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SG6043 (sg6043-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SG6043 (sg6043-il)
Reynolds number: 50,000
Max Cl/Cd: 37.93 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sg6043-il-50000-n5.txt
Download as CSV file: xf-sg6043-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6043                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2550   0.11519   0.10927  -0.0302   0.9899   0.1000
  -7.750  -0.2581   0.11308   0.10718  -0.0336   0.9857   0.1033
  -7.500  -0.2668   0.11142   0.10558  -0.0365   0.9800   0.1043
  -7.250  -0.2467   0.10577   0.09994  -0.0366   0.9770   0.1068
  -7.000  -0.2318   0.10188   0.09604  -0.0372   0.9735   0.1104
  -6.750  -0.2284   0.09896   0.09315  -0.0381   0.9681   0.1134
  -6.500  -0.2271   0.09608   0.09029  -0.0402   0.9631   0.1171
  -6.250  -0.2441   0.09492   0.08921  -0.0417   0.9547   0.1196
  -6.000  -0.2492   0.09240   0.08672  -0.0480   0.9469   0.1206
  -5.750  -0.2368   0.08765   0.08200  -0.0459   0.9429   0.1219
  -5.500  -0.2220   0.08351   0.07786  -0.0460   0.9389   0.1239
  -5.250  -0.2164   0.08028   0.07464  -0.0469   0.9326   0.1253
  -4.750  -0.2266   0.07601   0.06951  -0.0709   0.9427   0.0628
  -4.500  -0.2087   0.07298   0.06651  -0.0711   0.9386   0.0606
  -4.250  -0.1857   0.06854   0.06197  -0.0757   0.9330   0.0577
  -4.000  -0.1505   0.06282   0.05598  -0.0841   0.9280   0.0554
  -3.750  -0.1096   0.05783   0.05068  -0.0920   0.9245   0.0557
  -3.500  -0.0729   0.05349   0.04598  -0.0981   0.9200   0.0560
  -3.250  -0.0299   0.04880   0.04073  -0.1048   0.9160   0.0550
  -3.000   0.0148   0.04499   0.03632  -0.1105   0.9128   0.0548
  -2.750   0.0592   0.04206   0.03281  -0.1151   0.9101   0.0555
  -2.500   0.0945   0.04017   0.03049  -0.1176   0.9057   0.0586
  -2.250   0.1301   0.03838   0.02810  -0.1196   0.9008   0.0621
  -2.000   0.1674   0.03681   0.02617  -0.1217   0.8970   0.0649
  -1.750   0.2053   0.03570   0.02483  -0.1237   0.8938   0.0701
  -1.500   0.2289   0.03499   0.02388  -0.1231   0.8867   0.0770
  -1.250   0.2621   0.03430   0.02300  -0.1241   0.8820   0.0883
  -1.000   0.3002   0.03358   0.02223  -0.1261   0.8786   0.1090
  -0.750   0.3236   0.03326   0.02187  -0.1257   0.8708   0.1356
  -0.500   0.3604   0.03262   0.02135  -0.1276   0.8661   0.1837
  -0.250   0.4031   0.03146   0.02106  -0.1311   0.8631   0.3585
   0.000   0.4121   0.03067   0.02148  -0.1269   0.8548   0.7123
   0.250   0.4362   0.03022   0.02102  -0.1253   0.8485   1.0000
   0.500   0.4594   0.03070   0.02118  -0.1249   0.8397   1.0000
   0.750   0.4940   0.03098   0.02114  -0.1261   0.8340   1.0000
   1.000   0.5195   0.03142   0.02135  -0.1261   0.8259   1.0000
   1.250   0.5513   0.03172   0.02144  -0.1269   0.8191   1.0000
   1.500   0.5790   0.03211   0.02166  -0.1271   0.8114   1.0000
   1.750   0.6083   0.03243   0.02183  -0.1275   0.8037   1.0000
   2.000   0.6366   0.03278   0.02206  -0.1277   0.7959   1.0000
   2.250   0.6655   0.03307   0.02226  -0.1280   0.7878   1.0000
   2.500   0.6917   0.03345   0.02256  -0.1278   0.7791   1.0000
   2.750   0.7228   0.03363   0.02267  -0.1283   0.7714   1.0000
   3.000   0.7460   0.03407   0.02308  -0.1277   0.7613   1.0000
   3.250   0.7807   0.03403   0.02301  -0.1284   0.7545   1.0000
   3.500   0.8014   0.03453   0.02350  -0.1274   0.7431   1.0000
   3.750   0.8403   0.03417   0.02314  -0.1285   0.7375   1.0000
   4.000   0.8592   0.03469   0.02368  -0.1272   0.7248   1.0000
   4.250   0.8831   0.03496   0.02400  -0.1264   0.7138   1.0000
   4.500   0.9203   0.03447   0.02354  -0.1270   0.7068   1.0000
   4.750   0.9409   0.03481   0.02394  -0.1258   0.6938   1.0000
   5.000   0.9656   0.03491   0.02412  -0.1249   0.6819   1.0000
   5.250   1.0068   0.03401   0.02330  -0.1257   0.6745   1.0000
   5.500   1.0287   0.03414   0.02351  -0.1243   0.6605   1.0000
   5.750   1.0524   0.03415   0.02364  -0.1231   0.6465   1.0000
   6.000   1.0778   0.03403   0.02361  -0.1221   0.6322   1.0000
   6.250   1.1044   0.03380   0.02348  -0.1210   0.6173   1.0000
   6.500   1.1313   0.03353   0.02330  -0.1200   0.6012   1.0000
   6.750   1.1588   0.03319   0.02308  -0.1190   0.5837   1.0000
   7.000   1.1883   0.03275   0.02271  -0.1181   0.5649   1.0000
   7.250   1.2071   0.03299   0.02301  -0.1162   0.5425   1.0000
   7.500   1.2312   0.03293   0.02301  -0.1148   0.5190   1.0000
   7.750   1.2500   0.03323   0.02333  -0.1129   0.4932   1.0000
   8.000   1.2703   0.03349   0.02355  -0.1112   0.4662   1.0000
   8.250   1.2865   0.03406   0.02407  -0.1091   0.4382   1.0000
   8.500   1.2987   0.03494   0.02493  -0.1067   0.4099   1.0000
   8.750   1.3100   0.03594   0.02587  -0.1044   0.3823   1.0000
   9.000   1.3203   0.03707   0.02691  -0.1020   0.3558   1.0000
   9.250   1.3284   0.03842   0.02821  -0.0997   0.3304   1.0000
   9.500   1.3361   0.03989   0.02964  -0.0974   0.3068   1.0000
   9.750   1.3431   0.04148   0.03119  -0.0952   0.2848   1.0000
  10.000   1.3498   0.04316   0.03278  -0.0932   0.2650   1.0000
  10.250   1.3567   0.04492   0.03454  -0.0913   0.2465   1.0000
  10.500   1.3635   0.04676   0.03641  -0.0895   0.2294   1.0000
  10.750   1.3703   0.04865   0.03832  -0.0878   0.2140   1.0000
  11.000   1.3776   0.05057   0.04025  -0.0862   0.2002   1.0000
  11.250   1.3848   0.05254   0.04221  -0.0847   0.1876   1.0000
  11.500   1.3924   0.05456   0.04433  -0.0833   0.1758   1.0000
  11.750   1.4002   0.05665   0.04656  -0.0820   0.1650   1.0000
  12.000   1.4083   0.05874   0.04871  -0.0808   0.1555   1.0000
  12.250   1.4169   0.06081   0.05085  -0.0797   0.1469   1.0000
  12.500   1.4242   0.06315   0.05340  -0.0786   0.1386   1.0000
  12.750   1.4338   0.06516   0.05538  -0.0776   0.1317   1.0000
  13.000   1.4389   0.06791   0.05847  -0.0766   0.1249   1.0000
  13.250   1.4468   0.07015   0.06074  -0.0757   0.1190   1.0000
  13.500   1.4496   0.07319   0.06405  -0.0749   0.1136   1.0000
  13.750   1.4523   0.07618   0.06726  -0.0742   0.1087   1.0000
  14.000   1.4618   0.07842   0.06948  -0.0735   0.1041   1.0000
  14.250   1.4538   0.08279   0.07428  -0.0731   0.1005   1.0000
  14.500   1.4490   0.08677   0.07853  -0.0730   0.0970   1.0000
  14.750   1.4524   0.08970   0.08156  -0.0728   0.0935   1.0000
  15.000   1.4488   0.09376   0.08581  -0.0730   0.0908   1.0000
  15.250   1.4299   0.10002   0.09246  -0.0743   0.0890   1.0000
  15.500   1.4098   0.10681   0.09958  -0.0765   0.0874   1.0000
  15.750   1.3873   0.11443   0.10748  -0.0796   0.0862   1.0000
  16.000   1.3579   0.12396   0.11728  -0.0845   0.0856   1.0000
  16.250   1.3072   0.13959   0.13316  -0.0942   0.0864   1.0000
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