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PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il)
Reynolds number: 100,000
Max Cl/Cd: 46.95 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-pfcm-il-100000.txt
Download as CSV file: xf-pfcm-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5628   0.09756   0.09275  -0.0114   1.0000   0.0892
  -8.500  -0.5758   0.09306   0.08836  -0.0196   1.0000   0.0913
  -8.250  -0.5911   0.08792   0.08314  -0.0306   1.0000   0.0920
  -8.000  -0.5659   0.08463   0.07999  -0.0195   1.0000   0.0971
  -7.750  -0.5646   0.07998   0.07535  -0.0242   1.0000   0.1017
  -7.500  -0.5840   0.07551   0.07044  -0.0369   1.0000   0.1058
  -7.250  -0.5181   0.05869   0.05419  -0.0368   1.0000   0.1202
  -7.000  -0.5658   0.06621   0.06112  -0.0377   1.0000   0.1202
  -6.750  -0.5479   0.06252   0.05771  -0.0343   1.0000   0.1273
  -6.500  -0.5401   0.05890   0.05398  -0.0350   1.0000   0.1404
  -6.000  -0.5233   0.05227   0.04716  -0.0356   1.0000   0.1776
  -5.750  -0.5108   0.04945   0.04437  -0.0341   1.0000   0.1955
  -5.500  -0.5006   0.04679   0.04170  -0.0327   1.0000   0.2220
  -5.250  -0.4895   0.04450   0.03946  -0.0306   1.0000   0.2526
  -5.000  -0.4449   0.03678   0.02957  -0.0366   1.0000   0.1332
  -4.750  -0.4128   0.02952   0.02147  -0.0348   1.0000   0.0729
  -4.500  -0.3876   0.02731   0.01842  -0.0329   1.0000   0.0658
  -4.250  -0.3662   0.02472   0.01576  -0.0322   1.0000   0.0691
  -4.000  -0.3421   0.02285   0.01354  -0.0310   1.0000   0.0687
  -3.750  -0.3176   0.02116   0.01162  -0.0298   1.0000   0.0689
  -3.500  -0.2935   0.01973   0.01011  -0.0288   1.0000   0.0711
  -3.250  -0.2697   0.01857   0.00889  -0.0278   1.0000   0.0756
  -3.000  -0.2467   0.01740   0.00783  -0.0271   1.0000   0.0862
  -2.750  -0.2232   0.01632   0.00680  -0.0263   1.0000   0.0992
  -2.500  -0.1965   0.01334   0.00549  -0.0272   1.0000   0.3930
  -2.250  -0.1926   0.01233   0.00595  -0.0195   1.0000   0.8072
  -2.000  -0.1799   0.01220   0.00597  -0.0143   1.0000   0.9039
  -1.750  -0.1175   0.01223   0.00575  -0.0205   1.0000   1.0000
  -1.500  -0.1063   0.01217   0.00549  -0.0191   1.0000   1.0000
  -1.250  -0.0860   0.01224   0.00533  -0.0190   1.0000   1.0000
  -1.000  -0.0637   0.01239   0.00530  -0.0191   1.0000   1.0000
  -0.750  -0.0410   0.01259   0.00534  -0.0193   1.0000   1.0000
  -0.500  -0.0182   0.01284   0.00546  -0.0194   1.0000   1.0000
  -0.250   0.0045   0.01312   0.00563  -0.0195   1.0000   1.0000
   0.000   0.0271   0.01345   0.00585  -0.0197   1.0000   1.0000
   0.250   0.0506   0.01382   0.00615  -0.0201   0.9996   1.0000
   0.500   0.0965   0.01422   0.00648  -0.0247   0.9915   1.0000
   0.750   0.1427   0.01462   0.00686  -0.0293   0.9836   1.0000
   1.000   0.1848   0.01497   0.00720  -0.0330   0.9740   1.0000
   1.250   0.2282   0.01532   0.00758  -0.0369   0.9652   1.0000
   1.500   0.2727   0.01564   0.00795  -0.0409   0.9565   1.0000
   1.750   0.3111   0.01594   0.00834  -0.0436   0.9456   1.0000
   2.000   0.3513   0.01622   0.00873  -0.0466   0.9355   1.0000
   2.250   0.3998   0.01638   0.00905  -0.0510   0.9275   1.0000
   2.500   0.4388   0.01655   0.00941  -0.0534   0.9154   1.0000
   2.750   0.4784   0.01660   0.00965  -0.0556   0.9024   1.0000
   3.000   0.5248   0.01610   0.00940  -0.0576   0.8855   1.0000
   3.250   0.5586   0.01455   0.00803  -0.0539   0.8442   1.0000
   3.500   0.5782   0.01365   0.00719  -0.0488   0.7975   1.0000
   3.750   0.5979   0.01311   0.00666  -0.0446   0.7420   1.0000
   4.000   0.6113   0.01302   0.00608  -0.0387   0.5849   1.0000
   4.250   0.6064   0.01726   0.00732  -0.0331   0.1142   1.0000
   4.500   0.6259   0.01879   0.00873  -0.0315   0.0889   1.0000
   4.750   0.6469   0.02032   0.01022  -0.0300   0.0794   1.0000
   5.000   0.6700   0.02207   0.01188  -0.0291   0.0710   1.0000
   5.250   0.6964   0.02361   0.01352  -0.0284   0.0656   1.0000
   5.500   0.7239   0.02562   0.01562  -0.0278   0.0630   1.0000
   5.750   0.7518   0.02804   0.01822  -0.0271   0.0622   1.0000
   6.000   0.7778   0.03111   0.02150  -0.0266   0.0607   1.0000
   6.250   0.8009   0.03403   0.02492  -0.0254   0.0589   1.0000
   6.500   0.8258   0.03703   0.02829  -0.0243   0.0609   1.0000
   6.750   0.8465   0.04182   0.03395  -0.0219   0.0711   1.0000
  10.500   0.6768   0.11450   0.11012  -0.0216   0.1255   1.0000
  10.750   0.6468   0.11959   0.11509  -0.0270   0.1223   1.0000
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