  -0.3925   0.07253   0.06643  -0.0460   1.0000   0.0466
  -6.750  -0.3993   0.06944   0.06339  -0.0457   1.0000   0.0463
  -6.500  -0.4071   0.06641   0.06038  -0.0450   1.0000   0.0460
  -6.250  -0.4142   0.06343   0.05737  -0.0442   1.0000   0.0458
  -6.000  -0.3959   0.05791   0.05159  -0.0496   0.9912   0.0456
  -5.750  -0.3687   0.05196   0.04522  -0.0558   0.9794   0.0454
  -5.500  -0.3402   0.04670   0.03941  -0.0606   0.9684   0.0450
  -5.250  -0.3087   0.04201   0.03411  -0.0646   0.9588   0.0450
  -5.000  -0.2793   0.03821   0.02968  -0.0669   0.9480   0.0454
  -4.750  -0.2472   0.03493   0.02573  -0.0688   0.9385   0.0463
  -4.500  -0.2105   0.03221   0.02228  -0.0708   0.9308   0.0483
  -4.250  -0.1803   0.03047   0.02044  -0.0721   0.9209   0.0527
  -4.000  -0.1428   0.02867   0.01821  -0.0739   0.9141   0.0579
  -3.750  -0.1108   0.02707   0.01637  -0.0744   0.9049   0.0629
  -3.500  -0.0769   0.02583   0.01496  -0.0755   0.8970   0.0753
  -3.250  -0.0429   0.02464   0.01374  -0.0768   0.8888   0.1021
  -3.000  -0.0123   0.02355   0.01287  -0.0777   0.8798   0.1621
  -2.750   0.0206   0.02241   0.01207  -0.0790   0.8724   0.2526
  -2.500   0.0463   0.02161   0.01170  -0.0789   0.8627   0.3633
  -2.250   0.0746   0.02072   0.01135  -0.0785   0.8560   0.5163
  -2.000   0.0932   0.02008   0.01131  -0.0756   0.8461   0.6855
  -1.750   0.1790   0.01932   0.01055  -0.0850   0.8440   1.0000
  -1.500   0.2039   0.01947   0.01032  -0.0848   0.8339   1.0000
  -1.250   0.2346   0.01954   0.01003  -0.0854   0.8264   1.0000
  -1.000   0.2568   0.01979   0.01000  -0.0846   0.8160   1.0000
  -0.750   0.2832   0.01998   0.00991  -0.0845   0.8076   1.0000
  -0.500   0.3096   0.02018   0.00987  -0.0843   0.7993   1.0000
  -0.250   0.3340   0.02046   0.00995  -0.0839   0.7906   1.0000
   0.000   0.3620   0.02065   0.00993  -0.0839   0.7833   1.0000
   0.250   0.3849   0.02100   0.01013  -0.0832   0.7745   1.0000
   0.500   0.4134   0.02119   0.01017  -0.0833   0.7679   1.0000
   0.750   0.4353   0.02160   0.01047  -0.0825   0.7590   1.0000
   1.000   0.4639   0.02181   0.01056  -0.0825   0.7527   1.0000
   1.250   0.4852   0.02227   0.01095  -0.0817   0.7438   1.0000
   1.500   0.5136   0.02250   0.01109  -0.0817   0.7379   1.0000
   1.750   0.5343   0.02302   0.01158  -0.0808   0.7290   1.0000
   2.000   0.5626   0.02326   0.01176  -0.0808   0.7231   1.0000
   2.250   0.5829   0.02383   0.01233  -0.0799   0.7144   1.0000
   2.500   0.6109   0.02408   0.01258  -0.0797   0.7084   1.0000
   2.750   0.6308   0.02470   0.01322  -0.0788   0.6997   1.0000
   3.000   0.6586   0.02497   0.01350  -0.0787   0.6937   1.0000
   3.250   0.6781   0.02564   0.01421  -0.0777   0.6849   1.0000
   3.500   0.7059   0.02591   0.01454  -0.0775   0.6788   1.0000
   3.750   0.7246   0.02662   0.01533  -0.0764   0.6697   1.0000
   4.000   0.7532   0.02684   0.01561  -0.0762   0.6635   1.0000
   4.250   0.7709   0.02761   0.01647  -0.0750   0.6537   1.0000
   4.500   0.8015   0.02770   0.01667  -0.0750   0.6478   1.0000
   4.750   0.8179   0.02850   0.01760  -0.0736   0.6370   1.0000
   5.000   0.8399   0.02900   0.01823  -0.0727   0.6279   1.0000
   5.250   0.8673   0.02915   0.01854  -0.0721   0.6196   1.0000
   5.500   0.8855   0.02979   0.01933  -0.0708   0.6082   1.0000
   5.750   0.9078   0.03015   0.01985  -0.0696   0.5975   1.0000
   6.000   0.9375   0.03001   0.01986  -0.0690   0.5880   1.0000
   6.250   0.9588   0.03028   0.02035  -0.0677   0.5753   1.0000
   6.500   0.9796   0.03051   0.02077  -0.0662   0.5616   1.0000
   6.750   1.0016   0.03056   0.02103  -0.0646   0.5471   1.0000
   7.000   1.0248   0.03045   0.02111  -0.0631   0.5316   1.0000
   7.250   1.0453   0.03040   0.02130  -0.0612   0.5143   1.0000
   7.500   1.0603   0.03064   0.02176  -0.0589   0.4941   1.0000
   7.750   1.0818   0.03032   0.02161  -0.0568   0.4726   1.0000
   8.000   1.0933   0.03064   0.02214  -0.0541   0.4472   1.0000
   8.250   1.1063   0.03081   0.02244  -0.0513   0.4175   1.0000
   8.500   1.1162   0.03118   0.02291  -0.0484   0.3822   1.0000
   8.750   1.1227   0.03179   0.02344  -0.0451   0.3411   1.0000
   9.000   1.1234   0.03287   0.02432  -0.0414   0.2975   1.0000
   9.250   1.1201   0.03455   0.02571  -0.0381   0.2572   1.0000
   9.500   1.1147   0.03672   0.02768  -0.0353   0.2214   1.0000
   9.750   1.1083   0.03926   0.03001  -0.0330   0.1906   1.0000
  10.000   1.1005   0.04216   0.03270  -0.0313   0.1617   1.0000
  10.250   1.0935   0.04523   0.03560  -0.0301   0.1355   1.0000
  10.500   1.0865   0.04852   0.03871  -0.0293   0.1107   1.0000
  10.750   1.0807   0.05186   0.04188  -0.0287   0.0931   1.0000
  11.000   1.0772   0.05514   0.04513  -0.0280   0.0780   1.0000
  11.250   1.0743   0.05843   0.04836  -0.0275   0.0682   1.0000
  11.500   1.0750   0.06143   0.05148  -0.0268   0.0601   1.0000
  11.750   1.0762   0.06444   0.05457  -0.0262   0.0535   1.0000
  12.000   1.0785   0.06735   0.05754  -0.0258   0.0490   1.0000
  12.250   1.0839   0.07003   0.06032  -0.0250   0.0455   1.0000
  12.500   1.0940   0.07245   0.06301  -0.0239   0.0425   1.0000
  12.750   1.1033   0.07501   0.06577  -0.0230   0.0403   1.0000
  13.000   1.1120   0.07769   0.06857  -0.0223   0.0386   1.0000
  13.250   1.1205   0.08067   0.07168  -0.0217   0.0372   1.0000
  13.500   1.1190   0.08495   0.07634  -0.0221   0.0363   1.0000
  13.750   1.1132   0.08978   0.08150  -0.0231   0.0356   1.0000
  14.000   1.1030   0.09528   0.08731  -0.0249   0.0351   1.0000
  14.250   1.0912   0.10122   0.09356  -0.0272   0.0349   1.0000
  14.500   1.0759   0.10801   0.10056  -0.0304   0.0348   1.0000
  14.750   1.0590   0.11558   0.10835  -0.0344   0.0350   1.0000
  15.000   1.0413   0.12391   0.11687  -0.0391   0.0353   1.0000
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