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E178 (8.69%) (e178-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E178 (8.69%) (e178-il)
Reynolds number: 100,000
Max Cl/Cd: 55.81 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e178-il-100000-n5.txt
Download as CSV file: xf-e178-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E178  (8.69%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3799   0.07709   0.07293  -0.0228   1.0000   0.0300
  -8.000  -0.4552   0.08207   0.07773  -0.0250   1.0000   0.0308
  -7.750  -0.4483   0.07900   0.07466  -0.0243   1.0000   0.0291
  -7.500  -0.4453   0.07459   0.07029  -0.0275   1.0000   0.0285
  -7.250  -0.4410   0.06966   0.06539  -0.0316   1.0000   0.0278
  -7.000  -0.4351   0.06444   0.06015  -0.0358   1.0000   0.0272
  -6.750  -0.4278   0.05888   0.05452  -0.0397   1.0000   0.0267
  -6.500  -0.4193   0.05327   0.04877  -0.0429   1.0000   0.0261
  -6.250  -0.4106   0.04793   0.04323  -0.0450   1.0000   0.0258
  -6.000  -0.3896   0.04177   0.03664  -0.0488   0.9785   0.0257
  -5.750  -0.3603   0.03617   0.03042  -0.0526   0.9569   0.0265
  -5.500  -0.3301   0.03213   0.02559  -0.0547   0.9387   0.0294
  -5.250  -0.3017   0.02886   0.02165  -0.0556   0.9220   0.0299
  -5.000  -0.2742   0.02629   0.01848  -0.0558   0.9065   0.0303
  -4.750  -0.2485   0.02369   0.01546  -0.0556   0.8922   0.0312
  -4.500  -0.2230   0.02192   0.01342  -0.0552   0.8788   0.0326
  -4.250  -0.1974   0.02072   0.01195  -0.0546   0.8660   0.0346
  -4.000  -0.1718   0.01995   0.01096  -0.0541   0.8540   0.0394
  -3.750  -0.1462   0.01897   0.00975  -0.0532   0.8432   0.0415
  -3.500  -0.1214   0.01803   0.00866  -0.0524   0.8328   0.0430
  -3.250  -0.0968   0.01718   0.00772  -0.0517   0.8222   0.0461
  -3.000  -0.0714   0.01657   0.00697  -0.0510   0.8125   0.0517
  -2.750  -0.0461   0.01592   0.00625  -0.0503   0.8040   0.0654
  -2.500  -0.0209   0.01523   0.00569  -0.0498   0.7945   0.1137
  -2.250   0.0032   0.01441   0.00544  -0.0495   0.7861   0.2439
  -2.000   0.0253   0.01335   0.00531  -0.0487   0.7784   0.4728
  -1.750   0.0462   0.01261   0.00524  -0.0467   0.7700   0.6705
  -1.500   0.0934   0.01203   0.00502  -0.0488   0.7640   0.9152
  -1.250   0.1475   0.01195   0.00468  -0.0541   0.7561   1.0000
  -1.000   0.1719   0.01203   0.00452  -0.0534   0.7492   1.0000
  -0.750   0.1971   0.01213   0.00444  -0.0530   0.7409   1.0000
  -0.500   0.2220   0.01224   0.00434  -0.0524   0.7341   1.0000
  -0.250   0.2474   0.01235   0.00431  -0.0519   0.7265   1.0000
   0.000   0.2728   0.01247   0.00428  -0.0514   0.7199   1.0000
   0.250   0.2985   0.01260   0.00430  -0.0510   0.7126   1.0000
   0.500   0.3242   0.01274   0.00431  -0.0506   0.7063   1.0000
   0.750   0.3501   0.01289   0.00438  -0.0502   0.6991   1.0000
   1.000   0.3760   0.01303   0.00444  -0.0498   0.6931   1.0000
   1.250   0.4021   0.01320   0.00457  -0.0495   0.6859   1.0000
   1.500   0.4281   0.01335   0.00464  -0.0491   0.6801   1.0000
   1.750   0.4543   0.01353   0.00482  -0.0489   0.6727   1.0000
   2.000   0.4805   0.01368   0.00492  -0.0484   0.6672   1.0000
   2.250   0.5067   0.01389   0.00517  -0.0482   0.6594   1.0000
   2.500   0.5329   0.01405   0.00530  -0.0478   0.6536   1.0000
   2.750   0.5590   0.01426   0.00556  -0.0476   0.6454   1.0000
   3.000   0.5852   0.01441   0.00572  -0.0471   0.6387   1.0000
   3.250   0.6111   0.01459   0.00599  -0.0468   0.6295   1.0000
   3.500   0.6370   0.01476   0.00621  -0.0463   0.6205   1.0000
   3.750   0.6631   0.01488   0.00635  -0.0458   0.6122   1.0000
   4.000   0.6887   0.01504   0.00660  -0.0453   0.6011   1.0000
   4.250   0.7144   0.01517   0.00682  -0.0448   0.5895   1.0000
   4.500   0.7399   0.01529   0.00708  -0.0443   0.5770   1.0000
   4.750   0.7653   0.01539   0.00728  -0.0436   0.5634   1.0000
   5.000   0.7906   0.01549   0.00748  -0.0430   0.5483   1.0000
   5.250   0.8158   0.01558   0.00767  -0.0423   0.5317   1.0000
   5.500   0.8405   0.01571   0.00792  -0.0416   0.5112   1.0000
   5.750   0.8649   0.01584   0.00813  -0.0407   0.4872   1.0000
   6.000   0.8886   0.01603   0.00849  -0.0399   0.4564   1.0000
   6.250   0.9113   0.01633   0.00879  -0.0389   0.4149   1.0000
   6.500   0.9320   0.01685   0.00916  -0.0377   0.3566   1.0000
   6.750   0.9490   0.01782   0.00979  -0.0363   0.2845   1.0000
   7.000   0.9643   0.01912   0.01076  -0.0350   0.2181   1.0000
   7.250   0.9791   0.02050   0.01186  -0.0337   0.1623   1.0000
   7.500   0.9924   0.02202   0.01306  -0.0324   0.1109   1.0000
   7.750   1.0047   0.02361   0.01429  -0.0310   0.0645   1.0000
   8.000   1.0165   0.02527   0.01576  -0.0294   0.0390   1.0000
   8.250   1.0275   0.02698   0.01751  -0.0275   0.0287   1.0000
   8.500   1.0365   0.02880   0.01954  -0.0254   0.0241   1.0000
   8.750   1.0478   0.03029   0.02117  -0.0237   0.0206   1.0000
   9.000   1.0548   0.03210   0.02305  -0.0218   0.0180   1.0000
   9.250   1.0620   0.03383   0.02494  -0.0197   0.0166   1.0000
   9.500   1.0696   0.03568   0.02696  -0.0177   0.0158   1.0000
   9.750   1.0783   0.03768   0.02914  -0.0160   0.0150   1.0000
  10.000   1.0879   0.03984   0.03149  -0.0144   0.0144   1.0000
  10.250   1.0973   0.04217   0.03403  -0.0130   0.0139   1.0000
  10.500   1.1052   0.04469   0.03678  -0.0117   0.0135   1.0000
  10.750   1.1105   0.04744   0.03978  -0.0105   0.0132   1.0000
  11.000   1.1131   0.05036   0.04295  -0.0095   0.0130   1.0000
  11.250   1.1117   0.05362   0.04647  -0.0086   0.0127   1.0000
  11.500   1.1081   0.05708   0.05020  -0.0082   0.0127   1.0000
  11.750   1.1013   0.06093   0.05431  -0.0081   0.0126   1.0000
  12.000   1.0917   0.06517   0.05881  -0.0086   0.0126   1.0000
  12.250   1.0797   0.06987   0.06383  -0.0097   0.0126   1.0000
  12.500   1.0655   0.07513   0.06933  -0.0114   0.0126   1.0000
  12.750   1.0497   0.08092   0.07536  -0.0139   0.0127   1.0000
  13.000   1.0313   0.08755   0.08214  -0.0173   0.0127   1.0000
  13.250   1.0111   0.09514   0.08995  -0.0217   0.0129   1.0000
  13.500   0.9891   0.10391   0.09891  -0.0272   0.0131   1.0000
  13.750   0.9636   0.11495   0.11013  -0.0345   0.0134   1.0000
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