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PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il)
Reynolds number: 100,000
Max Cl/Cd: 44.94 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-pfcm-il-100000-n5.txt
Download as CSV file: xf-pfcm-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: PROPFAN CRUISE MISSILE WING 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5598   0.09028   0.08540  -0.0167   1.0000   0.0294
  -8.500  -0.5601   0.08565   0.08082  -0.0192   1.0000   0.0282
  -8.250  -0.5625   0.08047   0.07569  -0.0234   1.0000   0.0273
  -8.000  -0.5643   0.07453   0.06975  -0.0292   1.0000   0.0264
  -7.750  -0.5643   0.06880   0.06395  -0.0333   1.0000   0.0255
  -7.500  -0.5627   0.06311   0.05812  -0.0365   1.0000   0.0245
  -7.250  -0.5589   0.05741   0.05220  -0.0386   1.0000   0.0236
  -7.000  -0.5520   0.05204   0.04653  -0.0397   1.0000   0.0230
  -6.750  -0.5410   0.04845   0.04271  -0.0400   1.0000   0.0240
  -6.500  -0.5281   0.04503   0.03901  -0.0399   1.0000   0.0256
  -6.250  -0.5141   0.04130   0.03491  -0.0394   1.0000   0.0266
  -6.000  -0.4987   0.03755   0.03073  -0.0386   1.0000   0.0265
  -5.750  -0.4815   0.03411   0.02684  -0.0375   1.0000   0.0265
  -5.500  -0.4626   0.03108   0.02333  -0.0364   1.0000   0.0267
  -5.250  -0.4423   0.02844   0.02023  -0.0352   1.0000   0.0272
  -5.000  -0.4208   0.02647   0.01778  -0.0340   1.0000   0.0292
  -4.750  -0.3985   0.02511   0.01599  -0.0328   1.0000   0.0312
  -4.500  -0.3761   0.02330   0.01391  -0.0317   1.0000   0.0317
  -4.250  -0.3539   0.02130   0.01175  -0.0307   1.0000   0.0327
  -4.000  -0.3318   0.01991   0.01030  -0.0298   1.0000   0.0342
  -3.750  -0.3097   0.01885   0.00919  -0.0289   1.0000   0.0362
  -3.500  -0.2876   0.01799   0.00823  -0.0280   1.0000   0.0393
  -3.250  -0.2652   0.01733   0.00747  -0.0272   1.0000   0.0450
  -3.000  -0.2424   0.01657   0.00668  -0.0266   1.0000   0.0515
  -2.750  -0.2166   0.01590   0.00593  -0.0265   0.9992   0.0623
  -2.500  -0.1812   0.01463   0.00519  -0.0289   0.9949   0.1634
  -2.250  -0.1547   0.01268   0.00514  -0.0294   0.9908   0.6248
  -2.000  -0.1274   0.01240   0.00528  -0.0283   0.9847   0.7680
  -1.750  -0.1041   0.01217   0.00533  -0.0255   0.9781   0.8724
  -1.500  -0.0654   0.01211   0.00517  -0.0274   0.9726   0.9164
  -1.250  -0.0197   0.01208   0.00496  -0.0313   0.9676   0.9461
  -1.000   0.0281   0.01204   0.00477  -0.0359   0.9627   0.9775
  -0.750   0.0709   0.01200   0.00460  -0.0396   0.9555   1.0000
  -0.500   0.1061   0.01201   0.00447  -0.0417   0.9467   1.0000
  -0.250   0.1425   0.01201   0.00439  -0.0438   0.9391   1.0000
   0.000   0.1745   0.01204   0.00435  -0.0450   0.9289   1.0000
   0.250   0.2069   0.01208   0.00434  -0.0462   0.9196   1.0000
   0.500   0.2409   0.01210   0.00433  -0.0476   0.9114   1.0000
   0.750   0.2702   0.01216   0.00438  -0.0481   0.9004   1.0000
   1.000   0.3000   0.01223   0.00445  -0.0486   0.8900   1.0000
   1.250   0.3301   0.01229   0.00455  -0.0491   0.8804   1.0000
   1.500   0.3596   0.01235   0.00464  -0.0494   0.8705   1.0000
   1.750   0.3871   0.01245   0.00480  -0.0494   0.8591   1.0000
   2.000   0.4148   0.01255   0.00497  -0.0493   0.8478   1.0000
   2.250   0.4425   0.01264   0.00518  -0.0492   0.8367   1.0000
   2.500   0.4700   0.01273   0.00537  -0.0489   0.8249   1.0000
   2.750   0.4965   0.01280   0.00556  -0.0484   0.8102   1.0000
   3.000   0.5218   0.01274   0.00556  -0.0471   0.7867   1.0000
   3.250   0.5432   0.01256   0.00534  -0.0442   0.7338   1.0000
   3.500   0.5632   0.01260   0.00511  -0.0413   0.6509   1.0000
   3.750   0.5838   0.01299   0.00514  -0.0391   0.5471   1.0000
   4.000   0.5940   0.01496   0.00553  -0.0362   0.2461   1.0000
   4.250   0.6099   0.01694   0.00655  -0.0349   0.0854   1.0000
   4.500   0.6317   0.01801   0.00754  -0.0341   0.0573   1.0000
   4.750   0.6537   0.01903   0.00862  -0.0331   0.0488   1.0000
   5.000   0.6757   0.02003   0.00974  -0.0321   0.0438   1.0000
   5.250   0.6965   0.02129   0.01104  -0.0310   0.0405   1.0000
   5.500   0.7185   0.02257   0.01241  -0.0300   0.0368   1.0000
   5.750   0.7420   0.02380   0.01378  -0.0293   0.0333   1.0000
   6.250   0.7901   0.02725   0.01753  -0.0278   0.0299   1.0000
   6.500   0.8138   0.02972   0.02016  -0.0272   0.0284   1.0000
   6.750   0.8367   0.03196   0.02280  -0.0263   0.0262   1.0000
   7.000   0.8585   0.03448   0.02581  -0.0251   0.0246   1.0000
   7.250   0.8775   0.03768   0.02953  -0.0237   0.0239   1.0000
   7.500   0.8932   0.04127   0.03365  -0.0220   0.0234   1.0000
   7.750   0.9054   0.04512   0.03801  -0.0202   0.0230   1.0000
   8.000   0.9150   0.04872   0.04206  -0.0186   0.0218   1.0000
   8.250   0.9232   0.05180   0.04546  -0.0172   0.0204   1.0000
   8.500   0.9304   0.05453   0.04845  -0.0161   0.0193   1.0000
   8.750   0.9309   0.05847   0.05270  -0.0146   0.0190   1.0000
   9.000   0.9262   0.06289   0.05744  -0.0130   0.0190   1.0000
   9.250   0.9149   0.06769   0.06254  -0.0116   0.0191   1.0000
   9.500   0.8965   0.07247   0.06754  -0.0104   0.0194   1.0000
   9.750   0.8756   0.07794   0.07318  -0.0113   0.0198   1.0000
  10.000   0.8547   0.08470   0.08001  -0.0149   0.0202   1.0000
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