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BOEING 707 .40 SPAN AIRFOIL (b707c-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: BOEING 707 .40 SPAN AIRFOIL (b707c-il)
Reynolds number: 200,000
Max Cl/Cd: 43.24 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-b707c-il-200000.txt
Download as CSV file: xf-b707c-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3738   0.09788   0.09429  -0.0251   1.0000   0.0315
 -10.000  -0.3731   0.09422   0.09064  -0.0260   1.0000   0.0320
  -9.750  -0.4794   0.09871   0.09493  -0.0267   1.0000   0.0302
  -9.500  -0.4752   0.09537   0.09160  -0.0267   1.0000   0.0306
  -9.250  -0.4739   0.09185   0.08812  -0.0279   1.0000   0.0308
  -9.000  -0.4733   0.08835   0.08465  -0.0290   1.0000   0.0312
  -8.750  -0.4753   0.08462   0.08096  -0.0308   1.0000   0.0315
  -8.500  -0.4820   0.08056   0.07694  -0.0336   1.0000   0.0317
  -8.250  -0.4937   0.07704   0.07344  -0.0347   1.0000   0.0319
  -8.000  -0.5010   0.07370   0.07009  -0.0348   1.0000   0.0322
  -7.750  -0.5054   0.07049   0.06685  -0.0346   1.0000   0.0325
  -7.500  -0.5081   0.06744   0.06375  -0.0339   1.0000   0.0333
  -7.250  -0.5091   0.06449   0.06073  -0.0330   1.0000   0.0340
  -7.000  -0.5082   0.06174   0.05787  -0.0316   1.0000   0.0348
  -6.750  -0.5056   0.06115   0.05684  -0.0291   1.0000   0.0365
  -6.500  -0.5038   0.05998   0.05533  -0.0261   1.0000   0.0367
  -6.250  -0.4987   0.05543   0.05076  -0.0247   1.0000   0.0371
  -6.000  -0.4920   0.05111   0.04654  -0.0235   1.0000   0.0376
  -5.750  -0.4845   0.04819   0.04360  -0.0219   1.0000   0.0382
  -5.500  -0.4759   0.04573   0.04108  -0.0201   1.0000   0.0390
  -5.250  -0.4660   0.04353   0.03879  -0.0182   1.0000   0.0400
  -5.000  -0.4549   0.04146   0.03658  -0.0163   1.0000   0.0413
  -4.750  -0.4419   0.03974   0.03467  -0.0142   1.0000   0.0431
  -4.500  -0.3998   0.03772   0.03202  -0.0167   0.9943   0.0462
  -4.250  -0.3660   0.03379   0.02813  -0.0201   0.9885   0.0480
  -4.000  -0.3284   0.03153   0.02569  -0.0229   0.9828   0.0514
  -3.750  -0.2900   0.02942   0.02316  -0.0250   0.9756   0.0576
  -3.500  -0.2528   0.02735   0.02100  -0.0276   0.9686   0.0638
  -3.250  -0.2145   0.02532   0.01881  -0.0302   0.9609   0.0740
  -3.000  -0.1787   0.02361   0.01696  -0.0326   0.9516   0.0961
  -2.000  -0.0162   0.01701   0.00952  -0.0381   0.9120   0.0701
  -1.750   0.0218   0.01569   0.00809  -0.0386   0.8972   0.0525
  -1.500   0.0576   0.01467   0.00691  -0.0392   0.8793   0.0469
  -1.250   0.0907   0.01391   0.00604  -0.0394   0.8462   0.0461
  -1.000   0.1164   0.01292   0.00497  -0.0385   0.8005   0.0480
  -0.750   0.1401   0.01241   0.00433  -0.0373   0.7625   0.0532
  -0.500   0.1630   0.01200   0.00373  -0.0359   0.7356   0.0566
  -0.250   0.1854   0.01170   0.00315  -0.0345   0.7033   0.0671
   0.000   0.2053   0.01095   0.00284  -0.0329   0.6799   0.2617
   0.250   0.2102   0.00943   0.00298  -0.0281   0.6602   0.7445
   0.500   0.2308   0.00934   0.00312  -0.0253   0.6362   0.8579
   0.750   0.2616   0.00953   0.00320  -0.0251   0.6002   0.9084
   1.000   0.3074   0.00978   0.00333  -0.0282   0.5616   0.9474
   1.250   0.3501   0.01003   0.00336  -0.0310   0.5047   0.9649
   1.500   0.3977   0.01148   0.00358  -0.0357   0.2514   0.9859
   1.750   0.4500   0.01221   0.00391  -0.0414   0.2001   0.9975
   2.000   0.4733   0.01269   0.00399  -0.0412   0.0905   1.0000
   2.250   0.4880   0.01297   0.00414  -0.0391   0.0690   1.0000
   2.500   0.5045   0.01317   0.00427  -0.0372   0.0637   1.0000
   2.750   0.5218   0.01340   0.00445  -0.0354   0.0596   1.0000
   3.000   0.5405   0.01363   0.00468  -0.0337   0.0578   1.0000
   3.250   0.5598   0.01390   0.00494  -0.0322   0.0563   1.0000
   3.500   0.5799   0.01414   0.00520  -0.0308   0.0556   1.0000
   3.750   0.6005   0.01441   0.00549  -0.0295   0.0550   1.0000
   4.000   0.6212   0.01471   0.00583  -0.0283   0.0545   1.0000
   4.250   0.6418   0.01503   0.00618  -0.0270   0.0532   1.0000
   4.500   0.6623   0.01538   0.00655  -0.0257   0.0517   1.0000
   4.750   0.6824   0.01578   0.00697  -0.0244   0.0503   1.0000
   5.000   0.7014   0.01631   0.00752  -0.0229   0.0481   1.0000
   5.250   0.7180   0.01706   0.00826  -0.0211   0.0461   1.0000
   5.500   0.7383   0.01753   0.00878  -0.0198   0.0453   1.0000
   5.750   0.7578   0.01812   0.00942  -0.0184   0.0443   1.0000
   6.000   0.7773   0.01874   0.01008  -0.0171   0.0418   1.0000
   6.250   0.7946   0.01970   0.01102  -0.0155   0.0390   1.0000
   6.500   0.8125   0.02104   0.01237  -0.0139   0.0364   1.0000
   6.750   0.8332   0.02218   0.01357  -0.0127   0.0336   1.0000
   7.000   0.8549   0.02350   0.01486  -0.0119   0.0321   1.0000
   7.250   0.8804   0.02596   0.01726  -0.0119   0.0308   1.0000
   7.500   0.9025   0.02729   0.01882  -0.0109   0.0303   1.0000
   7.750   0.9249   0.02911   0.02086  -0.0100   0.0300   1.0000
   8.000   0.9460   0.03123   0.02321  -0.0089   0.0299   1.0000
   8.250   0.9657   0.03373   0.02597  -0.0078   0.0301   1.0000
   8.500   0.9844   0.03693   0.02935  -0.0069   0.0305   1.0000
   8.750   1.0024   0.03871   0.03141  -0.0053   0.0315   1.0000
  11.750   0.6529   0.10823   0.10474  -0.0023   0.0649   1.0000
  12.000   0.6382   0.11499   0.11147  -0.0062   0.0625   1.0000
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