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PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70.92 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-pfcm-il-1000000-n5.txt
Download as CSV file: xf-pfcm-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6031   0.12609   0.12445   0.0104   1.0000   0.0033
 -10.750  -0.6011   0.11670   0.11508   0.0065   1.0000   0.0032
  -8.750  -0.7693   0.02111   0.01752  -0.0391   1.0000   0.0036
  -8.500  -0.7496   0.01905   0.01515  -0.0384   1.0000   0.0038
  -8.250  -0.7286   0.01749   0.01332  -0.0378   1.0000   0.0040
  -8.000  -0.7069   0.01627   0.01191  -0.0371   1.0000   0.0042
  -7.750  -0.6792   0.01519   0.01064  -0.0377   0.9977   0.0044
  -7.500  -0.6495   0.01411   0.00938  -0.0386   0.9946   0.0046
  -7.250  -0.6200   0.01343   0.00862  -0.0395   0.9903   0.0050
  -7.000  -0.5887   0.01315   0.00831  -0.0406   0.9864   0.0053
  -6.750  -0.5589   0.01286   0.00799  -0.0413   0.9809   0.0058
  -6.500  -0.5285   0.01258   0.00765  -0.0421   0.9756   0.0064
  -6.250  -0.5001   0.01218   0.00717  -0.0425   0.9684   0.0070
  -6.000  -0.4723   0.01177   0.00669  -0.0427   0.9611   0.0073
  -5.750  -0.4454   0.01141   0.00625  -0.0426   0.9527   0.0075
  -5.500  -0.4208   0.01040   0.00510  -0.0422   0.9434   0.0084
  -5.250  -0.3947   0.01003   0.00467  -0.0419   0.9347   0.0090
  -5.000  -0.3683   0.00983   0.00442  -0.0417   0.9257   0.0097
  -4.750  -0.3417   0.00957   0.00411  -0.0416   0.9167   0.0104
  -4.500  -0.3152   0.00924   0.00370  -0.0414   0.9082   0.0108
  -4.250  -0.2885   0.00891   0.00329  -0.0412   0.8992   0.0112
  -4.000  -0.2614   0.00861   0.00292  -0.0411   0.8905   0.0115
  -3.750  -0.2342   0.00840   0.00263  -0.0410   0.8820   0.0119
  -3.500  -0.2068   0.00817   0.00233  -0.0410   0.8730   0.0122
  -3.250  -0.1792   0.00795   0.00204  -0.0410   0.8645   0.0126
  -3.000  -0.1516   0.00771   0.00171  -0.0409   0.8555   0.0151
  -2.750  -0.1238   0.00755   0.00154  -0.0410   0.8459   0.0185
  -2.500  -0.0959   0.00742   0.00138  -0.0410   0.8364   0.0254
  -2.250  -0.0681   0.00729   0.00126  -0.0411   0.8259   0.0367
  -2.000  -0.0402   0.00715   0.00114  -0.0412   0.8150   0.0564
  -1.750  -0.0124   0.00695   0.00103  -0.0413   0.8034   0.0941
  -1.500   0.0147   0.00639   0.00088  -0.0416   0.7918   0.2347
  -1.250   0.0409   0.00557   0.00074  -0.0419   0.7804   0.4585
  -1.000   0.0687   0.00541   0.00070  -0.0420   0.7696   0.5148
  -0.500   0.1237   0.00504   0.00072  -0.0421   0.7483   0.6586
  -0.250   0.1518   0.00501   0.00072  -0.0422   0.7387   0.6855
   0.000   0.1798   0.00499   0.00073  -0.0423   0.7288   0.7049
   0.250   0.2081   0.00500   0.00075  -0.0424   0.7185   0.7181
   0.750   0.2644   0.00506   0.00078  -0.0426   0.6923   0.7392
   1.000   0.2922   0.00513   0.00081  -0.0426   0.6707   0.7497
   1.250   0.3198   0.00522   0.00085  -0.0427   0.6454   0.7608
   1.500   0.3469   0.00539   0.00089  -0.0426   0.6015   0.7720
   1.750   0.3724   0.00581   0.00098  -0.0423   0.5086   0.7838
   2.000   0.3958   0.00666   0.00120  -0.0420   0.3395   0.7971
   2.500   0.4463   0.00758   0.00162  -0.0415   0.1676   0.8324
   2.750   0.4707   0.00792   0.00183  -0.0410   0.1017   0.8662
   3.000   0.4929   0.00807   0.00202  -0.0398   0.0647   0.9301
   3.250   0.5260   0.00830   0.00221  -0.0411   0.0393   0.9970
   3.500   0.5533   0.00855   0.00240  -0.0412   0.0260   1.0000
   3.750   0.5803   0.00880   0.00260  -0.0411   0.0184   1.0000
   4.000   0.6075   0.00901   0.00283  -0.0411   0.0166   1.0000
   4.250   0.6345   0.00924   0.00307  -0.0411   0.0156   1.0000
   4.500   0.6614   0.00949   0.00336  -0.0410   0.0146   1.0000
   4.750   0.6881   0.00977   0.00365  -0.0410   0.0137   1.0000
   5.000   0.7146   0.01008   0.00397  -0.0408   0.0125   1.0000
   5.250   0.7402   0.01057   0.00453  -0.0405   0.0110   1.0000
   5.500   0.7658   0.01102   0.00504  -0.0402   0.0104   1.0000
   5.750   0.7923   0.01127   0.00533  -0.0402   0.0100   1.0000
   6.000   0.8185   0.01156   0.00564  -0.0401   0.0094   1.0000
   6.250   0.8443   0.01192   0.00604  -0.0399   0.0088   1.0000
   6.500   0.8700   0.01228   0.00643  -0.0397   0.0081   1.0000
   6.750   0.8957   0.01263   0.00680  -0.0395   0.0075   1.0000
   7.000   0.9206   0.01309   0.00728  -0.0392   0.0068   1.0000
   7.250   0.9446   0.01373   0.00801  -0.0387   0.0063   1.0000
   7.500   0.9700   0.01406   0.00839  -0.0385   0.0059   1.0000
   7.750   0.9951   0.01445   0.00882  -0.0383   0.0054   1.0000
   8.000   1.0197   0.01490   0.00932  -0.0379   0.0049   1.0000
   8.250   1.0444   0.01532   0.00977  -0.0376   0.0045   1.0000
   8.500   1.0684   0.01583   0.01031  -0.0373   0.0042   1.0000
   8.750   1.0896   0.01687   0.01146  -0.0364   0.0037   1.0000
   9.000   1.1123   0.01757   0.01228  -0.0358   0.0036   1.0000
   9.250   1.1345   0.01836   0.01320  -0.0352   0.0035   1.0000
   9.500   1.1561   0.01922   0.01419  -0.0344   0.0033   1.0000
   9.750   1.1771   0.02015   0.01525  -0.0337   0.0031   1.0000
  10.000   1.1975   0.02113   0.01637  -0.0328   0.0030   1.0000
  10.250   1.2174   0.02215   0.01752  -0.0320   0.0028   1.0000
  10.500   1.2370   0.02315   0.01865  -0.0311   0.0027   1.0000
  10.750   1.2563   0.02410   0.01973  -0.0302   0.0025   1.0000
  11.000   1.2750   0.02510   0.02083  -0.0293   0.0024   1.0000
  11.250   1.2915   0.02636   0.02224  -0.0282   0.0022   1.0000
  11.500   1.3031   0.02826   0.02437  -0.0265   0.0021   1.0000
  11.750   1.3025   0.03169   0.02822  -0.0236   0.0019   1.0000
  12.000   1.3051   0.03432   0.03113  -0.0211   0.0019   1.0000
  12.250   1.3033   0.03684   0.03388  -0.0182   0.0019   1.0000
  12.500   1.2919   0.03995   0.03725  -0.0147   0.0019   1.0000
  12.750   1.2736   0.04397   0.04155  -0.0118   0.0019   1.0000
  13.000   1.2478   0.04929   0.04715  -0.0102   0.0019   1.0000
  13.250   1.2120   0.05680   0.05494  -0.0109   0.0019   1.0000
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