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E178 (8.69%) (e178-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E178 (8.69%) (e178-il)
Reynolds number: 200,000
Max Cl/Cd: 77.22 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e178-il-200000.txt
Download as CSV file: xf-e178-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4401   0.08968   0.08651  -0.0141   1.0000   0.0419
  -8.000  -0.4414   0.08597   0.08286  -0.0182   1.0000   0.0434
  -7.750  -0.4458   0.08206   0.07904  -0.0243   1.0000   0.0442
  -7.250  -0.4348   0.07185   0.06870  -0.0384   1.0000   0.0448
  -7.000  -0.4345   0.06515   0.06210  -0.0392   1.0000   0.0461
  -6.750  -0.4236   0.06290   0.05990  -0.0375   1.0000   0.0477
  -6.500  -0.4120   0.05970   0.05669  -0.0388   1.0000   0.0499
  -6.250  -0.4011   0.05570   0.05265  -0.0416   1.0000   0.0526
  -6.000  -0.3800   0.04791   0.04432  -0.0507   0.9847   0.0590
  -5.750  -0.3487   0.04549   0.04206  -0.0530   0.9717   0.0642
  -5.500  -0.3163   0.03961   0.03559  -0.0589   0.9533   0.0731
  -5.250  -0.2897   0.03685   0.03277  -0.0602   0.9359   0.0770
  -5.000  -0.2637   0.02775   0.02231  -0.0592   0.9187   0.0436
  -4.750  -0.2439   0.02379   0.01786  -0.0579   0.9033   0.0401
  -4.500  -0.2213   0.02184   0.01546  -0.0565   0.8891   0.0415
  -4.250  -0.1977   0.01985   0.01303  -0.0552   0.8762   0.0416
  -4.000  -0.1730   0.01814   0.01095  -0.0540   0.8644   0.0415
  -3.750  -0.1478   0.01685   0.00937  -0.0529   0.8535   0.0425
  -3.500  -0.1225   0.01600   0.00831  -0.0519   0.8437   0.0443
  -3.250  -0.0980   0.01474   0.00699  -0.0511   0.8335   0.0483
  -3.000  -0.0726   0.01399   0.00620  -0.0504   0.8239   0.0517
  -2.750  -0.0472   0.01343   0.00550  -0.0496   0.8155   0.0571
  -2.500  -0.0220   0.01258   0.00470  -0.0489   0.8064   0.0788
  -2.250   0.0011   0.01135   0.00427  -0.0485   0.7981   0.2584
  -2.000   0.0235   0.01058   0.00412  -0.0476   0.7905   0.4400
  -1.750   0.0420   0.00970   0.00412  -0.0456   0.7822   0.6736
  -1.500   0.1044   0.00904   0.00398  -0.0508   0.7765   0.9801
  -1.250   0.1468   0.00905   0.00378  -0.0539   0.7685   1.0000
  -1.000   0.1711   0.00913   0.00366  -0.0532   0.7618   1.0000
  -0.750   0.1966   0.00922   0.00361  -0.0528   0.7536   1.0000
  -0.500   0.2214   0.00932   0.00354  -0.0521   0.7474   1.0000
  -0.250   0.2472   0.00942   0.00355  -0.0518   0.7394   1.0000
   0.000   0.2724   0.00954   0.00352  -0.0511   0.7335   1.0000
   0.250   0.2985   0.00965   0.00357  -0.0509   0.7257   1.0000
   0.500   0.3242   0.00978   0.00357  -0.0503   0.7200   1.0000
   0.750   0.3505   0.00991   0.00366  -0.0501   0.7125   1.0000
   1.000   0.3764   0.01004   0.00369  -0.0496   0.7067   1.0000
   1.250   0.4029   0.01018   0.00382  -0.0494   0.6994   1.0000
   1.500   0.4291   0.01031   0.00388  -0.0490   0.6934   1.0000
   1.750   0.4556   0.01046   0.00403  -0.0487   0.6863   1.0000
   2.000   0.4820   0.01059   0.00411  -0.0484   0.6799   1.0000
   2.250   0.5084   0.01074   0.00426  -0.0481   0.6725   1.0000
   2.500   0.5348   0.01085   0.00434  -0.0477   0.6653   1.0000
   2.750   0.5612   0.01098   0.00449  -0.0474   0.6567   1.0000
   3.000   0.5876   0.01109   0.00454  -0.0469   0.6500   1.0000
   3.250   0.6140   0.01119   0.00471  -0.0466   0.6403   1.0000
   3.500   0.6404   0.01129   0.00484  -0.0462   0.6315   1.0000
   3.750   0.6668   0.01136   0.00489  -0.0457   0.6227   1.0000
   4.000   0.6931   0.01143   0.00502  -0.0453   0.6118   1.0000
   4.250   0.7194   0.01150   0.00514  -0.0448   0.6011   1.0000
   4.500   0.7457   0.01155   0.00525  -0.0444   0.5903   1.0000
   4.750   0.7719   0.01158   0.00533  -0.0439   0.5784   1.0000
   5.000   0.7979   0.01160   0.00541  -0.0433   0.5645   1.0000
   5.250   0.8238   0.01162   0.00551  -0.0428   0.5487   1.0000
   5.500   0.8495   0.01165   0.00564  -0.0422   0.5307   1.0000
   5.750   0.8750   0.01170   0.00574  -0.0416   0.5106   1.0000
   6.000   0.9000   0.01180   0.00589  -0.0409   0.4843   1.0000
   6.250   0.9243   0.01197   0.00610  -0.0402   0.4473   1.0000
   6.500   0.9463   0.01239   0.00636  -0.0392   0.3872   1.0000
   6.750   0.9618   0.01361   0.00697  -0.0378   0.2752   1.0000
   7.000   0.9753   0.01525   0.00802  -0.0365   0.1749   1.0000
   7.250   0.9913   0.01662   0.00904  -0.0354   0.1134   1.0000
   7.500   1.0014   0.01873   0.01068  -0.0334   0.0491   1.0000
   7.750   1.0109   0.02081   0.01265  -0.0312   0.0303   1.0000
   8.000   1.0268   0.02205   0.01402  -0.0296   0.0257   1.0000
   8.250   1.0401   0.02352   0.01555  -0.0278   0.0232   1.0000
   8.500   1.0493   0.02570   0.01778  -0.0256   0.0215   1.0000
   8.750   1.0640   0.02809   0.02026  -0.0239   0.0207   1.0000
   9.000   1.0834   0.03006   0.02239  -0.0227   0.0202   1.0000
   9.250   1.1034   0.03244   0.02501  -0.0216   0.0199   1.0000
   9.500   1.1215   0.03491   0.02776  -0.0204   0.0196   1.0000
   9.750   1.1358   0.03687   0.02999  -0.0190   0.0184   1.0000
  10.000   1.1474   0.03937   0.03278  -0.0174   0.0178   1.0000
  10.250   1.1546   0.04238   0.03613  -0.0156   0.0176   1.0000
  10.500   1.1550   0.04596   0.04008  -0.0133   0.0178   1.0000
  10.750   1.1484   0.04931   0.04376  -0.0106   0.0181   1.0000
  11.000   1.1374   0.05286   0.04759  -0.0083   0.0185   1.0000
  11.250   1.1235   0.05672   0.05171  -0.0068   0.0188   1.0000
  11.500   1.1082   0.06083   0.05606  -0.0062   0.0190   1.0000
  11.750   1.0913   0.06537   0.06081  -0.0065   0.0193   1.0000
  12.000   1.0730   0.07038   0.06603  -0.0076   0.0195   1.0000
  12.250   1.0540   0.07592   0.07173  -0.0095   0.0198   1.0000
  12.500   1.0345   0.08187   0.07786  -0.0123   0.0199   1.0000
  12.750   1.0144   0.08857   0.08469  -0.0158   0.0202   1.0000
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