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GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GM15 (smoothed) (gm15sm-il)
Reynolds number: 50,000
Max Cl/Cd: 45.24 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-gm15sm-il-50000.txt
Download as CSV file: xf-gm15sm-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GM15 (smoothed)                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3586   0.10565   0.09918  -0.0227   1.0000   0.1709
  -7.000  -0.3364   0.09951   0.09301  -0.0210   1.0000   0.1799
  -6.750  -0.3508   0.09956   0.09323  -0.0203   1.0000   0.1841
  -6.500  -0.3432   0.09557   0.08930  -0.0185   1.0000   0.1898
  -6.250  -0.3474   0.09429   0.08812  -0.0182   1.0000   0.1972
  -6.000  -0.3473   0.09160   0.08553  -0.0176   1.0000   0.2017
  -5.750  -0.3444   0.08918   0.08317  -0.0165   1.0000   0.2100
  -5.500  -0.3455   0.08713   0.08122  -0.0176   1.0000   0.2150
  -5.250  -0.3399   0.08421   0.07830  -0.0157   1.0000   0.2229
  -5.000  -0.3374   0.08179   0.07596  -0.0169   1.0000   0.2299
  -4.750  -0.3299   0.08033   0.07454  -0.0217   1.0000   0.2415
  -4.500  -0.3253   0.07628   0.07055  -0.0164   1.0000   0.2469
  -4.250  -0.3161   0.07369   0.06800  -0.0188   1.0000   0.2578
  -4.000  -0.3034   0.07109   0.06541  -0.0215   1.0000   0.2706
  -3.750  -0.2891   0.06826   0.06259  -0.0236   1.0000   0.2842
  -3.500  -0.2820   0.06502   0.05940  -0.0206   1.0000   0.2919
  -3.250  -0.2604   0.06221   0.05656  -0.0253   1.0000   0.3127
  -3.000  -0.1408   0.04892   0.04231  -0.0626   1.0000   0.1849
  -2.750  -0.1480   0.04933   0.04303  -0.0540   1.0000   0.2231
  -2.500  -0.0045   0.03145   0.02258  -0.0878   1.0000   0.1297
  -2.250   0.0238   0.02962   0.02052  -0.0885   1.0000   0.1416
  -2.000   0.0561   0.02757   0.01800  -0.0898   1.0000   0.1564
  -1.750   0.0828   0.02627   0.01661  -0.0897   1.0000   0.1783
  -1.500   0.1078   0.02550   0.01581  -0.0893   1.0000   0.2218
  -1.250   0.1292   0.02520   0.01566  -0.0880   1.0000   0.2929
  -1.000   0.1489   0.02508   0.01562  -0.0866   1.0000   0.3681
  -0.750   0.1694   0.02484   0.01534  -0.0855   1.0000   0.4246
  -0.500   0.1912   0.02459   0.01502  -0.0849   1.0000   0.4710
  -0.250   0.2143   0.02441   0.01472  -0.0847   1.0000   0.5140
   0.000   0.2377   0.02429   0.01455  -0.0847   1.0000   0.5574
   0.250   0.2614   0.02420   0.01449  -0.0849   1.0000   0.6062
   0.500   0.2856   0.02397   0.01451  -0.0851   1.0000   0.6750
   0.750   0.2965   0.02345   0.01457  -0.0837   1.0000   1.0000
   1.000   0.3228   0.02440   0.01502  -0.0857   1.0000   1.0000
   1.250   0.3430   0.02538   0.01569  -0.0862   1.0000   1.0000
   1.500   0.3868   0.02667   0.01668  -0.0912   0.9881   1.0000
   1.750   0.4384   0.02786   0.01764  -0.0971   0.9706   1.0000
   2.000   0.4874   0.02893   0.01857  -0.1022   0.9528   1.0000
   2.250   0.5387   0.02992   0.01949  -0.1074   0.9356   1.0000
   2.500   0.5794   0.03075   0.02029  -0.1106   0.9163   1.0000
   2.750   0.6229   0.03146   0.02100  -0.1139   0.8975   1.0000
   3.000   0.6716   0.03197   0.02157  -0.1178   0.8801   1.0000
   3.250   0.7052   0.03255   0.02226  -0.1191   0.8598   1.0000
   3.500   0.7498   0.03281   0.02263  -0.1218   0.8413   1.0000
   3.750   0.7978   0.03280   0.02279  -0.1245   0.8238   1.0000
   4.000   0.8316   0.03307   0.02327  -0.1251   0.8029   1.0000
   4.250   0.8833   0.03257   0.02302  -0.1276   0.7853   1.0000
   4.500   0.9231   0.03234   0.02301  -0.1282   0.7656   1.0000
   4.750   0.9640   0.03193   0.02284  -0.1286   0.7456   1.0000
   5.000   1.0105   0.03110   0.02238  -0.1292   0.7264   1.0000
   5.250   1.0435   0.03099   0.02253  -0.1284   0.7034   1.0000
   5.500   1.0778   0.03081   0.02261  -0.1275   0.6801   1.0000
   5.750   1.1157   0.03038   0.02246  -0.1266   0.6562   1.0000
   6.000   1.1486   0.03023   0.02264  -0.1251   0.6297   1.0000
   6.250   1.1744   0.02886   0.02135  -0.1205   0.5834   1.0000
   6.500   1.1909   0.02678   0.01900  -0.1137   0.5171   1.0000
   6.750   1.1983   0.02649   0.01874  -0.1082   0.4575   1.0000
   7.000   1.1915   0.02692   0.01875  -0.1006   0.3502   1.0000
   7.250   1.1752   0.03059   0.02078  -0.0936   0.1909   1.0000
   7.500   1.1808   0.03381   0.02332  -0.0904   0.1397   1.0000
   7.750   1.1999   0.03671   0.02591  -0.0885   0.1178   1.0000
   8.000   1.2317   0.03973   0.02895  -0.0879   0.1027   1.0000
   8.250   1.2648   0.04318   0.03231  -0.0880   0.0913   1.0000
   8.500   1.2936   0.04670   0.03641  -0.0870   0.0879   1.0000
   8.750   1.3166   0.05071   0.04094  -0.0855   0.0862   1.0000
   9.000   1.3323   0.05498   0.04576  -0.0835   0.0856   1.0000
   9.250   1.3411   0.05916   0.05045  -0.0812   0.0843   1.0000
   9.500   1.3465   0.06327   0.05497  -0.0788   0.0826   1.0000
   9.750   1.3488   0.06760   0.05966  -0.0765   0.0815   1.0000
  10.000   1.3381   0.07216   0.06476  -0.0734   0.0823   1.0000
  10.250   1.3207   0.07689   0.06995  -0.0704   0.0839   1.0000
  10.500   1.2994   0.08143   0.07481  -0.0676   0.0853   1.0000
  10.750   1.2748   0.08588   0.07950  -0.0653   0.0866   1.0000
  11.000   1.2505   0.09087   0.08467  -0.0645   0.0878   1.0000
  11.250   1.2285   0.09651   0.09045  -0.0650   0.0891   1.0000
  11.500   1.2108   0.10267   0.09671  -0.0664   0.0903   1.0000
  11.750   1.2060   0.10906   0.10314  -0.0675   0.0914   1.0000
  12.000   1.1308   0.12476   0.11898  -0.0817   0.1033   1.0000
  12.250   1.0856   0.14217   0.13625  -0.0962   0.1137   1.0000
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