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E. Bambino (ebambino7-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E. Bambino (ebambino7-il)
Reynolds number: 100,000
Max Cl/Cd: 33.02 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ebambino7-il-100000-n5.txt
Download as CSV file: xf-ebambino7-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.5692   0.11202   0.10770   0.0181   1.0000   0.0258
  -7.000  -0.5665   0.10851   0.10423   0.0143   1.0000   0.0259
  -6.750  -0.5639   0.10485   0.10062   0.0099   1.0000   0.0260
  -6.500  -0.5553   0.09920   0.09500   0.0165   1.0000   0.0286
  -6.250  -0.5519   0.09552   0.09136   0.0141   1.0000   0.0301
  -6.000  -0.5467   0.09164   0.08750   0.0104   1.0000   0.0315
  -5.750  -0.5374   0.08772   0.08357   0.0053   1.0000   0.0334
  -5.500  -0.5228   0.08409   0.07985  -0.0016   1.0000   0.0344
  -5.250  -0.5062   0.08065   0.07624  -0.0065   1.0000   0.0347
  -5.000  -0.5033   0.07482   0.07060  -0.0041   1.0000   0.0363
  -4.750  -0.4909   0.07099   0.06674  -0.0050   1.0000   0.0390
  -4.500  -0.4678   0.06776   0.06331  -0.0090   1.0000   0.0431
  -4.000  -0.4342   0.05896   0.05429  -0.0121   1.0000   0.0464
  -3.750  -0.4177   0.05514   0.05043  -0.0125   1.0000   0.0493
  -3.500  -0.3952   0.05177   0.04686  -0.0136   1.0000   0.0538
  -3.250  -0.3671   0.04885   0.04346  -0.0150   1.0000   0.0583
  -3.000  -0.3497   0.04454   0.03922  -0.0150   1.0000   0.0612
  -2.750  -0.3254   0.04126   0.03574  -0.0153   1.0000   0.0629
  -2.250  -0.2661   0.03401   0.02771  -0.0142   1.0000   0.0323
  -2.000  -0.2376   0.03065   0.02393  -0.0134   1.0000   0.0241
  -1.750  -0.2109   0.02785   0.02083  -0.0127   1.0000   0.0213
  -1.500  -0.1770   0.02499   0.01747  -0.0127   0.9812   0.0185
  -1.250  -0.1378   0.02290   0.01490  -0.0135   0.9482   0.0168
  -1.000  -0.1045   0.02082   0.01243  -0.0137   0.9142   0.0169
  -0.750  -0.0756   0.01887   0.01019  -0.0130   0.8732   0.0183
  -0.500  -0.0527   0.01767   0.00856  -0.0105   0.7802   0.0192
  -0.250  -0.0340   0.01693   0.00716  -0.0072   0.6762   0.0195
   0.000  -0.0112   0.01632   0.00596  -0.0055   0.5859   0.0204
   0.250   0.0115   0.01665   0.00498  -0.0044   0.3177   0.0228
   0.500   0.0379   0.01668   0.00444  -0.0041   0.1845   0.0325
   1.000   0.1209   0.01385   0.00388  -0.0084   0.1478   1.0000
   1.250   0.1460   0.01394   0.00367  -0.0079   0.1413   1.0000
   1.500   0.1711   0.01402   0.00353  -0.0074   0.1226   1.0000
   1.750   0.1960   0.01433   0.00344  -0.0070   0.0780   1.0000
   2.000   0.2212   0.01452   0.00343  -0.0066   0.0742   1.0000
   2.250   0.2466   0.01472   0.00347  -0.0062   0.0726   1.0000
   2.500   0.2721   0.01494   0.00359  -0.0058   0.0713   1.0000
   2.750   0.2976   0.01520   0.00377  -0.0055   0.0699   1.0000
   3.000   0.3231   0.01555   0.00408  -0.0052   0.0673   1.0000
   3.250   0.3484   0.01600   0.00449  -0.0049   0.0640   1.0000
   3.500   0.3738   0.01642   0.00490  -0.0047   0.0615   1.0000
   3.750   0.3994   0.01679   0.00528  -0.0045   0.0601   1.0000
   4.000   0.4250   0.01718   0.00575  -0.0042   0.0595   1.0000
   4.250   0.4506   0.01761   0.00623  -0.0040   0.0590   1.0000
   4.500   0.4761   0.01807   0.00676  -0.0038   0.0585   1.0000
   4.750   0.5015   0.01855   0.00731  -0.0036   0.0582   1.0000
   5.000   0.5251   0.01946   0.00827  -0.0036   0.0510   1.0000
   5.250   0.5516   0.01943   0.00830  -0.0037   0.0434   1.0000
   5.500   0.5778   0.01950   0.00834  -0.0038   0.0393   1.0000
   5.750   0.6055   0.01913   0.00809  -0.0038   0.0356   1.0000
   6.000   0.6313   0.01961   0.00875  -0.0035   0.0166   1.0000
   6.250   0.6571   0.02013   0.00940  -0.0033   0.0154   1.0000
   6.500   0.6829   0.02068   0.01009  -0.0030   0.0148   1.0000
   6.750   0.7080   0.02148   0.01107  -0.0027   0.0137   1.0000
   7.000   0.7328   0.02239   0.01220  -0.0023   0.0125   1.0000
   7.250   0.7576   0.02329   0.01331  -0.0019   0.0123   1.0000
   7.500   0.7819   0.02438   0.01457  -0.0015   0.0123   1.0000
   7.750   0.8051   0.02569   0.01607  -0.0011   0.0125   1.0000
   8.000   0.8254   0.02753   0.01811  -0.0005   0.0130   1.0000
   8.250   0.8493   0.02845   0.01917   0.0000   0.0137   1.0000
   8.500   0.8746   0.02906   0.02004   0.0006   0.0146   1.0000
   8.750   0.9003   0.02969   0.02099   0.0013   0.0160   1.0000
   9.000   0.9230   0.03113   0.02288   0.0022   0.0171   1.0000
   9.250   0.9428   0.03326   0.02542   0.0032   0.0177   1.0000
   9.500   0.9601   0.03599   0.02860   0.0043   0.0183   1.0000
   9.750   0.9742   0.03931   0.03239   0.0054   0.0188   1.0000
  10.000   0.9838   0.04324   0.03679   0.0065   0.0194   1.0000
  11.500   0.9399   0.07118   0.06668   0.0026   0.0210   1.0000
  11.750   0.9208   0.07955   0.07517  -0.0049   0.0207   1.0000
  12.000   0.8999   0.09089   0.08655  -0.0141   0.0204   1.0000
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