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BOEING 707 .40 SPAN AIRFOIL (b707c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: BOEING 707 .40 SPAN AIRFOIL (b707c-il)
Reynolds number: 1,000,000
Max Cl/Cd: 73.05 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-b707c-il-1000000.txt
Download as CSV file: xf-b707c-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING 707 .40 SPAN AIRFOIL                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4801   0.08746   0.08577  -0.0256   1.0000   0.0108
  -9.000  -0.4816   0.08351   0.08184  -0.0277   1.0000   0.0109
  -8.750  -0.4861   0.07926   0.07761  -0.0305   1.0000   0.0109
  -8.500  -0.5003   0.07461   0.07298  -0.0346   1.0000   0.0109
  -8.250  -0.5162   0.07120   0.06956  -0.0342   1.0000   0.0110
  -8.000  -0.5245   0.06783   0.06614  -0.0338   1.0000   0.0110
  -7.750  -0.5316   0.06478   0.06305  -0.0324   1.0000   0.0111
  -7.500  -0.5124   0.05943   0.05756  -0.0372   0.9970   0.0119
  -7.250  -0.4884   0.05381   0.05165  -0.0406   0.9926   0.0123
  -7.000  -0.4668   0.04983   0.04751  -0.0426   0.9885   0.0123
  -6.750  -0.4511   0.04414   0.04163  -0.0450   0.9851   0.0126
  -6.500  -0.4323   0.04151   0.03891  -0.0457   0.9790   0.0127
  -6.250  -0.4073   0.03877   0.03606  -0.0473   0.9747   0.0129
  -6.000  -0.3810   0.03628   0.03344  -0.0488   0.9682   0.0132
  -5.750  -0.3513   0.03368   0.03068  -0.0506   0.9596   0.0136
  -5.500  -0.3217   0.03111   0.02791  -0.0518   0.9446   0.0142
  -5.250  -0.2883   0.02893   0.02539  -0.0513   0.9245   0.0155
  -5.000  -0.2653   0.02703   0.02319  -0.0503   0.8898   0.0155
  -4.750  -0.2520   0.02368   0.01945  -0.0482   0.8446   0.0158
  -4.500  -0.2356   0.02256   0.01801  -0.0464   0.7774   0.0161
  -4.250  -0.2182   0.02168   0.01678  -0.0446   0.7074   0.0163
  -4.000  -0.1971   0.02067   0.01553  -0.0435   0.6733   0.0167
  -3.750  -0.1743   0.01956   0.01422  -0.0425   0.6534   0.0173
  -3.250  -0.1262   0.01689   0.01090  -0.0397   0.6160   0.0197
  -3.000  -0.1021   0.01586   0.00979  -0.0392   0.5973   0.0202
  -2.750  -0.0774   0.01509   0.00890  -0.0387   0.5750   0.0208
  -2.500  -0.0516   0.01174   0.00510  -0.0366   0.5512   0.0158
  -2.250  -0.0302   0.01148   0.00446  -0.0353   0.4546   0.0157
  -2.000  -0.0130   0.01173   0.00403  -0.0335   0.2672   0.0156
  -1.750   0.0082   0.01125   0.00335  -0.0323   0.2199   0.0159
  -1.500   0.0323   0.01092   0.00297  -0.0316   0.2097   0.0163
  -1.250   0.0566   0.01064   0.00261  -0.0308   0.1980   0.0164
  -1.000   0.0814   0.01047   0.00230  -0.0302   0.1721   0.0167
  -0.750   0.1041   0.01071   0.00219  -0.0293   0.0378   0.0173
  -0.500   0.1301   0.01061   0.00208  -0.0289   0.0366   0.0185
  -0.250   0.1563   0.01053   0.00200  -0.0285   0.0356   0.0210
   0.000   0.1827   0.01052   0.00201  -0.0281   0.0350   0.0266
   0.250   0.2090   0.01054   0.00206  -0.0278   0.0331   0.0343
   0.500   0.2348   0.01062   0.00214  -0.0274   0.0310   0.0390
   0.750   0.2610   0.01065   0.00217  -0.0271   0.0306   0.0436
   1.000   0.2875   0.01067   0.00217  -0.0269   0.0298   0.0470
   1.250   0.3136   0.01069   0.00219  -0.0266   0.0292   0.0584
   1.500   0.3347   0.01000   0.00219  -0.0256   0.0272   0.3747
   1.750   0.3596   0.00997   0.00229  -0.0252   0.0260   0.4254
   2.000   0.3816   0.00959   0.00232  -0.0243   0.0251   0.5610
   2.250   0.4037   0.00923   0.00236  -0.0232   0.0241   0.7041
   2.500   0.4288   0.00921   0.00242  -0.0227   0.0231   0.7411
   2.750   0.4534   0.00918   0.00249  -0.0221   0.0224   0.7774
   3.000   0.4772   0.00915   0.00256  -0.0212   0.0212   0.8174
   3.250   0.5003   0.00908   0.00265  -0.0202   0.0206   0.8665
   3.500   0.5255   0.00903   0.00276  -0.0195   0.0190   0.9210
   3.750   0.5621   0.00919   0.00288  -0.0215   0.0125   0.9542
   4.000   0.6034   0.00945   0.00315  -0.0247   0.0120   0.9723
   4.250   0.6424   0.00972   0.00343  -0.0274   0.0117   0.9816
   4.500   0.6777   0.00998   0.00368  -0.0292   0.0116   0.9892
   4.750   0.7106   0.01023   0.00392  -0.0306   0.0116   0.9952
   5.000   0.7467   0.01050   0.00419  -0.0327   0.0115   0.9995
   5.250   0.7712   0.01074   0.00444  -0.0321   0.0115   1.0000
   5.500   0.7929   0.01098   0.00468  -0.0310   0.0115   1.0000
   5.750   0.8147   0.01122   0.00494  -0.0299   0.0116   1.0000
   6.000   0.8366   0.01148   0.00521  -0.0288   0.0116   1.0000
   6.250   0.8585   0.01176   0.00551  -0.0277   0.0117   1.0000
   6.500   0.8803   0.01205   0.00583  -0.0266   0.0118   1.0000
   6.750   0.9019   0.01237   0.00618  -0.0255   0.0118   1.0000
   7.000   0.9233   0.01270   0.00654  -0.0244   0.0119   1.0000
   7.250   0.9437   0.01313   0.00700  -0.0231   0.0118   1.0000
   7.500   0.9644   0.01354   0.00745  -0.0219   0.0118   1.0000
   7.750   0.9848   0.01398   0.00793  -0.0206   0.0118   1.0000
   8.000   1.0051   0.01442   0.00842  -0.0194   0.0119   1.0000
   8.250   1.0246   0.01494   0.00898  -0.0180   0.0120   1.0000
   8.500   1.0438   0.01548   0.00958  -0.0166   0.0120   1.0000
   8.750   1.0624   0.01606   0.01022  -0.0152   0.0121   1.0000
   9.000   1.0802   0.01670   0.01092  -0.0136   0.0122   1.0000
   9.250   1.0972   0.01742   0.01171  -0.0120   0.0122   1.0000
   9.500   1.1136   0.01818   0.01256  -0.0102   0.0122   1.0000
   9.750   1.1288   0.01906   0.01352  -0.0084   0.0123   1.0000
  10.000   1.1425   0.02011   0.01467  -0.0064   0.0124   1.0000
  10.250   1.1572   0.02106   0.01570  -0.0045   0.0125   1.0000
  10.500   1.1694   0.02234   0.01712  -0.0024   0.0124   1.0000
  10.750   1.1833   0.02309   0.01794  -0.0004   0.0125   1.0000
  11.000   1.1964   0.02374   0.01865   0.0017   0.0127   1.0000
  11.250   1.2069   0.02484   0.01987   0.0040   0.0128   1.0000
  11.500   1.2173   0.02595   0.02112   0.0063   0.0129   1.0000
  15.500   0.7876   0.17401   0.17222  -0.0370   0.0158   1.0000
  15.750   0.7929   0.17759   0.17579  -0.0388   0.0155   1.0000
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