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E180 (8.59%) (e180-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E180 (8.59%) (e180-il)
Reynolds number: 50,000
Max Cl/Cd: 36.19 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e180-il-50000-n5.txt
Download as CSV file: xf-e180-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E180  (8.59%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5024   0.09449   0.08812  -0.0097   1.0000   0.0415
  -8.250  -0.4981   0.09050   0.08419  -0.0112   1.0000   0.0407
  -8.000  -0.4960   0.08632   0.08008  -0.0135   1.0000   0.0399
  -7.750  -0.4951   0.08201   0.07584  -0.0166   1.0000   0.0393
  -7.500  -0.4920   0.07734   0.07121  -0.0203   1.0000   0.0385
  -7.250  -0.4884   0.07229   0.06616  -0.0240   1.0000   0.0378
  -7.000  -0.4835   0.06726   0.06109  -0.0274   1.0000   0.0371
  -6.750  -0.4771   0.06226   0.05599  -0.0303   1.0000   0.0366
  -6.500  -0.4691   0.05737   0.05093  -0.0327   1.0000   0.0366
  -6.250  -0.4589   0.05276   0.04607  -0.0344   1.0000   0.0369
  -6.000  -0.4467   0.04842   0.04140  -0.0355   1.0000   0.0377
  -5.750  -0.4327   0.04446   0.03701  -0.0360   1.0000   0.0384
  -5.500  -0.4177   0.04079   0.03288  -0.0359   1.0000   0.0394
  -5.250  -0.4025   0.03760   0.02924  -0.0351   1.0000   0.0401
  -5.000  -0.3889   0.03482   0.02602  -0.0336   1.0000   0.0406
  -4.750  -0.3763   0.03251   0.02327  -0.0315   1.0000   0.0413
  -4.500  -0.3594   0.03039   0.02067  -0.0301   0.9973   0.0422
  -4.250  -0.3231   0.02772   0.01775  -0.0323   0.9839   0.0454
  -4.000  -0.2844   0.02596   0.01555  -0.0344   0.9719   0.0545
  -3.750  -0.2471   0.02415   0.01352  -0.0362   0.9608   0.0660
  -3.500  -0.2096   0.02264   0.01194  -0.0382   0.9498   0.0929
  -3.250  -0.1727   0.02116   0.01060  -0.0403   0.9392   0.1490
  -3.000  -0.1394   0.01970   0.00965  -0.0419   0.9284   0.2508
  -2.750  -0.1134   0.01836   0.00919  -0.0420   0.9167   0.4375
  -2.500  -0.0885   0.01718   0.00905  -0.0397   0.9066   0.7096
  -2.250   0.0245   0.01650   0.00806  -0.0539   0.9109   1.0000
  -2.000   0.0531   0.01659   0.00774  -0.0545   0.8970   1.0000
  -1.750   0.0799   0.01671   0.00749  -0.0546   0.8839   1.0000
  -1.500   0.1056   0.01687   0.00733  -0.0545   0.8719   1.0000
  -1.250   0.1303   0.01704   0.00724  -0.0540   0.8604   1.0000
  -1.000   0.1538   0.01725   0.00722  -0.0535   0.8489   1.0000
  -0.750   0.1773   0.01747   0.00721  -0.0528   0.8381   1.0000
  -0.500   0.2011   0.01770   0.00725  -0.0521   0.8284   1.0000
  -0.250   0.2249   0.01793   0.00732  -0.0514   0.8190   1.0000
   0.000   0.2480   0.01820   0.00746  -0.0507   0.8090   1.0000
   0.250   0.2716   0.01848   0.00760  -0.0500   0.8001   1.0000
   0.500   0.2954   0.01874   0.00777  -0.0493   0.7915   1.0000
   0.750   0.3187   0.01907   0.00802  -0.0487   0.7821   1.0000
   1.000   0.3427   0.01935   0.00823  -0.0480   0.7742   1.0000
   1.250   0.3663   0.01969   0.00854  -0.0473   0.7652   1.0000
   1.500   0.3902   0.02004   0.00887  -0.0468   0.7566   1.0000
   1.750   0.4148   0.02033   0.00914  -0.0461   0.7489   1.0000
   2.000   0.4384   0.02074   0.00958  -0.0456   0.7395   1.0000
   2.250   0.4627   0.02107   0.00995  -0.0449   0.7316   1.0000
   2.500   0.4865   0.02145   0.01037  -0.0443   0.7226   1.0000
   2.750   0.5100   0.02186   0.01085  -0.0437   0.7132   1.0000
   3.000   0.5347   0.02214   0.01117  -0.0427   0.7052   1.0000
   3.250   0.5578   0.02256   0.01173  -0.0420   0.6946   1.0000
   3.500   0.5810   0.02295   0.01224  -0.0412   0.6839   1.0000
   3.750   0.6047   0.02326   0.01266  -0.0403   0.6734   1.0000
   4.000   0.6291   0.02345   0.01295  -0.0390   0.6630   1.0000
   4.250   0.6524   0.02370   0.01339  -0.0379   0.6504   1.0000
   4.500   0.6756   0.02390   0.01376  -0.0366   0.6368   1.0000
   4.750   0.6990   0.02402   0.01404  -0.0352   0.6224   1.0000
   5.000   0.7220   0.02412   0.01433  -0.0338   0.6062   1.0000
   5.250   0.7443   0.02422   0.01464  -0.0323   0.5871   1.0000
   5.500   0.7678   0.02404   0.01472  -0.0304   0.5675   1.0000
   5.750   0.7897   0.02397   0.01489  -0.0287   0.5431   1.0000
   6.000   0.8116   0.02381   0.01493  -0.0267   0.5147   1.0000
   6.250   0.8326   0.02368   0.01500  -0.0247   0.4786   1.0000
   6.500   0.8522   0.02361   0.01500  -0.0224   0.4274   1.0000
   6.750   0.8679   0.02398   0.01514  -0.0199   0.3468   1.0000
   7.000   0.8760   0.02551   0.01594  -0.0174   0.2490   1.0000
   7.250   0.8794   0.02793   0.01772  -0.0157   0.1639   1.0000
   7.500   0.8840   0.03032   0.01963  -0.0141   0.1097   1.0000
   7.750   0.8906   0.03253   0.02163  -0.0125   0.0829   1.0000
   8.000   0.8986   0.03461   0.02368  -0.0107   0.0688   1.0000
   8.250   0.9073   0.03665   0.02570  -0.0090   0.0613   1.0000
   8.500   0.9225   0.03846   0.02773  -0.0073   0.0558   1.0000
   8.750   0.9403   0.04036   0.02971  -0.0058   0.0518   1.0000
   9.000   0.9637   0.04247   0.03203  -0.0047   0.0479   1.0000
   9.250   0.9829   0.04463   0.03452  -0.0036   0.0437   1.0000
   9.500   0.9990   0.04698   0.03706  -0.0027   0.0409   1.0000
   9.750   1.0163   0.04999   0.04032  -0.0019   0.0394   1.0000
  10.000   1.0290   0.05356   0.04419  -0.0010   0.0385   1.0000
  10.250   1.0334   0.05705   0.04812   0.0003   0.0380   1.0000
  10.500   1.0309   0.06065   0.05211   0.0016   0.0377   1.0000
  10.750   1.0231   0.06428   0.05606   0.0028   0.0376   1.0000
  11.000   1.0118   0.06820   0.06025   0.0032   0.0375   1.0000
  11.250   0.9977   0.07254   0.06484   0.0027   0.0375   1.0000
  11.500   0.9817   0.07737   0.06989   0.0014   0.0375   1.0000
  11.750   0.9654   0.08260   0.07530  -0.0008   0.0377   1.0000
  12.000   0.9468   0.08865   0.08150  -0.0039   0.0379   1.0000
  12.250   0.9286   0.09520   0.08817  -0.0076   0.0381   1.0000
  12.500   0.9113   0.10233   0.09538  -0.0119   0.0383   1.0000
  12.750   0.8956   0.10988   0.10299  -0.0165   0.0386   1.0000
  13.000   0.8737   0.12026   0.11346  -0.0235   0.0394   1.0000
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