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BOEING 707 .99 SPAN AIRFOIL (b707e-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: BOEING 707 .99 SPAN AIRFOIL (b707e-il)
Reynolds number: 200,000
Max Cl/Cd: 67.69 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-b707e-il-200000.txt
Download as CSV file: xf-b707e-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING 707 .99 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4570   0.08637   0.08291  -0.0329   1.0000   0.0340
  -8.250  -0.4664   0.08242   0.07901  -0.0370   1.0000   0.0343
  -8.000  -0.4758   0.07934   0.07591  -0.0384   1.0000   0.0347
  -7.750  -0.4816   0.07677   0.07324  -0.0394   1.0000   0.0351
  -7.500  -0.4839   0.07427   0.07063  -0.0391   1.0000   0.0353
  -7.250  -0.4840   0.07182   0.06804  -0.0380   1.0000   0.0354
  -7.000  -0.4829   0.06926   0.06534  -0.0366   1.0000   0.0355
  -6.750  -0.4890   0.06100   0.05725  -0.0360   1.0000   0.0368
  -6.500  -0.4857   0.05800   0.05432  -0.0343   1.0000   0.0379
  -6.250  -0.4847   0.05563   0.05195  -0.0321   1.0000   0.0392
  -6.000  -0.4888   0.05375   0.05003  -0.0288   1.0000   0.0402
  -5.750  -0.4938   0.05200   0.04822  -0.0253   0.9998   0.0412
  -5.500  -0.4606   0.04819   0.04409  -0.0292   0.9947   0.0450
  -5.250  -0.4174   0.04905   0.04409  -0.0315   0.9872   0.0485
  -5.000  -0.3972   0.04043   0.03561  -0.0351   0.9834   0.0511
  -4.750  -0.3699   0.03751   0.03258  -0.0369   0.9770   0.0544
  -4.500  -0.3313   0.03720   0.03147  -0.0384   0.9711   0.0627
  -4.250  -0.3066   0.03223   0.02670  -0.0407   0.9663   0.0669
  -4.000  -0.2756   0.03051   0.02455  -0.0418   0.9598   0.0783
  -3.750  -0.2409   0.02828   0.02226  -0.0442   0.9564   0.0863
  -3.500  -0.2133   0.02627   0.02008  -0.0451   0.9494   0.0986
  -2.250  -0.0256   0.01889   0.01113  -0.0502   0.9283   0.0624
  -2.000   0.0046   0.01700   0.00923  -0.0506   0.9216   0.0596
  -1.750   0.0391   0.01568   0.00785  -0.0514   0.9169   0.0538
  -1.500   0.0734   0.01501   0.00707  -0.0523   0.9121   0.0500
  -1.250   0.1022   0.01465   0.00670  -0.0523   0.9045   0.0487
  -1.000   0.1336   0.01377   0.00584  -0.0529   0.8998   0.0480
  -0.750   0.1570   0.01327   0.00535  -0.0520   0.8912   0.0479
  -0.500   0.1866   0.01277   0.00482  -0.0523   0.8859   0.0483
  -0.250   0.2101   0.01247   0.00445  -0.0514   0.8774   0.0499
   0.000   0.2396   0.01218   0.00406  -0.0515   0.8717   0.0560
   0.250   0.2592   0.01140   0.00388  -0.0501   0.8621   0.2835
   0.500   0.3602   0.00958   0.00421  -0.0625   0.8587   0.9846
   0.750   0.4180   0.00939   0.00380  -0.0679   0.8321   1.0000
   1.000   0.4329   0.00933   0.00360  -0.0651   0.8089   1.0000
   1.250   0.4504   0.00930   0.00343  -0.0628   0.7889   1.0000
   1.500   0.4691   0.00929   0.00333  -0.0608   0.7722   1.0000
   1.750   0.4885   0.00928   0.00329  -0.0591   0.7560   1.0000
   2.000   0.5089   0.00927   0.00324  -0.0575   0.7404   1.0000
   2.250   0.5298   0.00927   0.00321  -0.0560   0.7243   1.0000
   2.500   0.5514   0.00928   0.00320  -0.0547   0.7082   1.0000
   2.750   0.5734   0.00932   0.00324  -0.0534   0.6925   1.0000
   3.000   0.5951   0.00936   0.00325  -0.0520   0.6722   1.0000
   3.250   0.6159   0.00943   0.00324  -0.0503   0.6428   1.0000
   3.500   0.6370   0.00955   0.00330  -0.0489   0.6133   1.0000
   3.750   0.6578   0.00973   0.00338  -0.0473   0.5772   1.0000
   4.000   0.6769   0.01000   0.00351  -0.0454   0.5185   1.0000
   4.250   0.6903   0.01063   0.00368  -0.0426   0.4235   1.0000
   4.500   0.7033   0.01145   0.00406  -0.0400   0.3358   1.0000
   4.750   0.7192   0.01215   0.00447  -0.0379   0.2759   1.0000
   5.000   0.7367   0.01278   0.00490  -0.0362   0.2291   1.0000
   5.250   0.7531   0.01353   0.00533  -0.0344   0.1662   1.0000
   5.500   0.7667   0.01458   0.00593  -0.0322   0.0863   1.0000
   5.750   0.7859   0.01519   0.00648  -0.0308   0.0690   1.0000
   6.000   0.8058   0.01574   0.00702  -0.0295   0.0592   1.0000
   6.250   0.8251   0.01637   0.00764  -0.0281   0.0513   1.0000
   6.500   0.8439   0.01706   0.00843  -0.0265   0.0464   1.0000
   6.750   0.8577   0.01824   0.00973  -0.0242   0.0391   1.0000
   7.000   0.8624   0.02059   0.01212  -0.0205   0.0323   1.0000
   7.250   0.8811   0.02168   0.01331  -0.0188   0.0291   1.0000
   7.500   0.8990   0.02290   0.01454  -0.0174   0.0251   1.0000
   7.750   0.9193   0.02549   0.01706  -0.0166   0.0228   1.0000
   8.000   0.9413   0.02678   0.01857  -0.0154   0.0218   1.0000
   8.250   0.9634   0.02867   0.02069  -0.0143   0.0209   1.0000
   8.500   0.9840   0.03094   0.02324  -0.0131   0.0207   1.0000
   8.750   1.0016   0.03364   0.02632  -0.0114   0.0207   1.0000
   9.000   1.0154   0.03666   0.02970  -0.0095   0.0210   1.0000
   9.250   1.0252   0.04009   0.03349  -0.0072   0.0215   1.0000
   9.500   1.0304   0.04437   0.03810  -0.0049   0.0223   1.0000
   9.750   0.9734   0.03886   0.03376   0.0040   0.0278   1.0000
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