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BOEING 707 .08 SPAN AIRFOIL (b707a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: BOEING 707 .08 SPAN AIRFOIL (b707a-il)
Reynolds number: 200,000
Max Cl/Cd: 43.61 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-b707a-il-200000-n5.txt
Download as CSV file: xf-b707a-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING 707 .08 SPAN AIRFOIL                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.9521   0.10030   0.09540  -0.0092   1.0000   0.0176
 -15.500  -0.9838   0.09028   0.08512  -0.0151   1.0000   0.0175
 -15.250  -1.0041   0.08314   0.07777  -0.0189   1.0000   0.0174
 -15.000  -1.0213   0.07695   0.07138  -0.0220   1.0000   0.0174
 -14.750  -1.0355   0.07155   0.06578  -0.0244   1.0000   0.0173
 -14.500  -1.0459   0.06689   0.06093  -0.0263   1.0000   0.0173
 -14.250  -1.0545   0.06260   0.05646  -0.0278   1.0000   0.0173
 -14.000  -1.0593   0.05893   0.05262  -0.0289   1.0000   0.0173
 -13.750  -1.0629   0.05548   0.04902  -0.0297   1.0000   0.0173
 -13.500  -1.0643   0.05241   0.04579  -0.0302   1.0000   0.0173
 -13.250  -1.0640   0.04960   0.04283  -0.0305   1.0000   0.0173
 -13.000  -1.0625   0.04701   0.04011  -0.0306   1.0000   0.0174
 -12.750  -1.0602   0.04457   0.03753  -0.0305   1.0000   0.0174
 -12.500  -1.0566   0.04234   0.03519  -0.0302   1.0000   0.0175
 -12.250  -1.0519   0.04033   0.03306  -0.0297   1.0000   0.0175
 -12.000  -1.0470   0.03839   0.03101  -0.0291   1.0000   0.0176
 -11.750  -1.0414   0.03659   0.02910  -0.0282   1.0000   0.0177
 -11.500  -1.0357   0.03490   0.02731  -0.0272   1.0000   0.0178
 -11.250  -1.0293   0.03340   0.02572  -0.0259   1.0000   0.0178
 -11.000  -1.0231   0.03198   0.02421  -0.0244   1.0000   0.0179
 -10.750  -1.0166   0.03071   0.02286  -0.0225   1.0000   0.0180
 -10.500  -1.0104   0.02954   0.02160  -0.0203   1.0000   0.0181
 -10.250  -1.0041   0.02850   0.02049  -0.0178   1.0000   0.0182
 -10.000  -0.9980   0.02754   0.01945  -0.0149   1.0000   0.0183
  -9.750  -0.9899   0.02659   0.01844  -0.0123   1.0000   0.0185
  -9.500  -0.9798   0.02566   0.01746  -0.0099   1.0000   0.0186
  -9.250  -0.9691   0.02473   0.01650  -0.0076   1.0000   0.0189
  -9.000  -0.9566   0.02390   0.01561  -0.0054   1.0000   0.0191
  -8.750  -0.9430   0.02310   0.01477  -0.0033   1.0000   0.0194
  -8.500  -0.9284   0.02236   0.01398  -0.0013   1.0000   0.0197
  -8.250  -0.9130   0.02164   0.01322   0.0007   1.0000   0.0201
  -8.000  -0.8968   0.02097   0.01251   0.0025   1.0000   0.0205
  -7.750  -0.8800   0.02033   0.01182   0.0044   1.0000   0.0210
  -7.500  -0.8629   0.01970   0.01116   0.0061   1.0000   0.0216
  -7.250  -0.8455   0.01908   0.01054   0.0079   1.0000   0.0224
  -7.000  -0.8274   0.01849   0.00996   0.0096   1.0000   0.0236
  -6.750  -0.8085   0.01797   0.00949   0.0111   1.0000   0.0259
  -6.500  -0.7878   0.01760   0.00927   0.0124   1.0000   0.0326
  -6.250  -0.7656   0.01735   0.00898   0.0135   1.0000   0.0424
  -6.000  -0.7431   0.01712   0.00872   0.0147   1.0000   0.0478
  -5.750  -0.7156   0.01686   0.00841   0.0147   0.9981   0.0519
  -5.500  -0.6838   0.01653   0.00807   0.0137   0.9932   0.0555
  -5.250  -0.6535   0.01622   0.00771   0.0132   0.9876   0.0582
  -5.000  -0.6220   0.01581   0.00730   0.0123   0.9812   0.0611
  -4.750  -0.5945   0.01546   0.00693   0.0123   0.9736   0.0632
  -4.500  -0.5645   0.01513   0.00657   0.0119   0.9666   0.0657
  -4.250  -0.5352   0.01471   0.00616   0.0115   0.9551   0.0688
  -3.750  -0.4269   0.01439   0.00498   0.0010   0.6263   0.0812
  -3.500  -0.4058   0.01444   0.00469   0.0024   0.5373   0.0861
  -3.250  -0.3822   0.01431   0.00442   0.0034   0.4986   0.0922
  -3.000  -0.3609   0.01406   0.00408   0.0045   0.4097   0.1173
  -2.750  -0.3446   0.01296   0.00346   0.0060   0.3784   0.2720
  -2.500  -0.3212   0.01282   0.00357   0.0070   0.3689   0.3785
  -2.250  -0.2949   0.01286   0.00355   0.0075   0.3634   0.3982
  -2.000  -0.2683   0.01289   0.00352   0.0080   0.3596   0.4092
  -1.500  -0.2153   0.01297   0.00350   0.0090   0.3516   0.4274
  -1.250  -0.1889   0.01301   0.00352   0.0095   0.3463   0.4355
  -1.000  -0.1625   0.01315   0.00353   0.0100   0.3393   0.4418
  -0.750  -0.1361   0.01319   0.00356   0.0105   0.3327   0.4476
  -0.500  -0.1096   0.01324   0.00360   0.0110   0.3270   0.4532
  -0.250  -0.0828   0.01334   0.00364   0.0114   0.3230   0.4585
   0.000  -0.0559   0.01344   0.00369   0.0118   0.3190   0.4645
   0.250  -0.0293   0.01343   0.00375   0.0123   0.3137   0.4714
   0.500  -0.0027   0.01354   0.00383   0.0127   0.3077   0.4787
   0.750   0.0245   0.01362   0.00389   0.0131   0.3011   0.4844
   1.000   0.0511   0.01363   0.00394   0.0135   0.2930   0.4882
   1.250   0.0783   0.01359   0.00397   0.0139   0.2842   0.4908
   1.500   0.1055   0.01356   0.00398   0.0143   0.2745   0.4939
   1.750   0.1333   0.01345   0.00399   0.0146   0.2609   0.4973
   2.000   0.1611   0.01334   0.00392   0.0149   0.2307   0.5014
   2.500   0.2138   0.01344   0.00382   0.0158   0.1984   0.5105
   2.750   0.2400   0.01356   0.00397   0.0163   0.1886   0.5161
   3.000   0.2661   0.01373   0.00414   0.0167   0.1790   0.5222
   3.250   0.2923   0.01387   0.00430   0.0172   0.1682   0.5285
   3.500   0.3184   0.01396   0.00446   0.0177   0.1571   0.5363
   3.750   0.3443   0.01410   0.00461   0.0182   0.1437   0.5460
   4.000   0.3698   0.01422   0.00476   0.0188   0.1308   0.5582
   4.250   0.3951   0.01434   0.00496   0.0194   0.1208   0.5749
   4.500   0.4199   0.01446   0.00518   0.0201   0.1108   0.5993
   4.750   0.4442   0.01456   0.00542   0.0210   0.1009   0.6361
   5.000   0.4680   0.01463   0.00569   0.0220   0.0880   0.6860
   5.250   0.4917   0.01474   0.00597   0.0230   0.0773   0.7424
   5.500   0.5178   0.01490   0.00629   0.0236   0.0706   0.8050
   5.750   0.5582   0.01519   0.00679   0.0213   0.0655   0.8856
   6.000   0.6079   0.01567   0.00734   0.0167   0.0609   0.9487
   6.250   0.6451   0.01613   0.00782   0.0147   0.0584   0.9794
   6.500   0.6822   0.01658   0.00831   0.0127   0.0566   0.9966
   6.750   0.7079   0.01696   0.00874   0.0130   0.0548   1.0000
   7.000   0.7293   0.01742   0.00920   0.0142   0.0524   1.0000
   7.250   0.7514   0.01781   0.00965   0.0153   0.0507   1.0000
   7.500   0.7734   0.01821   0.01010   0.0164   0.0484   1.0000
   7.750   0.7951   0.01866   0.01058   0.0176   0.0464   1.0000
   8.000   0.8175   0.01903   0.01102   0.0186   0.0434   1.0000
   8.250   0.8395   0.01945   0.01151   0.0197   0.0414   1.0000
   8.500   0.8619   0.01985   0.01200   0.0207   0.0390   1.0000
   8.750   0.8840   0.02027   0.01251   0.0218   0.0355   1.0000
   9.000   0.9047   0.02088   0.01303   0.0229   0.0224   1.0000
   9.250   0.9230   0.02176   0.01388   0.0242   0.0197   1.0000
   9.500   0.9417   0.02258   0.01477   0.0255   0.0188   1.0000
   9.750   0.9598   0.02346   0.01572   0.0269   0.0182   1.0000
  10.000   0.9776   0.02433   0.01669   0.0282   0.0178   1.0000
  10.250   0.9948   0.02524   0.01773   0.0296   0.0174   1.0000
  10.500   1.0110   0.02622   0.01884   0.0311   0.0171   1.0000
  10.750   1.0263   0.02726   0.02000   0.0326   0.0169   1.0000
  11.000   1.0400   0.02838   0.02126   0.0341   0.0167   1.0000
  11.250   1.0519   0.02962   0.02264   0.0358   0.0165   1.0000
  11.500   1.0616   0.03097   0.02414   0.0376   0.0163   1.0000
  11.750   1.0697   0.03235   0.02566   0.0394   0.0163   1.0000
  12.000   1.0721   0.03402   0.02748   0.0416   0.0161   1.0000
  12.250   1.0697   0.03571   0.02931   0.0442   0.0161   1.0000
  12.500   1.0618   0.03796   0.03172   0.0464   0.0160   1.0000
  12.750   1.0502   0.04101   0.03494   0.0469   0.0160   1.0000
  13.000   1.0241   0.04782   0.04203   0.0420   0.0161   1.0000
  13.250   0.9765   0.06134   0.05586   0.0309   0.0163   1.0000
  13.500   0.9267   0.07312   0.06783   0.0235   0.0166   1.0000
  13.750   0.8842   0.08401   0.07886   0.0172   0.0168   1.0000
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