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SG6042 (sg6042-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SG6042 (sg6042-il)
Reynolds number: 500,000
Max Cl/Cd: 106.28 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sg6042-il-500000-n5.txt
Download as CSV file: xf-sg6042-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6042                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2887   0.08517   0.08278  -0.0628   0.9858   0.0075
  -8.750  -0.2826   0.08027   0.07789  -0.0670   0.9819   0.0077
  -8.500  -0.2751   0.07560   0.07324  -0.0714   0.9771   0.0080
  -8.250  -0.2672   0.06936   0.06700  -0.0786   0.9731   0.0082
  -8.000  -0.2684   0.06290   0.06057  -0.0854   0.9621   0.0084
  -7.750  -0.3161   0.02319   0.01915  -0.1180   0.9367   0.0084
  -7.500  -0.2913   0.01955   0.01486  -0.1196   0.9332   0.0088
  -7.250  -0.2670   0.01796   0.01289  -0.1197   0.9278   0.0091
  -7.000  -0.2404   0.01659   0.01133  -0.1203   0.9233   0.0095
  -6.750  -0.2105   0.01575   0.01036  -0.1212   0.9199   0.0098
  -6.500  -0.1822   0.01498   0.00945  -0.1216   0.9158   0.0102
  -6.250  -0.1555   0.01426   0.00859  -0.1217   0.9103   0.0107
  -6.000  -0.1264   0.01364   0.00782  -0.1221   0.9059   0.0114
  -5.750  -0.0971   0.01320   0.00723  -0.1225   0.9017   0.0120
  -5.500  -0.0719   0.01239   0.00636  -0.1222   0.8957   0.0126
  -5.250  -0.0437   0.01189   0.00579  -0.1224   0.8909   0.0132
  -5.000  -0.0159   0.01144   0.00527  -0.1225   0.8862   0.0138
  -4.750   0.0106   0.01104   0.00480  -0.1223   0.8806   0.0144
  -4.500   0.0387   0.01070   0.00437  -0.1223   0.8757   0.0151
  -4.250   0.0661   0.01029   0.00392  -0.1223   0.8711   0.0162
  -4.000   0.0929   0.01001   0.00361  -0.1221   0.8655   0.0172
  -3.750   0.1208   0.00975   0.00329  -0.1221   0.8606   0.0182
  -3.500   0.1486   0.00953   0.00301  -0.1221   0.8557   0.0192
  -3.250   0.1754   0.00930   0.00276  -0.1219   0.8498   0.0212
  -3.000   0.2034   0.00910   0.00255  -0.1218   0.8445   0.0252
  -2.750   0.2306   0.00890   0.00238  -0.1217   0.8391   0.0353
  -2.500   0.2579   0.00873   0.00224  -0.1216   0.8333   0.0487
  -2.250   0.2859   0.00860   0.00211  -0.1216   0.8282   0.0620
  -2.000   0.3129   0.00846   0.00201  -0.1214   0.8219   0.0786
  -1.750   0.3402   0.00830   0.00192  -0.1213   0.8151   0.1074
  -1.500   0.3672   0.00809   0.00184  -0.1212   0.8085   0.1526
  -1.250   0.3938   0.00777   0.00177  -0.1211   0.8016   0.2417
  -1.000   0.4205   0.00742   0.00171  -0.1211   0.7949   0.3535
  -0.750   0.4465   0.00708   0.00169  -0.1209   0.7867   0.4744
  -0.500   0.4723   0.00682   0.00172  -0.1205   0.7779   0.5867
  -0.250   0.4983   0.00672   0.00174  -0.1200   0.7680   0.6494
   0.000   0.5245   0.00666   0.00176  -0.1195   0.7580   0.6890
   0.250   0.5504   0.00663   0.00179  -0.1189   0.7479   0.7290
   0.500   0.5753   0.00659   0.00182  -0.1181   0.7358   0.7712
   0.750   0.5995   0.00657   0.00186  -0.1171   0.7214   0.8089
   1.000   0.6229   0.00657   0.00189  -0.1159   0.7062   0.8428
   1.250   0.6456   0.00659   0.00192  -0.1145   0.6896   0.8744
   1.500   0.6673   0.00664   0.00195  -0.1129   0.6688   0.9048
   1.750   0.6909   0.00672   0.00198  -0.1118   0.6476   0.9380
   2.000   0.7245   0.00684   0.00201  -0.1130   0.6233   0.9855
   2.250   0.7493   0.00705   0.00208  -0.1124   0.5981   1.0000
   2.500   0.7721   0.00731   0.00219  -0.1114   0.5687   1.0000
   2.750   0.7943   0.00761   0.00232  -0.1103   0.5353   1.0000
   3.000   0.8163   0.00793   0.00247  -0.1091   0.5008   1.0000
   3.250   0.8386   0.00825   0.00264  -0.1081   0.4695   1.0000
   3.500   0.8610   0.00858   0.00282  -0.1071   0.4390   1.0000
   3.750   0.8830   0.00894   0.00303  -0.1060   0.4071   1.0000
   4.000   0.9049   0.00931   0.00324  -0.1050   0.3755   1.0000
   4.250   0.9269   0.00969   0.00347  -0.1039   0.3448   1.0000
   4.500   0.9482   0.01012   0.00374  -0.1028   0.3120   1.0000
   4.750   0.9697   0.01053   0.00401  -0.1017   0.2823   1.0000
   5.000   0.9913   0.01094   0.00428  -0.1007   0.2544   1.0000
   5.250   1.0131   0.01134   0.00456  -0.0997   0.2305   1.0000
   5.500   1.0346   0.01175   0.00487  -0.0986   0.2078   1.0000
   5.750   1.0562   0.01215   0.00517  -0.0976   0.1881   1.0000
   6.000   1.0778   0.01254   0.00548  -0.0966   0.1705   1.0000
   6.250   1.0992   0.01292   0.00581  -0.0955   0.1555   1.0000
   6.500   1.1207   0.01330   0.00613  -0.0945   0.1431   1.0000
   6.750   1.1415   0.01369   0.00648  -0.0934   0.1308   1.0000
   7.000   1.1614   0.01410   0.00683  -0.0920   0.1194   1.0000
   7.250   1.1812   0.01448   0.00720  -0.0907   0.1097   1.0000
   7.500   1.2009   0.01486   0.00757  -0.0893   0.1020   1.0000
   7.750   1.2195   0.01531   0.00798  -0.0878   0.0937   1.0000
   8.000   1.2388   0.01571   0.00839  -0.0864   0.0867   1.0000
   8.250   1.2571   0.01617   0.00884  -0.0849   0.0800   1.0000
   8.500   1.2756   0.01662   0.00929  -0.0834   0.0735   1.0000
   8.750   1.2935   0.01711   0.00977  -0.0819   0.0682   1.0000
   9.000   1.3114   0.01758   0.01027  -0.0804   0.0633   1.0000
   9.250   1.3282   0.01814   0.01081  -0.0788   0.0585   1.0000
   9.500   1.3459   0.01862   0.01134  -0.0773   0.0549   1.0000
   9.750   1.3622   0.01920   0.01192  -0.0757   0.0510   1.0000
  10.000   1.3783   0.01979   0.01256  -0.0740   0.0477   1.0000
  10.250   1.3946   0.02036   0.01318  -0.0725   0.0449   1.0000
  10.500   1.4098   0.02103   0.01386  -0.0708   0.0420   1.0000
  10.750   1.4240   0.02175   0.01462  -0.0690   0.0394   1.0000
  11.000   1.4393   0.02240   0.01534  -0.0675   0.0370   1.0000
  11.250   1.4531   0.02317   0.01614  -0.0658   0.0345   1.0000
  11.500   1.4653   0.02406   0.01707  -0.0640   0.0322   1.0000
  11.750   1.4792   0.02484   0.01792  -0.0624   0.0306   1.0000
  12.000   1.4917   0.02572   0.01887  -0.0607   0.0287   1.0000
  12.250   1.5029   0.02673   0.01992  -0.0590   0.0269   1.0000
  12.500   1.5132   0.02782   0.02107  -0.0573   0.0254   1.0000
  12.750   1.5243   0.02887   0.02222  -0.0557   0.0242   1.0000
  13.000   1.5341   0.03004   0.02347  -0.0541   0.0229   1.0000
  13.250   1.5428   0.03134   0.02482  -0.0525   0.0218   1.0000
  13.500   1.5494   0.03284   0.02639  -0.0508   0.0206   1.0000
  13.750   1.5573   0.03426   0.02791  -0.0494   0.0199   1.0000
  14.000   1.5647   0.03576   0.02952  -0.0480   0.0191   1.0000
  14.250   1.5712   0.03738   0.03123  -0.0467   0.0183   1.0000
  14.500   1.5763   0.03918   0.03312  -0.0454   0.0175   1.0000
  14.750   1.5794   0.04123   0.03524  -0.0442   0.0167   1.0000
  15.000   1.5805   0.04354   0.03765  -0.0432   0.0161   1.0000
  15.250   1.5844   0.04567   0.03990  -0.0423   0.0156   1.0000
  15.500   1.5862   0.04809   0.04245  -0.0416   0.0153   1.0000
  15.750   1.5889   0.05049   0.04496  -0.0412   0.0146   1.0000
  16.000   1.5889   0.05331   0.04790  -0.0408   0.0142   1.0000
  16.250   1.5879   0.05638   0.05108  -0.0407   0.0138   1.0000
  16.500   1.5854   0.05977   0.05458  -0.0409   0.0134   1.0000
  16.750   1.5809   0.06357   0.05850  -0.0414   0.0131   1.0000
  17.000   1.5740   0.06787   0.06293  -0.0422   0.0129   1.0000
  17.250   1.5649   0.07273   0.06792  -0.0435   0.0126   1.0000
  17.500   1.5580   0.07743   0.07278  -0.0450   0.0125   1.0000
  17.750   1.5507   0.08234   0.07784  -0.0467   0.0123   1.0000
  18.000   1.5412   0.08780   0.08346  -0.0488   0.0121   1.0000
  18.250   1.5305   0.09365   0.08946  -0.0513   0.0120   1.0000
  18.500   1.5179   0.10001   0.09598  -0.0543   0.0118   1.0000
  18.750   1.5044   0.10671   0.10283  -0.0576   0.0116   1.0000
  19.000   1.4896   0.11381   0.11009  -0.0613   0.0115   1.0000
  19.250   1.4737   0.12130   0.11773  -0.0653   0.0114   1.0000
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