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BOEING 707 .08 SPAN AIRFOIL (b707a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: BOEING 707 .08 SPAN AIRFOIL (b707a-il)
Reynolds number: 100,000
Max Cl/Cd: 32.18 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-b707a-il-100000-n5.txt
Download as CSV file: xf-b707a-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.7996   0.10558   0.09960  -0.0053   1.0000   0.0277
 -13.500  -0.8408   0.09306   0.08691  -0.0131   1.0000   0.0273
 -13.250  -0.8778   0.08303   0.07668  -0.0193   1.0000   0.0270
 -13.000  -0.9076   0.07510   0.06852  -0.0238   1.0000   0.0268
 -12.750  -0.9328   0.06844   0.06162  -0.0271   1.0000   0.0267
 -12.500  -0.9525   0.06301   0.05594  -0.0292   1.0000   0.0267
 -12.250  -0.9677   0.05843   0.05112  -0.0303   1.0000   0.0266
 -12.000  -0.9795   0.05450   0.04694  -0.0305   1.0000   0.0267
 -11.750  -0.9874   0.05108   0.04328  -0.0301   1.0000   0.0268
 -11.500  -0.9919   0.04807   0.04003  -0.0291   1.0000   0.0270
 -11.250  -0.9921   0.04545   0.03719  -0.0277   1.0000   0.0272
 -11.000  -0.9892   0.04302   0.03452  -0.0261   1.0000   0.0275
 -10.750  -0.9826   0.04082   0.03213  -0.0244   1.0000   0.0278
 -10.500  -0.9739   0.03890   0.03004  -0.0226   1.0000   0.0282
 -10.250  -0.9663   0.03764   0.02873  -0.0206   1.0000   0.0285
 -10.000  -0.9580   0.03651   0.02754  -0.0185   1.0000   0.0290
  -9.750  -0.9471   0.03539   0.02634  -0.0166   1.0000   0.0299
  -9.500  -0.9340   0.03409   0.02493  -0.0149   1.0000   0.0308
  -9.250  -0.9202   0.03282   0.02356  -0.0132   1.0000   0.0322
  -9.000  -0.9067   0.03196   0.02266  -0.0114   1.0000   0.0332
  -8.750  -0.8920   0.03091   0.02153  -0.0097   1.0000   0.0348
  -8.500  -0.8767   0.02981   0.02036  -0.0079   1.0000   0.0365
  -8.250  -0.8616   0.02891   0.01945  -0.0061   1.0000   0.0383
  -8.000  -0.8467   0.02785   0.01831  -0.0041   1.0000   0.0411
  -7.750  -0.8316   0.02698   0.01739  -0.0022   1.0000   0.0444
  -7.500  -0.8160   0.02616   0.01651  -0.0004   1.0000   0.0487
  -7.250  -0.7999   0.02539   0.01568   0.0015   1.0000   0.0533
  -7.000  -0.7826   0.02473   0.01491   0.0033   1.0000   0.0582
  -6.750  -0.7661   0.02405   0.01423   0.0050   1.0000   0.0630
  -6.500  -0.7492   0.02337   0.01353   0.0067   1.0000   0.0678
  -6.250  -0.7308   0.02281   0.01289   0.0083   1.0000   0.0728
  -6.000  -0.7147   0.02206   0.01218   0.0101   1.0000   0.0774
  -5.750  -0.6959   0.02152   0.01156   0.0116   1.0000   0.0819
  -5.500  -0.6792   0.02078   0.01085   0.0134   1.0000   0.0860
  -5.250  -0.6602   0.02022   0.01025   0.0149   1.0000   0.0906
  -5.000  -0.6417   0.01956   0.00959   0.0164   1.0000   0.0958
  -4.750  -0.6220   0.01900   0.00901   0.0178   1.0000   0.1019
  -4.500  -0.6024   0.01837   0.00843   0.0192   1.0000   0.1088
  -4.250  -0.5818   0.01781   0.00790   0.0205   1.0000   0.1169
  -4.000  -0.5617   0.01712   0.00734   0.0218   1.0000   0.1345
  -3.750  -0.5456   0.01578   0.00653   0.0233   1.0000   0.2450
  -3.500  -0.5280   0.01527   0.00668   0.0251   1.0000   0.3834
  -3.250  -0.5046   0.01522   0.00659   0.0262   1.0000   0.4083
  -3.000  -0.4809   0.01516   0.00646   0.0273   1.0000   0.4248
  -2.750  -0.4576   0.01510   0.00640   0.0284   1.0000   0.4400
  -2.500  -0.4340   0.01501   0.00633   0.0295   1.0000   0.4503
  -2.250  -0.4001   0.01501   0.00625   0.0283   0.9937   0.4638
  -2.000  -0.3591   0.01491   0.00623   0.0258   0.9797   0.4731
  -1.750  -0.3211   0.01482   0.00609   0.0240   0.9585   0.4832
  -1.250  -0.1997   0.01466   0.00565   0.0122   0.7295   0.5085
  -1.000  -0.1687   0.01504   0.00557   0.0123   0.6079   0.5194
  -0.750  -0.1438   0.01532   0.00551   0.0132   0.5388   0.5285
  -0.500  -0.1175   0.01544   0.00550   0.0138   0.4919   0.5357
  -0.250  -0.0903   0.01553   0.00543   0.0141   0.4458   0.5410
   0.000  -0.0630   0.01565   0.00533   0.0143   0.4080   0.5450
   0.250  -0.0357   0.01577   0.00527   0.0146   0.3853   0.5486
   0.500  -0.0087   0.01589   0.00528   0.0149   0.3699   0.5525
   0.750   0.0184   0.01603   0.00535   0.0152   0.3573   0.5567
   1.000   0.0456   0.01617   0.00545   0.0155   0.3466   0.5611
   1.250   0.0726   0.01641   0.00558   0.0158   0.3366   0.5659
   1.500   0.0999   0.01653   0.00575   0.0161   0.3263   0.5708
   1.750   0.1269   0.01672   0.00597   0.0165   0.3162   0.5766
   2.000   0.1539   0.01697   0.00619   0.0168   0.3056   0.5838
   2.250   0.1809   0.01709   0.00640   0.0171   0.2927   0.5920
   2.500   0.2078   0.01714   0.00658   0.0175   0.2789   0.6024
   2.750   0.2348   0.01706   0.00674   0.0179   0.2616   0.6151
   3.000   0.2617   0.01693   0.00683   0.0184   0.2409   0.6321
   3.250   0.2874   0.01679   0.00678   0.0191   0.2265   0.6544
   3.500   0.3123   0.01675   0.00677   0.0200   0.2136   0.6846
   3.750   0.3370   0.01684   0.00696   0.0209   0.2012   0.7243
   4.000   0.3627   0.01702   0.00729   0.0216   0.1892   0.7743
   4.250   0.3955   0.01727   0.00774   0.0211   0.1775   0.8346
   4.500   0.4420   0.01767   0.00828   0.0176   0.1648   0.8991
   4.750   0.4851   0.01808   0.00875   0.0145   0.1524   0.9497
   5.000   0.5246   0.01849   0.00917   0.0121   0.1392   0.9818
   5.250   0.5605   0.01892   0.00959   0.0103   0.1270   1.0000
   5.500   0.5821   0.01934   0.01001   0.0114   0.1181   1.0000
   5.750   0.6034   0.01981   0.01046   0.0126   0.1105   1.0000
   6.000   0.6246   0.02028   0.01090   0.0137   0.1043   1.0000
   6.250   0.6462   0.02076   0.01143   0.0149   0.0975   1.0000
   6.500   0.6674   0.02125   0.01192   0.0160   0.0927   1.0000
   6.750   0.6889   0.02179   0.01254   0.0172   0.0884   1.0000
   7.000   0.7100   0.02231   0.01307   0.0183   0.0853   1.0000
   7.250   0.7314   0.02288   0.01374   0.0194   0.0818   1.0000
   7.500   0.7526   0.02342   0.01432   0.0205   0.0786   1.0000
   7.750   0.7734   0.02403   0.01498   0.0216   0.0764   1.0000
   8.000   0.7941   0.02470   0.01577   0.0228   0.0743   1.0000
   8.250   0.8145   0.02533   0.01648   0.0239   0.0719   1.0000
   8.500   0.8344   0.02601   0.01720   0.0250   0.0696   1.0000
   8.750   0.8540   0.02680   0.01815   0.0262   0.0676   1.0000
   9.000   0.8731   0.02759   0.01904   0.0273   0.0657   1.0000
   9.250   0.8913   0.02838   0.01988   0.0285   0.0633   1.0000
   9.500   0.9091   0.02934   0.02102   0.0298   0.0607   1.0000
   9.750   0.9256   0.03027   0.02204   0.0310   0.0583   1.0000
  10.000   0.9409   0.03138   0.02333   0.0323   0.0553   1.0000
  10.250   0.9545   0.03250   0.02453   0.0337   0.0522   1.0000
  10.500   0.9668   0.03387   0.02615   0.0351   0.0484   1.0000
  10.750   0.9768   0.03530   0.02776   0.0366   0.0457   1.0000
  11.000   0.9845   0.03692   0.02961   0.0382   0.0427   1.0000
  11.250   0.9880   0.03885   0.03180   0.0398   0.0397   1.0000
  11.500   0.9864   0.04085   0.03397   0.0417   0.0376   1.0000
  11.750   0.9758   0.04354   0.03688   0.0437   0.0364   1.0000
  12.000   0.9578   0.04744   0.04101   0.0437   0.0352   1.0000
  12.250   0.9250   0.05532   0.04913   0.0377   0.0362   1.0000
  12.500   0.8870   0.06624   0.06020   0.0292   0.0374   1.0000
  12.750   0.8384   0.07818   0.07233   0.0217   0.0386   1.0000
  13.000   0.7552   0.09773   0.09205   0.0104   0.0395   1.0000
  13.250   0.7204   0.10881   0.10312   0.0046   0.0378   1.0000
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