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E180 (8.59%) (e180-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E180 (8.59%) (e180-il)
Reynolds number: 50,000
Max Cl/Cd: 35.47 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e180-il-50000.txt
Download as CSV file: xf-e180-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4757   0.09610   0.09000   0.0049   1.0000   0.2496
  -7.500  -0.4691   0.09272   0.08669   0.0050   1.0000   0.2653
  -7.250  -0.4645   0.08953   0.08358   0.0049   1.0000   0.2826
  -7.000  -0.4620   0.08652   0.08065   0.0047   1.0000   0.2982
  -6.750  -0.4693   0.08427   0.07853   0.0038   1.0000   0.3152
  -6.500  -0.4561   0.08019   0.07451   0.0049   1.0000   0.3331
  -6.250  -0.3557   0.06384   0.05863   0.0007   1.0000   0.3635
  -6.000  -0.3537   0.06045   0.05529   0.0014   1.0000   0.3839
  -5.750  -0.4338   0.07054   0.06509   0.0075   1.0000   0.4039
  -5.250  -0.4138   0.04851   0.04143  -0.0354   1.0000   0.1329
  -5.000  -0.4010   0.04391   0.03649  -0.0348   1.0000   0.1198
  -4.750  -0.3906   0.04090   0.03334  -0.0330   1.0000   0.1150
  -4.500  -0.3816   0.03792   0.02997  -0.0311   1.0000   0.1104
  -4.250  -0.3695   0.03511   0.02631  -0.0291   1.0000   0.1057
  -4.000  -0.3555   0.03275   0.02358  -0.0274   1.0000   0.1060
  -3.750  -0.3409   0.03089   0.02168  -0.0259   1.0000   0.1125
  -3.500  -0.3225   0.02911   0.01931  -0.0244   1.0000   0.1183
  -3.250  -0.3030   0.02712   0.01718  -0.0232   1.0000   0.1258
  -3.000  -0.2830   0.02566   0.01550  -0.0220   1.0000   0.1442
  -2.750  -0.2609   0.02408   0.01389  -0.0210   1.0000   0.1757
  -2.500  -0.2374   0.02244   0.01256  -0.0202   1.0000   0.2392
  -2.250  -0.1610   0.01750   0.01061  -0.0248   1.0000   1.0000
  -2.000  -0.1486   0.01772   0.01028  -0.0233   1.0000   1.0000
  -1.750  -0.1349   0.01798   0.01004  -0.0220   1.0000   1.0000
  -1.500  -0.1202   0.01827   0.00995  -0.0209   1.0000   1.0000
  -1.250  -0.1046   0.01860   0.00993  -0.0199   1.0000   1.0000
  -1.000  -0.0884   0.01895   0.00998  -0.0191   1.0000   1.0000
  -0.750  -0.0599   0.01948   0.01018  -0.0207   0.9956   1.0000
  -0.500  -0.0181   0.02020   0.01054  -0.0247   0.9857   1.0000
  -0.250   0.0208   0.02091   0.01098  -0.0282   0.9759   1.0000
   0.000   0.0600   0.02165   0.01150  -0.0316   0.9664   1.0000
   0.250   0.1004   0.02244   0.01207  -0.0351   0.9570   1.0000
   0.500   0.1321   0.02313   0.01262  -0.0371   0.9469   1.0000
   0.750   0.1652   0.02389   0.01326  -0.0393   0.9375   1.0000
   1.000   0.2040   0.02472   0.01398  -0.0424   0.9280   1.0000
   1.250   0.2321   0.02547   0.01467  -0.0436   0.9180   1.0000
   1.500   0.2599   0.02628   0.01542  -0.0447   0.9082   1.0000
   1.750   0.2930   0.02714   0.01627  -0.0467   0.8985   1.0000
   2.000   0.3258   0.02801   0.01714  -0.0486   0.8883   1.0000
   2.250   0.3483   0.02888   0.01801  -0.0487   0.8775   1.0000
   2.500   0.3746   0.02979   0.01895  -0.0494   0.8666   1.0000
   2.750   0.4045   0.03073   0.01994  -0.0507   0.8553   1.0000
   3.000   0.4372   0.03166   0.02099  -0.0522   0.8435   1.0000
   3.250   0.4716   0.03258   0.02202  -0.0539   0.8310   1.0000
   3.500   0.5013   0.03350   0.02305  -0.0548   0.8175   1.0000
   3.750   0.5312   0.03440   0.02408  -0.0555   0.8030   1.0000
   4.000   0.5536   0.03535   0.02521  -0.0550   0.7873   1.0000
   4.250   0.5767   0.03629   0.02630  -0.0546   0.7705   1.0000
   4.500   0.6063   0.03704   0.02724  -0.0545   0.7523   1.0000
   4.750   0.6487   0.03726   0.02774  -0.0550   0.7336   1.0000
   5.000   0.6673   0.03806   0.02877  -0.0533   0.7120   1.0000
   5.250   0.7125   0.03739   0.02844  -0.0522   0.6908   1.0000
   5.500   0.7357   0.03747   0.02877  -0.0497   0.6656   1.0000
   5.750   0.7662   0.03667   0.02826  -0.0466   0.6393   1.0000
   6.000   0.7997   0.03497   0.02694  -0.0424   0.6110   1.0000
   6.250   0.8352   0.03220   0.02448  -0.0370   0.5798   1.0000
   6.500   0.8648   0.02917   0.02170  -0.0310   0.5379   1.0000
   6.750   0.8879   0.02607   0.01872  -0.0245   0.4700   1.0000
   7.000   0.8945   0.02522   0.01699  -0.0180   0.3340   1.0000
   7.250   0.8906   0.02827   0.01868  -0.0141   0.2194   1.0000
   7.500   0.8984   0.03160   0.02134  -0.0113   0.1545   1.0000
   7.750   0.9195   0.03430   0.02365  -0.0098   0.1239   1.0000
   8.000   0.9513   0.03744   0.02666  -0.0089   0.1097   1.0000
   8.250   0.9761   0.04048   0.03024  -0.0076   0.1032   1.0000
   8.500   0.9998   0.04396   0.03369  -0.0071   0.0964   1.0000
   8.750   1.0131   0.04718   0.03762  -0.0055   0.0927   1.0000
   9.000   1.0252   0.05107   0.04209  -0.0042   0.0912   1.0000
   9.250   1.0324   0.05537   0.04690  -0.0029   0.0913   1.0000
   9.500   1.0344   0.05992   0.05190  -0.0017   0.0920   1.0000
   9.750   1.0316   0.06457   0.05693  -0.0007   0.0932   1.0000
  10.000   1.0254   0.06933   0.06198   0.0001   0.0944   1.0000
  10.250   1.0212   0.07433   0.06717   0.0005   0.0957   1.0000
  10.500   1.0081   0.07893   0.07201   0.0009   0.0974   1.0000
  10.750   0.9582   0.08347   0.07677  -0.0006   0.0991   1.0000
  11.000   0.9083   0.09183   0.08515  -0.0071   0.1020   1.0000
  11.250   0.8783   0.10121   0.09450  -0.0136   0.1057   1.0000
  11.500   0.8734   0.10798   0.10125  -0.0161   0.1085   1.0000
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