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LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il)
Reynolds number: 100,000
Max Cl/Cd: 44.93 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-c141c-il-100000-n5.txt
Download as CSV file: xf-c141c-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL426.57 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5685   0.08936   0.08384  -0.0442   1.0000   0.0368
 -10.500  -0.5911   0.07948   0.07401  -0.0507   1.0000   0.0363
 -10.250  -0.6323   0.06883   0.06331  -0.0575   1.0000   0.0353
 -10.000  -0.6718   0.06344   0.05784  -0.0565   1.0000   0.0348
  -9.750  -0.7056   0.05979   0.05407  -0.0522   1.0000   0.0346
  -9.500  -0.7288   0.05631   0.05042  -0.0483   1.0000   0.0346
  -9.250  -0.7455   0.05308   0.04697  -0.0443   1.0000   0.0349
  -9.000  -0.7576   0.04988   0.04351  -0.0405   1.0000   0.0352
  -8.750  -0.7657   0.04666   0.03996  -0.0367   1.0000   0.0356
  -8.500  -0.7695   0.04349   0.03642  -0.0332   1.0000   0.0360
  -8.000  -0.7642   0.03770   0.02977  -0.0270   1.0000   0.0373
  -7.750  -0.7558   0.03512   0.02670  -0.0244   1.0000   0.0383
  -7.500  -0.7437   0.03313   0.02435  -0.0222   1.0000   0.0397
  -7.250  -0.7284   0.03207   0.02325  -0.0207   1.0000   0.0412
  -7.000  -0.7123   0.03087   0.02188  -0.0190   1.0000   0.0430
  -6.750  -0.6949   0.02941   0.02014  -0.0175   1.0000   0.0447
  -6.500  -0.6760   0.02795   0.01838  -0.0160   1.0000   0.0465
  -6.250  -0.6569   0.02676   0.01705  -0.0147   1.0000   0.0488
  -6.000  -0.6376   0.02600   0.01626  -0.0136   1.0000   0.0515
  -5.750  -0.6117   0.02505   0.01514  -0.0136   0.9986   0.0549
  -5.500  -0.5818   0.02404   0.01397  -0.0143   0.9962   0.0587
  -5.250  -0.5515   0.02331   0.01327  -0.0154   0.9938   0.0634
  -5.000  -0.5222   0.02257   0.01238  -0.0159   0.9908   0.0684
  -4.750  -0.4929   0.02186   0.01171  -0.0167   0.9878   0.0745
  -4.500  -0.4615   0.02129   0.01104  -0.0177   0.9850   0.0819
  -4.250  -0.4320   0.02070   0.01050  -0.0186   0.9820   0.0910
  -4.000  -0.4038   0.02015   0.00997  -0.0190   0.9781   0.1020
  -3.750  -0.3735   0.01967   0.00953  -0.0200   0.9746   0.1178
  -3.500  -0.3414   0.01921   0.00915  -0.0212   0.9718   0.1410
  -3.250  -0.3134   0.01868   0.00880  -0.0218   0.9678   0.1771
  -3.000  -0.2860   0.01805   0.00851  -0.0222   0.9635   0.2439
  -2.750  -0.2582   0.01709   0.00831  -0.0230   0.9602   0.3969
  -2.500  -0.2309   0.01629   0.00842  -0.0228   0.9575   0.6031
  -2.250  -0.2065   0.01610   0.00860  -0.0214   0.9529   0.7134
  -2.000  -0.1795   0.01611   0.00875  -0.0205   0.9482   0.7844
  -1.750  -0.1463   0.01626   0.00895  -0.0208   0.9450   0.8385
  -1.500  -0.1076   0.01649   0.00917  -0.0223   0.9426   0.8819
  -1.250  -0.0670   0.01678   0.00941  -0.0243   0.9399   0.9208
  -1.000  -0.0095   0.01719   0.00975  -0.0297   0.9401   0.9580
  -0.750   0.0451   0.01736   0.00983  -0.0353   0.9386   0.9732
  -0.500   0.0890   0.01740   0.00979  -0.0391   0.9347   0.9824
  -0.250   0.1365   0.01739   0.00974  -0.0436   0.9316   0.9892
   0.000   0.1847   0.01737   0.00968  -0.0482   0.9290   0.9957
   0.250   0.2266   0.01732   0.00962  -0.0516   0.9250   1.0000
   0.500   0.2504   0.01727   0.00956  -0.0513   0.9164   1.0000
   0.750   0.2882   0.01717   0.00946  -0.0536   0.9124   1.0000
   1.000   0.3073   0.01716   0.00946  -0.0522   0.9020   1.0000
   1.250   0.3442   0.01703   0.00936  -0.0541   0.8975   1.0000
   1.500   0.3634   0.01702   0.00937  -0.0526   0.8867   1.0000
   1.750   0.3957   0.01684   0.00923  -0.0534   0.8786   1.0000
   2.000   0.4287   0.01654   0.00899  -0.0540   0.8680   1.0000
   2.250   0.4618   0.01603   0.00853  -0.0542   0.8520   1.0000
   2.500   0.4858   0.01563   0.00816  -0.0527   0.8309   1.0000
   2.750   0.5110   0.01529   0.00786  -0.0514   0.8101   1.0000
   3.000   0.5384   0.01498   0.00759  -0.0506   0.7893   1.0000
   3.250   0.5618   0.01479   0.00743  -0.0492   0.7635   1.0000
   3.500   0.5887   0.01457   0.00722  -0.0483   0.7322   1.0000
   3.750   0.6160   0.01443   0.00701  -0.0474   0.6893   1.0000
   4.000   0.6429   0.01442   0.00681  -0.0464   0.6255   1.0000
   4.250   0.6636   0.01477   0.00674  -0.0443   0.5325   1.0000
   4.500   0.6752   0.01556   0.00692  -0.0410   0.4194   1.0000
   4.750   0.6841   0.01654   0.00732  -0.0376   0.3202   1.0000
   5.000   0.6955   0.01746   0.00781  -0.0347   0.2480   1.0000
   5.250   0.7093   0.01826   0.00832  -0.0323   0.1992   1.0000
   5.500   0.7245   0.01899   0.00888  -0.0302   0.1658   1.0000
   5.750   0.7404   0.01970   0.00945  -0.0282   0.1416   1.0000
   6.000   0.7570   0.02039   0.01006  -0.0263   0.1231   1.0000
   6.250   0.7738   0.02109   0.01071  -0.0244   0.1089   1.0000
   6.500   0.7904   0.02184   0.01143  -0.0226   0.0978   1.0000
   6.750   0.8071   0.02262   0.01216  -0.0208   0.0885   1.0000
   7.000   0.8250   0.02337   0.01296  -0.0191   0.0804   1.0000
   7.250   0.8414   0.02428   0.01381  -0.0174   0.0744   1.0000
   7.500   0.8601   0.02507   0.01473  -0.0159   0.0682   1.0000
   7.750   0.8770   0.02605   0.01566  -0.0144   0.0637   1.0000
   8.000   0.8965   0.02702   0.01676  -0.0131   0.0593   1.0000
   8.250   0.9149   0.02795   0.01773  -0.0118   0.0553   1.0000
   8.500   0.9330   0.02920   0.01896  -0.0106   0.0525   1.0000
   8.750   0.9538   0.03041   0.02039  -0.0095   0.0495   1.0000
   9.000   0.9724   0.03154   0.02163  -0.0083   0.0466   1.0000
   9.250   0.9897   0.03269   0.02279  -0.0071   0.0444   1.0000
   9.500   1.0091   0.03437   0.02459  -0.0061   0.0427   1.0000
   9.750   1.0278   0.03619   0.02674  -0.0050   0.0411   1.0000
  10.000   1.0436   0.03801   0.02881  -0.0035   0.0395   1.0000
  10.250   1.0569   0.03961   0.03060  -0.0019   0.0381   1.0000
  10.500   1.0689   0.04104   0.03213  -0.0002   0.0368   1.0000
  10.750   1.0809   0.04281   0.03394   0.0013   0.0357   1.0000
  11.000   1.0833   0.04521   0.03678   0.0043   0.0349   1.0000
  11.250   1.0819   0.04787   0.03983   0.0075   0.0343   1.0000
  11.500   1.0762   0.05072   0.04303   0.0108   0.0338   1.0000
  11.750   1.0667   0.05378   0.04643   0.0139   0.0334   1.0000
  12.000   1.0534   0.05714   0.05010   0.0167   0.0332   1.0000
  12.250   1.0364   0.06090   0.05416   0.0190   0.0330   1.0000
  12.500   1.0158   0.06523   0.05877   0.0203   0.0329   1.0000
  12.750   0.9913   0.07036   0.06418   0.0205   0.0329   1.0000
  13.000   0.9624   0.07670   0.07077   0.0188   0.0330   1.0000
  13.250   0.9282   0.08502   0.07932   0.0147   0.0333   1.0000
  13.500   0.8849   0.09738   0.09187   0.0064   0.0338   1.0000
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