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PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il)
Reynolds number: 50,000
Max Cl/Cd: 33.04 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-pfcm-il-50000-n5.txt
Download as CSV file: xf-pfcm-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5700   0.12866   0.12155   0.0014   1.0000   0.1063
 -10.250  -0.5779   0.12594   0.11891  -0.0025   1.0000   0.1112
 -10.000  -0.5897   0.12318   0.11627  -0.0076   1.0000   0.1122
  -9.750  -0.5672   0.11723   0.11027  -0.0041   1.0000   0.1153
  -9.500  -0.5618   0.11331   0.10638  -0.0049   1.0000   0.1180
  -9.250  -0.5605   0.10950   0.10261  -0.0066   1.0000   0.1210
  -9.000  -0.5765   0.10618   0.09946  -0.0124   1.0000   0.1267
  -8.500  -0.5618   0.09010   0.08330  -0.0223   1.0000   0.0551
  -8.250  -0.5606   0.08547   0.07872  -0.0246   1.0000   0.0529
  -8.000  -0.5609   0.08025   0.07351  -0.0284   1.0000   0.0509
  -7.750  -0.5617   0.07480   0.06801  -0.0322   1.0000   0.0487
  -7.250  -0.5596   0.06381   0.05637  -0.0387   1.0000   0.0436
  -7.000  -0.5509   0.05949   0.05189  -0.0391   1.0000   0.0431
  -6.750  -0.5409   0.05527   0.04742  -0.0395   1.0000   0.0427
  -6.500  -0.5292   0.05121   0.04299  -0.0396   1.0000   0.0427
  -6.250  -0.5147   0.04767   0.03888  -0.0394   1.0000   0.0438
  -6.000  -0.5007   0.04392   0.03497  -0.0392   1.0000   0.0459
  -5.750  -0.4833   0.04090   0.03165  -0.0387   1.0000   0.0474
  -5.500  -0.4639   0.03775   0.02802  -0.0379   1.0000   0.0474
  -5.250  -0.4430   0.03494   0.02469  -0.0370   1.0000   0.0479
  -5.000  -0.4210   0.03246   0.02180  -0.0360   1.0000   0.0487
  -4.750  -0.3981   0.03027   0.01924  -0.0350   1.0000   0.0500
  -4.500  -0.3748   0.02843   0.01708  -0.0339   1.0000   0.0528
  -4.250  -0.3512   0.02698   0.01527  -0.0327   1.0000   0.0578
  -4.000  -0.3290   0.02537   0.01366  -0.0316   1.0000   0.0622
  -3.750  -0.3065   0.02409   0.01221  -0.0302   1.0000   0.0663
  -3.500  -0.2842   0.02295   0.01081  -0.0289   1.0000   0.0718
  -3.250  -0.2622   0.02190   0.00973  -0.0282   1.0000   0.0864
  -3.000  -0.2399   0.02076   0.00860  -0.0275   1.0000   0.1067
  -2.750  -0.2171   0.01835   0.00735  -0.0280   1.0000   0.2775
  -2.500  -0.2114   0.01684   0.00768  -0.0220   1.0000   0.7101
  -2.250  -0.1409   0.01664   0.00765  -0.0240   1.0000   0.9866
  -2.000  -0.1192   0.01640   0.00712  -0.0244   1.0000   1.0000
  -1.750  -0.1124   0.01625   0.00675  -0.0219   1.0000   1.0000
  -1.500  -0.0980   0.01622   0.00647  -0.0206   1.0000   1.0000
  -1.250  -0.0800   0.01626   0.00626  -0.0198   1.0000   1.0000
  -1.000  -0.0602   0.01636   0.00611  -0.0193   1.0000   1.0000
  -0.750  -0.0395   0.01651   0.00605  -0.0189   1.0000   1.0000
  -0.500  -0.0183   0.01670   0.00607  -0.0186   1.0000   1.0000
  -0.250   0.0031   0.01693   0.00615  -0.0184   1.0000   1.0000
   0.000   0.0389   0.01722   0.00628  -0.0209   0.9932   1.0000
   0.250   0.0785   0.01753   0.00648  -0.0242   0.9842   1.0000
   0.500   0.1179   0.01784   0.00672  -0.0273   0.9752   1.0000
   0.750   0.1564   0.01814   0.00699  -0.0302   0.9658   1.0000
   1.000   0.1929   0.01844   0.00728  -0.0327   0.9554   1.0000
   1.250   0.2293   0.01874   0.00760  -0.0350   0.9454   1.0000
   1.500   0.2679   0.01905   0.00797  -0.0377   0.9362   1.0000
   1.750   0.3049   0.01935   0.00839  -0.0401   0.9264   1.0000
   2.000   0.3394   0.01965   0.00881  -0.0419   0.9156   1.0000
   2.250   0.3742   0.01996   0.00926  -0.0437   0.9050   1.0000
   2.500   0.4098   0.02025   0.00978  -0.0456   0.8950   1.0000
   2.750   0.4444   0.02052   0.01027  -0.0471   0.8842   1.0000
   3.000   0.4757   0.02081   0.01079  -0.0479   0.8715   1.0000
   3.250   0.5074   0.02105   0.01130  -0.0486   0.8579   1.0000
   3.500   0.5401   0.02119   0.01182  -0.0491   0.8428   1.0000
   3.750   0.5728   0.02082   0.01178  -0.0481   0.8149   1.0000
   4.000   0.5984   0.01908   0.01008  -0.0416   0.7259   1.0000
   4.250   0.6156   0.01863   0.00928  -0.0360   0.5894   1.0000
   4.500   0.6203   0.02059   0.00935  -0.0306   0.2484   1.0000
   4.750   0.6317   0.02349   0.01115  -0.0292   0.1111   1.0000
   5.000   0.6505   0.02521   0.01277  -0.0279   0.0893   1.0000
   5.250   0.6707   0.02671   0.01434  -0.0267   0.0757   1.0000
   5.500   0.6919   0.02824   0.01589  -0.0258   0.0651   1.0000
   5.750   0.7177   0.02981   0.01774  -0.0247   0.0604   1.0000
   6.000   0.7458   0.03170   0.01982  -0.0240   0.0566   1.0000
   6.250   0.7733   0.03397   0.02225  -0.0235   0.0530   1.0000
   6.500   0.7991   0.03633   0.02501  -0.0228   0.0485   1.0000
   6.750   0.8235   0.03898   0.02812  -0.0220   0.0456   1.0000
   7.000   0.8456   0.04209   0.03171  -0.0209   0.0443   1.0000
   7.250   0.8643   0.04549   0.03560  -0.0197   0.0435   1.0000
   7.500   0.8797   0.04913   0.03973  -0.0184   0.0429   1.0000
   7.750   0.8927   0.05252   0.04345  -0.0172   0.0413   1.0000
   8.250   0.9056   0.06049   0.05214  -0.0147   0.0383   1.0000
   8.500   0.9064   0.06464   0.05674  -0.0133   0.0378   1.0000
   8.750   0.9045   0.06898   0.06142  -0.0121   0.0378   1.0000
   9.000   0.8993   0.07336   0.06607  -0.0112   0.0379   1.0000
   9.250   0.8911   0.07775   0.07066  -0.0106   0.0381   1.0000
   9.500   0.8794   0.08197   0.07504  -0.0101   0.0383   1.0000
   9.750   0.8662   0.08639   0.07955  -0.0104   0.0385   1.0000
  10.000   0.8537   0.09125   0.08448  -0.0117   0.0388   1.0000
  10.250   0.8434   0.09650   0.08977  -0.0138   0.0391   1.0000
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