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SG6043 (sg6043-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SG6043 (sg6043-il)
Reynolds number: 1,000,000
Max Cl/Cd: 175.24 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6043-il-1000000.txt
Download as CSV file: xf-sg6043-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1477   0.10361   0.10181  -0.0823   0.9835   0.0113
  -9.750  -0.1390   0.09957   0.09777  -0.0855   0.9805   0.0114
  -9.500  -0.1261   0.09582   0.09402  -0.0890   0.9787   0.0114
  -9.250  -0.1126   0.09164   0.08985  -0.0930   0.9773   0.0115
  -9.000  -0.1003   0.08692   0.08513  -0.0973   0.9761   0.0116
  -8.750  -0.0828   0.08420   0.08241  -0.1000   0.9753   0.0118
  -8.500  -0.0659   0.08143   0.07964  -0.1028   0.9739   0.0120
  -8.250  -0.0584   0.07892   0.07714  -0.1036   0.9673   0.0122
  -8.000  -0.0417   0.07557   0.07379  -0.1075   0.9651   0.0125
  -7.750  -0.0240   0.07184   0.07007  -0.1122   0.9633   0.0129
  -7.500  -0.0187   0.06873   0.06696  -0.1137   0.9545   0.0134
  -7.000   0.0174   0.05461   0.05280  -0.1348   0.9393   0.0147
  -6.750   0.0484   0.05157   0.04974  -0.1420   0.9342   0.0151
  -6.500   0.0809   0.04732   0.04543  -0.1514   0.9264   0.0157
  -6.250   0.1085   0.01535   0.01310  -0.1627   0.8868   0.0181
  -6.000   0.1285   0.01396   0.01160  -0.1642   0.8796   0.0184
  -5.750   0.1439   0.01413   0.00994  -0.1807   0.8869   0.0147
  -5.500   0.1713   0.01264   0.00817  -0.1812   0.8809   0.0148
  -5.250   0.1984   0.01162   0.00698  -0.1814   0.8753   0.0150
  -5.000   0.2252   0.01093   0.00618  -0.1814   0.8694   0.0153
  -4.750   0.2536   0.01034   0.00546  -0.1816   0.8641   0.0155
  -4.500   0.2807   0.00983   0.00486  -0.1815   0.8588   0.0158
  -4.250   0.3080   0.00936   0.00432  -0.1815   0.8532   0.0160
  -4.000   0.3365   0.00901   0.00387  -0.1816   0.8480   0.0165
  -3.750   0.3636   0.00870   0.00352  -0.1815   0.8426   0.0170
  -3.500   0.3913   0.00838   0.00314  -0.1814   0.8371   0.0174
  -3.250   0.4200   0.00815   0.00284  -0.1815   0.8320   0.0177
  -3.000   0.4475   0.00775   0.00240  -0.1815   0.8270   0.0186
  -2.750   0.4753   0.00756   0.00218  -0.1815   0.8218   0.0193
  -2.500   0.5038   0.00743   0.00200  -0.1816   0.8168   0.0203
  -2.250   0.5315   0.00730   0.00185  -0.1815   0.8117   0.0214
  -2.000   0.5592   0.00716   0.00170  -0.1814   0.8061   0.0243
  -1.750   0.5876   0.00701   0.00158  -0.1814   0.8005   0.0411
  -1.500   0.6151   0.00686   0.00153  -0.1814   0.7949   0.0697
  -1.250   0.6426   0.00678   0.00149  -0.1813   0.7889   0.0902
  -1.000   0.6706   0.00670   0.00146  -0.1813   0.7831   0.1237
  -0.750   0.6979   0.00652   0.00145  -0.1813   0.7767   0.1828
  -0.500   0.7257   0.00629   0.00145  -0.1814   0.7700   0.2953
  -0.250   0.7534   0.00596   0.00150  -0.1817   0.7635   0.4551
   0.000   0.7806   0.00580   0.00157  -0.1816   0.7562   0.5636
   0.250   0.8076   0.00573   0.00162  -0.1814   0.7491   0.6309
   0.500   0.8342   0.00568   0.00167  -0.1810   0.7407   0.6815
   0.750   0.8604   0.00565   0.00172  -0.1806   0.7320   0.7326
   1.000   0.8858   0.00562   0.00178  -0.1800   0.7226   0.7845
   1.250   0.9100   0.00556   0.00185  -0.1790   0.7130   0.8450
   1.500   0.9285   0.00538   0.00184  -0.1766   0.7028   1.0000
   1.750   0.9544   0.00549   0.00188  -0.1762   0.6907   1.0000
   2.000   0.9801   0.00561   0.00193  -0.1757   0.6771   1.0000
   2.250   1.0053   0.00574   0.00199  -0.1751   0.6628   1.0000
   2.500   1.0304   0.00588   0.00207  -0.1745   0.6480   1.0000
   2.750   1.0546   0.00606   0.00216  -0.1737   0.6306   1.0000
   3.000   1.0779   0.00627   0.00227  -0.1727   0.6108   1.0000
   3.250   1.1014   0.00648   0.00239  -0.1718   0.5895   1.0000
   3.500   1.1244   0.00671   0.00253  -0.1708   0.5681   1.0000
   3.750   1.1470   0.00697   0.00268  -0.1697   0.5473   1.0000
   4.000   1.1698   0.00722   0.00284  -0.1687   0.5245   1.0000
   4.250   1.1911   0.00754   0.00304  -0.1674   0.4986   1.0000
   4.500   1.2127   0.00785   0.00324  -0.1662   0.4733   1.0000
   4.750   1.2338   0.00819   0.00346  -0.1649   0.4479   1.0000
   5.000   1.2537   0.00859   0.00371  -0.1634   0.4183   1.0000
   5.250   1.2729   0.00901   0.00399  -0.1618   0.3880   1.0000
   5.500   1.2905   0.00947   0.00428  -0.1598   0.3553   1.0000
   5.750   1.3074   0.00996   0.00460  -0.1578   0.3224   1.0000
   6.000   1.3246   0.01044   0.00493  -0.1558   0.2945   1.0000
   6.250   1.3428   0.01086   0.00525  -0.1541   0.2709   1.0000
   6.500   1.3603   0.01133   0.00560  -0.1522   0.2481   1.0000
   6.750   1.3780   0.01179   0.00595  -0.1504   0.2255   1.0000
   7.000   1.3946   0.01230   0.00635  -0.1484   0.2045   1.0000
   7.250   1.4122   0.01276   0.00673  -0.1466   0.1870   1.0000
   7.500   1.4298   0.01323   0.00713  -0.1449   0.1708   1.0000
   7.750   1.4467   0.01373   0.00755  -0.1430   0.1551   1.0000
   8.000   1.4634   0.01423   0.00800  -0.1412   0.1412   1.0000
   8.250   1.4802   0.01474   0.00845  -0.1394   0.1292   1.0000
   8.500   1.4964   0.01529   0.00894  -0.1375   0.1178   1.0000
   8.750   1.5132   0.01579   0.00942  -0.1357   0.1089   1.0000
   9.000   1.5297   0.01632   0.00993  -0.1340   0.1004   1.0000
   9.250   1.5448   0.01694   0.01051  -0.1320   0.0918   1.0000
   9.500   1.5614   0.01747   0.01104  -0.1303   0.0860   1.0000
   9.750   1.5764   0.01811   0.01165  -0.1284   0.0791   1.0000
  10.000   1.5915   0.01873   0.01227  -0.1266   0.0732   1.0000
  10.250   1.6062   0.01940   0.01294  -0.1248   0.0676   1.0000
  10.500   1.6205   0.02010   0.01363  -0.1229   0.0627   1.0000
  10.750   1.6343   0.02085   0.01439  -0.1210   0.0579   1.0000
  11.000   1.6483   0.02159   0.01514  -0.1192   0.0542   1.0000
  11.250   1.6601   0.02250   0.01605  -0.1172   0.0497   1.0000
  11.500   1.6745   0.02323   0.01683  -0.1156   0.0476   1.0000
  11.750   1.6869   0.02414   0.01775  -0.1137   0.0448   1.0000
  12.000   1.6971   0.02522   0.01884  -0.1117   0.0417   1.0000
  12.250   1.7107   0.02605   0.01974  -0.1101   0.0403   1.0000
  12.500   1.7225   0.02705   0.02078  -0.1084   0.0383   1.0000
  12.750   1.7318   0.02827   0.02201  -0.1065   0.0361   1.0000
  13.000   1.7419   0.02945   0.02325  -0.1048   0.0343   1.0000
  13.250   1.7534   0.03052   0.02439  -0.1033   0.0329   1.0000
  13.500   1.7627   0.03181   0.02571  -0.1016   0.0311   1.0000
  13.750   1.7682   0.03348   0.02740  -0.0997   0.0289   1.0000
  14.000   1.7799   0.03462   0.02862  -0.0984   0.0277   1.0000
  14.250   1.7886   0.03605   0.03011  -0.0970   0.0262   1.0000
  14.500   1.7944   0.03780   0.03189  -0.0954   0.0245   1.0000
  14.750   1.8009   0.03953   0.03369  -0.0940   0.0233   1.0000
  15.000   1.8085   0.04119   0.03542  -0.0928   0.0222   1.0000
  15.250   1.8140   0.04311   0.03739  -0.0915   0.0210   1.0000
  15.500   1.8161   0.04544   0.03977  -0.0902   0.0198   1.0000
  15.750   1.8205   0.04759   0.04201  -0.0891   0.0190   1.0000
  16.000   1.8255   0.04973   0.04423  -0.0882   0.0183   1.0000
  16.250   1.8287   0.05212   0.04670  -0.0873   0.0175   1.0000
  16.500   1.8299   0.05483   0.04947  -0.0866   0.0167   1.0000
  16.750   1.8261   0.05823   0.05296  -0.0859   0.0159   1.0000
  17.000   1.8293   0.06086   0.05568  -0.0855   0.0154   1.0000
  17.250   1.8310   0.06372   0.05864  -0.0852   0.0150   1.0000
  17.500   1.8311   0.06690   0.06191  -0.0851   0.0145   1.0000
  17.750   1.8293   0.07042   0.06553  -0.0851   0.0141   1.0000
  18.000   1.8257   0.07428   0.06948  -0.0854   0.0137   1.0000
  18.250   1.8195   0.07865   0.07395  -0.0859   0.0133   1.0000
  18.500   1.8100   0.08367   0.07908  -0.0868   0.0129   1.0000
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