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E. Bambino (ebambino7-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E. Bambino (ebambino7-il)
Reynolds number: 200,000
Max Cl/Cd: 37.51 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ebambino7-il-200000-n5.txt
Download as CSV file: xf-ebambino7-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E. Bambino                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.5692   0.10993   0.10687   0.0220   1.0000   0.0085
  -7.000  -0.5672   0.10544   0.10242   0.0202   1.0000   0.0086
  -6.750  -0.5644   0.10123   0.09823   0.0188   1.0000   0.0088
  -6.500  -0.5609   0.09722   0.09425   0.0172   1.0000   0.0090
  -6.250  -0.5578   0.09326   0.09032   0.0148   1.0000   0.0091
  -6.000  -0.5516   0.08911   0.08618   0.0116   1.0000   0.0093
  -5.750  -0.5437   0.08494   0.08200   0.0086   1.0000   0.0095
  -5.500  -0.5339   0.08074   0.07779   0.0055   1.0000   0.0097
  -5.250  -0.5223   0.07653   0.07355   0.0025   1.0000   0.0100
  -5.000  -0.5088   0.07230   0.06928  -0.0004   1.0000   0.0103
  -4.750  -0.4935   0.06809   0.06502  -0.0032   1.0000   0.0106
  -4.500  -0.4763   0.06393   0.06077  -0.0056   1.0000   0.0110
  -4.250  -0.4574   0.05982   0.05657  -0.0078   1.0000   0.0114
  -4.000  -0.4368   0.05580   0.05241  -0.0096   1.0000   0.0120
  -3.750  -0.4148   0.05188   0.04835  -0.0111   1.0000   0.0126
  -3.500  -0.3881   0.04791   0.04420  -0.0130   0.9708   0.0134
  -3.250  -0.3580   0.04417   0.04019  -0.0145   0.9326   0.0146
  -3.000  -0.3267   0.04216   0.03782  -0.0138   0.8908   0.0161
  -2.750  -0.3047   0.03963   0.03491  -0.0124   0.8331   0.0163
  -2.250  -0.2699   0.03205   0.02645  -0.0105   0.7142   0.0189
  -1.250  -0.1641   0.02425   0.01525  -0.0078   0.1604   0.0208
  -1.000  -0.1334   0.02179   0.01235  -0.0067   0.1479   0.0127
  -0.750  -0.1038   0.01972   0.00986  -0.0058   0.1349   0.0110
  -0.500  -0.0748   0.01824   0.00790  -0.0052   0.0750   0.0101
  -0.250  -0.0469   0.01713   0.00649  -0.0046   0.0674   0.0097
   0.000  -0.0195   0.01617   0.00539  -0.0041   0.0638   0.0097
   0.250   0.0076   0.01536   0.00448  -0.0037   0.0621   0.0107
   0.500   0.0350   0.01482   0.00380  -0.0035   0.0612   0.0137
   0.750   0.0629   0.01450   0.00327  -0.0032   0.0605   0.0155
   1.000   0.0908   0.01421   0.00297  -0.0030   0.0598   0.0396
   1.250   0.1077   0.01189   0.00291  -0.0016   0.0588   0.7131
   1.500   0.1590   0.01167   0.00314  -0.0051   0.0555   0.9949
   1.750   0.1914   0.01193   0.00327  -0.0063   0.0526   1.0000
   2.000   0.2163   0.01221   0.00344  -0.0059   0.0508   1.0000
   2.250   0.2413   0.01252   0.00367  -0.0055   0.0498   1.0000
   2.500   0.2665   0.01283   0.00388  -0.0052   0.0491   1.0000
   2.750   0.2920   0.01305   0.00402  -0.0049   0.0486   1.0000
   3.000   0.3176   0.01330   0.00422  -0.0046   0.0480   1.0000
   3.250   0.3435   0.01359   0.00447  -0.0044   0.0473   1.0000
   3.500   0.3693   0.01393   0.00477  -0.0043   0.0465   1.0000
   3.750   0.3953   0.01431   0.00513  -0.0041   0.0458   1.0000
   4.000   0.4212   0.01473   0.00557  -0.0040   0.0452   1.0000
   4.250   0.4471   0.01518   0.00602  -0.0038   0.0446   1.0000
   4.500   0.4733   0.01535   0.00619  -0.0039   0.0422   1.0000
   4.750   0.4999   0.01529   0.00606  -0.0041   0.0387   1.0000
   5.000   0.5280   0.01474   0.00556  -0.0042   0.0313   1.0000
   5.250   0.5540   0.01530   0.00616  -0.0040   0.0149   1.0000
   5.500   0.5802   0.01574   0.00671  -0.0039   0.0117   1.0000
   5.750   0.6066   0.01617   0.00727  -0.0037   0.0105   1.0000
   6.000   0.6319   0.01708   0.00839  -0.0035   0.0079   1.0000
   6.250   0.6578   0.01768   0.00913  -0.0034   0.0077   1.0000
   6.500   0.6836   0.01834   0.00993  -0.0032   0.0076   1.0000
   6.750   0.7085   0.01932   0.01104  -0.0030   0.0077   1.0000
   7.000   0.7337   0.02009   0.01187  -0.0027   0.0081   1.0000
   7.250   0.7587   0.02088   0.01265  -0.0024   0.0083   1.0000
   7.500   0.7821   0.02208   0.01387  -0.0020   0.0068   1.0000
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