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E178 (8.69%) (e178-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E178 (8.69%) (e178-il)
Reynolds number: 50,000
Max Cl/Cd: 37.69 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e178-il-50000-n5.txt
Download as CSV file: xf-e178-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4465   0.10493   0.09849  -0.0107   1.0000   0.1057
  -8.500  -0.4535   0.09670   0.09030  -0.0194   1.0000   0.0549
  -8.250  -0.4497   0.09268   0.08635  -0.0211   1.0000   0.0546
  -8.000  -0.4480   0.08865   0.08241  -0.0235   1.0000   0.0545
  -7.750  -0.4451   0.08454   0.07836  -0.0261   1.0000   0.0542
  -7.500  -0.4409   0.08013   0.07400  -0.0292   1.0000   0.0539
  -7.250  -0.4356   0.07569   0.06959  -0.0321   1.0000   0.0533
  -7.000  -0.4295   0.07122   0.06512  -0.0349   1.0000   0.0524
  -6.750  -0.4228   0.06655   0.06044  -0.0377   1.0000   0.0512
  -6.500  -0.4154   0.06179   0.05561  -0.0404   1.0000   0.0500
  -6.250  -0.4071   0.05704   0.05073  -0.0427   1.0000   0.0490
  -6.000  -0.3984   0.05245   0.04593  -0.0442   1.0000   0.0482
  -5.750  -0.3900   0.04833   0.04155  -0.0448   1.0000   0.0476
  -5.500  -0.3828   0.04482   0.03775  -0.0441   1.0000   0.0473
  -5.250  -0.3762   0.04179   0.03439  -0.0428   1.0000   0.0472
  -5.000  -0.3637   0.03878   0.03098  -0.0422   0.9971   0.0475
  -4.750  -0.3279   0.03508   0.02661  -0.0454   0.9838   0.0495
  -4.500  -0.2901   0.03218   0.02280  -0.0480   0.9718   0.0551
  -4.250  -0.2539   0.02948   0.01967  -0.0503   0.9612   0.0577
  -4.000  -0.2158   0.02735   0.01716  -0.0524   0.9516   0.0604
  -3.750  -0.1778   0.02556   0.01500  -0.0541   0.9422   0.0642
  -3.500  -0.1427   0.02414   0.01325  -0.0550   0.9316   0.0692
  -3.250  -0.1080   0.02295   0.01192  -0.0563   0.9213   0.0790
  -2.750  -0.0423   0.02050   0.00998  -0.0590   0.9015   0.1994
  -2.500  -0.0186   0.01903   0.00949  -0.0588   0.8906   0.4085
  -2.250   0.0012   0.01777   0.00943  -0.0557   0.8811   0.7017
  -2.000   0.0909   0.01705   0.00850  -0.0659   0.8790   1.0000
  -1.750   0.1172   0.01720   0.00820  -0.0658   0.8675   1.0000
  -1.500   0.1433   0.01736   0.00801  -0.0656   0.8569   1.0000
  -1.250   0.1688   0.01754   0.00788  -0.0653   0.8467   1.0000
  -1.000   0.1927   0.01776   0.00785  -0.0647   0.8360   1.0000
  -0.750   0.2171   0.01799   0.00784  -0.0642   0.8263   1.0000
  -0.500   0.2426   0.01820   0.00780  -0.0637   0.8178   1.0000
  -0.250   0.2663   0.01847   0.00790  -0.0631   0.8080   1.0000
   0.000   0.2905   0.01875   0.00802  -0.0626   0.7990   1.0000
   0.250   0.3159   0.01898   0.00810  -0.0620   0.7913   1.0000
   0.500   0.3394   0.01932   0.00833  -0.0615   0.7819   1.0000
   0.750   0.3640   0.01962   0.00852  -0.0610   0.7739   1.0000
   1.000   0.3892   0.01992   0.00875  -0.0605   0.7658   1.0000
   1.250   0.4135   0.02029   0.00908  -0.0601   0.7572   1.0000
   1.500   0.4394   0.02056   0.00929  -0.0596   0.7503   1.0000
   1.750   0.4630   0.02099   0.00971  -0.0592   0.7412   1.0000
   2.000   0.4883   0.02132   0.01001  -0.0587   0.7340   1.0000
   2.250   0.5125   0.02173   0.01047  -0.0582   0.7255   1.0000
   2.500   0.5366   0.02215   0.01092  -0.0577   0.7172   1.0000
   2.750   0.5620   0.02247   0.01128  -0.0572   0.7098   1.0000
   3.000   0.5852   0.02297   0.01184  -0.0566   0.7004   1.0000
   3.250   0.6103   0.02330   0.01224  -0.0560   0.6926   1.0000
   3.500   0.6343   0.02370   0.01279  -0.0553   0.6832   1.0000
   3.750   0.6574   0.02415   0.01335  -0.0546   0.6729   1.0000
   4.000   0.6817   0.02448   0.01379  -0.0538   0.6630   1.0000
   4.250   0.7074   0.02465   0.01407  -0.0528   0.6537   1.0000
   4.500   0.7303   0.02503   0.01460  -0.0519   0.6415   1.0000
   4.750   0.7536   0.02532   0.01514  -0.0508   0.6289   1.0000
   5.000   0.7773   0.02550   0.01549  -0.0496   0.6154   1.0000
   5.250   0.8013   0.02557   0.01574  -0.0483   0.6010   1.0000
   5.500   0.8257   0.02551   0.01586  -0.0468   0.5855   1.0000
   5.750   0.8473   0.02563   0.01621  -0.0453   0.5661   1.0000
   6.000   0.8709   0.02544   0.01622  -0.0435   0.5459   1.0000
   6.250   0.8924   0.02536   0.01648  -0.0417   0.5213   1.0000
   6.500   0.9138   0.02518   0.01651  -0.0397   0.4921   1.0000
   6.750   0.9332   0.02516   0.01668  -0.0376   0.4544   1.0000
   7.000   0.9513   0.02524   0.01681  -0.0353   0.4049   1.0000
   7.250   0.9658   0.02574   0.01711  -0.0328   0.3371   1.0000
   7.500   0.9743   0.02709   0.01799  -0.0303   0.2661   1.0000
   7.750   0.9791   0.02904   0.01956  -0.0281   0.2089   1.0000
   8.000   0.9819   0.03124   0.02143  -0.0260   0.1650   1.0000
   8.250   0.9845   0.03349   0.02347  -0.0240   0.1297   1.0000
   8.500   0.9858   0.03583   0.02563  -0.0220   0.1023   1.0000
   8.750   0.9861   0.03816   0.02783  -0.0199   0.0826   1.0000
   9.000   0.9886   0.04054   0.03017  -0.0181   0.0662   1.0000
   9.250   0.9937   0.04290   0.03269  -0.0165   0.0550   1.0000
   9.500   1.0009   0.04530   0.03506  -0.0151   0.0478   1.0000
   9.750   1.0110   0.04750   0.03749  -0.0139   0.0404   1.0000
  10.000   1.0246   0.04991   0.04001  -0.0125   0.0361   1.0000
  10.250   1.0465   0.05272   0.04325  -0.0110   0.0333   1.0000
  10.500   1.0593   0.05596   0.04686  -0.0099   0.0316   1.0000
  10.750   1.0645   0.05948   0.05071  -0.0090   0.0306   1.0000
  11.000   1.0640   0.06314   0.05468  -0.0084   0.0299   1.0000
  11.250   1.0586   0.06707   0.05887  -0.0082   0.0292   1.0000
  11.500   1.0504   0.07130   0.06336  -0.0087   0.0289   1.0000
  11.750   1.0392   0.07597   0.06828  -0.0097   0.0287   1.0000
  12.000   1.0252   0.08120   0.07375  -0.0115   0.0286   1.0000
  12.250   1.0071   0.08750   0.08030  -0.0143   0.0290   1.0000
  12.500   0.9861   0.09481   0.08783  -0.0183   0.0296   1.0000
  12.750   0.9620   0.10350   0.09670  -0.0236   0.0304   1.0000
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