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E193 (10.22%) (e193-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E193 (10.22%) (e193-il)
Reynolds number: 200,000
Max Cl/Cd: 82.26 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e193-il-200000.txt
Download as CSV file: xf-e193-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3614   0.08676   0.08353  -0.0434   1.0000   0.0506
  -8.000  -0.3770   0.08405   0.08093  -0.0447   1.0000   0.0508
  -7.750  -0.3878   0.08060   0.07755  -0.0474   1.0000   0.0510
  -7.500  -0.4030   0.07795   0.07494  -0.0471   1.0000   0.0511
  -7.250  -0.4069   0.07226   0.06931  -0.0484   0.9971   0.0518
  -7.000  -0.3841   0.06969   0.06679  -0.0472   0.9933   0.0533
  -6.750  -0.3549   0.06554   0.06258  -0.0527   0.9865   0.0554
  -6.500  -0.3166   0.05666   0.05330  -0.0702   0.9740   0.0628
  -6.250  -0.2941   0.04938   0.04582  -0.0768   0.9636   0.0652
  -6.000  -0.2606   0.04613   0.04257  -0.0803   0.9588   0.0675
  -5.750  -0.2318   0.04099   0.03675  -0.0863   0.9458   0.0779
  -5.500  -0.2068   0.02920   0.02370  -0.0872   0.9337   0.0406
  -5.250  -0.1764   0.02623   0.02043  -0.0883   0.9233   0.0392
  -5.000  -0.1477   0.02250   0.01623  -0.0890   0.9133   0.0370
  -4.750  -0.1192   0.01998   0.01324  -0.0888   0.9016   0.0356
  -4.500  -0.0916   0.01824   0.01114  -0.0883   0.8888   0.0354
  -4.250  -0.0644   0.01692   0.00959  -0.0878   0.8763   0.0360
  -4.000  -0.0378   0.01587   0.00838  -0.0871   0.8643   0.0375
  -3.750  -0.0112   0.01514   0.00747  -0.0864   0.8530   0.0398
  -3.500   0.0133   0.01419   0.00650  -0.0857   0.8420   0.0456
  -3.250   0.0381   0.01349   0.00572  -0.0849   0.8303   0.0532
  -3.000   0.0620   0.01242   0.00490  -0.0840   0.8201   0.1132
  -2.750   0.0870   0.01187   0.00462  -0.0836   0.8111   0.2000
  -2.500   0.1109   0.01138   0.00449  -0.0831   0.8008   0.3059
  -2.250   0.1340   0.01087   0.00442  -0.0823   0.7920   0.4360
  -2.000   0.1568   0.01044   0.00435  -0.0812   0.7837   0.5579
  -1.750   0.1771   0.01000   0.00435  -0.0792   0.7750   0.6970
  -1.500   0.2062   0.00961   0.00436  -0.0781   0.7682   0.8754
  -1.250   0.2760   0.00955   0.00417  -0.0862   0.7606   0.9837
  -1.000   0.3211   0.00956   0.00395  -0.0900   0.7535   1.0000
  -0.750   0.3445   0.00966   0.00393  -0.0892   0.7453   1.0000
  -0.500   0.3690   0.00977   0.00387  -0.0886   0.7385   1.0000
  -0.250   0.3930   0.00989   0.00389  -0.0879   0.7307   1.0000
   0.000   0.4180   0.01002   0.00388  -0.0873   0.7243   1.0000
   0.250   0.4423   0.01016   0.00394  -0.0867   0.7170   1.0000
   0.500   0.4675   0.01029   0.00397  -0.0861   0.7105   1.0000
   0.750   0.4924   0.01045   0.00406  -0.0855   0.7040   1.0000
   1.000   0.5176   0.01059   0.00413  -0.0850   0.6973   1.0000
   1.250   0.5433   0.01076   0.00422  -0.0846   0.6915   1.0000
   1.500   0.5682   0.01091   0.00436  -0.0840   0.6845   1.0000
   1.750   0.5946   0.01108   0.00443  -0.0837   0.6791   1.0000
   2.000   0.6194   0.01125   0.00463  -0.0832   0.6720   1.0000
   2.250   0.6456   0.01141   0.00475  -0.0828   0.6661   1.0000
   2.500   0.6711   0.01160   0.00493  -0.0824   0.6597   1.0000
   2.750   0.6969   0.01176   0.00508  -0.0819   0.6530   1.0000
   3.000   0.7232   0.01194   0.00523  -0.0816   0.6470   1.0000
   3.250   0.7484   0.01210   0.00544  -0.0811   0.6393   1.0000
   3.500   0.7750   0.01226   0.00556  -0.0808   0.6329   1.0000
   3.750   0.7999   0.01240   0.00576  -0.0802   0.6245   1.0000
   4.000   0.8261   0.01254   0.00588  -0.0798   0.6172   1.0000
   4.250   0.8514   0.01265   0.00606  -0.0792   0.6084   1.0000
   4.500   0.8768   0.01278   0.00622  -0.0787   0.5998   1.0000
   4.750   0.9030   0.01286   0.00628  -0.0782   0.5910   1.0000
   5.000   0.9274   0.01296   0.00649  -0.0775   0.5808   1.0000
   5.250   0.9527   0.01305   0.00663  -0.0769   0.5710   1.0000
   5.500   0.9785   0.01312   0.00668  -0.0763   0.5610   1.0000
   5.750   1.0024   0.01318   0.00686  -0.0755   0.5488   1.0000
   6.000   1.0265   0.01325   0.00702  -0.0747   0.5360   1.0000
   6.250   1.0502   0.01330   0.00715  -0.0737   0.5215   1.0000
   6.500   1.0733   0.01335   0.00723  -0.0727   0.5043   1.0000
   6.750   1.0948   0.01340   0.00735  -0.0713   0.4799   1.0000
   7.000   1.1146   0.01355   0.00747  -0.0697   0.4477   1.0000
   7.250   1.1327   0.01387   0.00771  -0.0680   0.4052   1.0000
   7.500   1.1476   0.01448   0.00811  -0.0658   0.3494   1.0000
   7.750   1.1563   0.01557   0.00880  -0.0629   0.2780   1.0000
   8.000   1.1633   0.01688   0.00973  -0.0600   0.2154   1.0000
   8.250   1.1696   0.01825   0.01079  -0.0571   0.1601   1.0000
   8.500   1.1735   0.01974   0.01195  -0.0539   0.1085   1.0000
   8.750   1.1683   0.02167   0.01346  -0.0494   0.0574   1.0000
   9.000   1.1628   0.02353   0.01517  -0.0448   0.0392   1.0000
   9.250   1.1653   0.02497   0.01670  -0.0416   0.0342   1.0000
   9.500   1.1679   0.02649   0.01828  -0.0388   0.0313   1.0000
  10.000   1.1688   0.03026   0.02221  -0.0337   0.0282   1.0000
  10.250   1.1746   0.03194   0.02402  -0.0319   0.0271   1.0000
  10.500   1.1810   0.03368   0.02583  -0.0303   0.0257   1.0000
  10.750   1.1881   0.03538   0.02759  -0.0289   0.0243   1.0000
  11.000   1.1947   0.03729   0.02953  -0.0276   0.0233   1.0000
  11.250   1.2061   0.03957   0.03182  -0.0259   0.0224   1.0000
  11.500   1.2230   0.04147   0.03384  -0.0246   0.0220   1.0000
  11.750   1.2402   0.04341   0.03593  -0.0236   0.0218   1.0000
  12.000   1.2543   0.04563   0.03836  -0.0225   0.0215   1.0000
  12.250   1.2670   0.04821   0.04121  -0.0214   0.0214   1.0000
  12.500   1.2748   0.05117   0.04443  -0.0202   0.0213   1.0000
  12.750   1.2785   0.05448   0.04801  -0.0192   0.0214   1.0000
  13.000   1.2771   0.05815   0.05195  -0.0181   0.0215   1.0000
  13.250   1.2723   0.06222   0.05628  -0.0174   0.0217   1.0000
  13.500   1.2649   0.06679   0.06110  -0.0169   0.0219   1.0000
  13.750   1.2592   0.07203   0.06658  -0.0167   0.0223   1.0000
  14.000   1.2494   0.07548   0.07022  -0.0168   0.0224   1.0000
  14.250   1.2371   0.07934   0.07431  -0.0174   0.0226   1.0000
  14.500   1.2205   0.08425   0.07944  -0.0187   0.0227   1.0000
  14.750   1.2024   0.08955   0.08498  -0.0206   0.0229   1.0000
  15.000   1.1650   0.09824   0.09408  -0.0250   0.0238   1.0000
  15.250   1.1183   0.11032   0.10654  -0.0322   0.0247   1.0000
  15.500   1.0857   0.12136   0.11779  -0.0393   0.0252   1.0000
  15.750   1.0503   0.13481   0.13140  -0.0484   0.0256   1.0000
  16.000   1.0023   0.15558   0.15228  -0.0616   0.0270   1.0000
  16.250   0.9891   0.16590   0.16257  -0.0669   0.0285   1.0000
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