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PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: PROPFAN CRUISE MISSILE WING AIRFOIL (pfcm-il)
Reynolds number: 50,000
Max Cl/Cd: 30.65 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-pfcm-il-50000.txt
Download as CSV file: xf-pfcm-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5492   0.10760   0.10077   0.0051   1.0000   0.2671
  -8.500  -0.5488   0.10455   0.09778   0.0050   1.0000   0.2832
  -8.250  -0.5556   0.10210   0.09542   0.0045   1.0000   0.2992
  -8.000  -0.5343   0.09744   0.09074   0.0067   1.0000   0.3212
  -7.750  -0.5484   0.09579   0.08921   0.0065   1.0000   0.3414
  -7.500  -0.5189   0.09120   0.08457   0.0102   1.0000   0.3783
  -7.250  -0.5192   0.08890   0.08234   0.0122   1.0000   0.4098
  -6.750  -0.4858   0.08154   0.07499   0.0163   1.0000   0.4728
  -6.500  -0.4751   0.07843   0.07191   0.0182   1.0000   0.5037
  -5.500  -0.4898   0.04579   0.03768  -0.0377   1.0000   0.1585
  -5.250  -0.4667   0.04122   0.03252  -0.0379   1.0000   0.1386
  -5.000  -0.4428   0.03758   0.02824  -0.0375   1.0000   0.1263
  -4.750  -0.4175   0.03469   0.02450  -0.0366   1.0000   0.1183
  -4.500  -0.3934   0.03185   0.02133  -0.0357   1.0000   0.1159
  -4.250  -0.3684   0.02954   0.01861  -0.0346   1.0000   0.1164
  -4.000  -0.3440   0.02749   0.01627  -0.0337   1.0000   0.1226
  -3.750  -0.3188   0.02566   0.01425  -0.0325   1.0000   0.1285
  -3.500  -0.2930   0.02399   0.01242  -0.0310   1.0000   0.1351
  -3.250  -0.2687   0.02243   0.01093  -0.0297   1.0000   0.1517
  -3.000  -0.1261   0.01792   0.00920  -0.0361   1.0000   1.0000
  -2.750  -0.1185   0.01745   0.00853  -0.0342   1.0000   1.0000
  -2.500  -0.1155   0.01704   0.00798  -0.0316   1.0000   1.0000
  -2.250  -0.1162   0.01668   0.00751  -0.0281   1.0000   1.0000
  -2.000  -0.1174   0.01640   0.00710  -0.0245   1.0000   1.0000
  -1.750  -0.1120   0.01624   0.00674  -0.0218   1.0000   1.0000
  -1.500  -0.0985   0.01619   0.00645  -0.0203   1.0000   1.0000
  -1.250  -0.0809   0.01622   0.00620  -0.0194   1.0000   1.0000
  -1.000  -0.0614   0.01632   0.00607  -0.0189   1.0000   1.0000
  -0.750  -0.0409   0.01646   0.00601  -0.0184   1.0000   1.0000
  -0.500  -0.0199   0.01664   0.00603  -0.0181   1.0000   1.0000
  -0.250   0.0015   0.01686   0.00610  -0.0178   1.0000   1.0000
   0.000   0.0229   0.01712   0.00622  -0.0176   1.0000   1.0000
   0.250   0.0445   0.01742   0.00642  -0.0175   1.0000   1.0000
   0.500   0.0660   0.01776   0.00668  -0.0174   1.0000   1.0000
   0.750   0.0874   0.01814   0.00700  -0.0173   1.0000   1.0000
   1.000   0.1087   0.01856   0.00738  -0.0173   1.0000   1.0000
   1.250   0.1299   0.01903   0.00783  -0.0173   1.0000   1.0000
   1.500   0.1509   0.01954   0.00833  -0.0174   1.0000   1.0000
   1.750   0.1717   0.02009   0.00890  -0.0175   1.0000   1.0000
   2.000   0.1923   0.02069   0.00953  -0.0177   1.0000   1.0000
   2.250   0.2127   0.02134   0.01023  -0.0179   1.0000   1.0000
   2.500   0.2329   0.02204   0.01103  -0.0181   1.0000   1.0000
   2.750   0.2528   0.02279   0.01187  -0.0184   1.0000   1.0000
   3.000   0.2724   0.02360   0.01278  -0.0187   1.0000   1.0000
   3.250   0.2918   0.02447   0.01377  -0.0190   1.0000   1.0000
   3.500   0.3107   0.02540   0.01485  -0.0194   1.0000   1.0000
   3.750   0.3590   0.02672   0.01652  -0.0255   0.9859   1.0000
   4.000   0.4160   0.02808   0.01829  -0.0327   0.9647   1.0000
   4.250   0.4792   0.02917   0.01992  -0.0402   0.9356   1.0000
   4.500   0.6225   0.02031   0.01013  -0.0291   0.2975   1.0000
   4.750   0.6314   0.02401   0.01242  -0.0264   0.1759   1.0000
   5.000   0.6551   0.02615   0.01444  -0.0250   0.1450   1.0000
   5.250   0.6853   0.02843   0.01647  -0.0244   0.1259   1.0000
   5.500   0.7190   0.03069   0.01898  -0.0239   0.1182   1.0000
   5.750   0.7502   0.03379   0.02205  -0.0237   0.1126   1.0000
   6.000   0.7762   0.03609   0.02499  -0.0225   0.1072   1.0000
   6.250   0.8019   0.03920   0.02859  -0.0215   0.1060   1.0000
   6.500   0.8254   0.04285   0.03283  -0.0203   0.1084   1.0000
   6.750   0.8470   0.04707   0.03741  -0.0194   0.1116   1.0000
   7.000   0.8626   0.05123   0.04257  -0.0175   0.1211   1.0000
   7.250   0.8758   0.05619   0.04822  -0.0164   0.1326   1.0000
   7.500   0.8844   0.06204   0.05468  -0.0161   0.1491   1.0000
   7.750   0.8807   0.07086   0.06435  -0.0193   0.1979   1.0000
   8.000   0.8195   0.08781   0.08167  -0.0398   0.3059   1.0000
   8.250   0.7559   0.07289   0.06695  -0.0138   0.2104   1.0000
   8.500   0.7138   0.07989   0.07389  -0.0174   0.2129   1.0000
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