Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

SG6043 (sg6043-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SG6043 (sg6043-il)
Reynolds number: 100,000
Max Cl/Cd: 65.6 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sg6043-il-100000-n5.txt
Download as CSV file: xf-sg6043-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2183   0.10267   0.09778  -0.0635   0.9637   0.0521
  -7.500  -0.2198   0.10035   0.09551  -0.0666   0.9550   0.0524
  -7.250  -0.2140   0.09712   0.09230  -0.0715   0.9480   0.0526
  -7.000  -0.2048   0.09318   0.08839  -0.0712   0.9429   0.0530
  -6.750  -0.1889   0.08956   0.08476  -0.0704   0.9402   0.0538
  -6.250  -0.1672   0.08330   0.07852  -0.0736   0.9285   0.0554
  -6.000  -0.1487   0.07932   0.07452  -0.0785   0.9243   0.0563
  -5.500  -0.1176   0.06711   0.06217  -0.0933   0.9102   0.0356
  -5.250  -0.1044   0.06341   0.05843  -0.0964   0.9030   0.0349
  -5.000  -0.0772   0.05789   0.05277  -0.1041   0.8978   0.0350
  -4.750  -0.0410   0.05194   0.04660  -0.1127   0.8948   0.0347
  -4.500  -0.0169   0.04715   0.04157  -0.1172   0.8885   0.0336
  -4.250   0.0228   0.04027   0.03413  -0.1250   0.8845   0.0321
  -4.000   0.0679   0.03439   0.02744  -0.1317   0.8824   0.0314
  -3.750   0.1083   0.03121   0.02372  -0.1356   0.8806   0.0317
  -3.500   0.1474   0.02923   0.02135  -0.1386   0.8790   0.0335
  -3.250   0.1721   0.02777   0.01946  -0.1386   0.8727   0.0354
  -3.000   0.2062   0.02609   0.01728  -0.1399   0.8692   0.0366
  -2.750   0.2411   0.02486   0.01592  -0.1414   0.8666   0.0379
  -2.500   0.2778   0.02378   0.01469  -0.1431   0.8646   0.0402
  -2.250   0.3157   0.02279   0.01354  -0.1448   0.8631   0.0443
  -2.000   0.3335   0.02261   0.01339  -0.1432   0.8547   0.0485
  -1.750   0.3679   0.02186   0.01259  -0.1444   0.8516   0.0553
  -1.500   0.4052   0.02116   0.01190  -0.1461   0.8493   0.0717
  -1.250   0.4440   0.02053   0.01135  -0.1482   0.8475   0.1064
  -1.000   0.4616   0.02048   0.01140  -0.1466   0.8387   0.1383
  -0.750   0.4977   0.01983   0.01103  -0.1483   0.8355   0.2129
  -0.500   0.5367   0.01882   0.01087  -0.1508   0.8334   0.4817
  -0.250   0.5586   0.01853   0.01102  -0.1492   0.8274   0.6628
   0.000   0.5753   0.01819   0.01098  -0.1461   0.8211   0.7989
   0.250   0.6072   0.01769   0.01050  -0.1460   0.8176   1.0000
   0.500   0.6323   0.01788   0.01054  -0.1455   0.8104   1.0000
   0.750   0.6641   0.01790   0.01041  -0.1462   0.8049   1.0000
   1.000   0.7035   0.01774   0.01010  -0.1481   0.8015   1.0000
   1.250   0.7257   0.01797   0.01024  -0.1471   0.7929   1.0000
   1.500   0.7604   0.01788   0.01006  -0.1481   0.7876   1.0000
   1.750   0.7976   0.01772   0.00981  -0.1496   0.7831   1.0000
   2.000   0.8191   0.01795   0.00999  -0.1484   0.7734   1.0000
   2.250   0.8584   0.01771   0.00969  -0.1502   0.7688   1.0000
   2.500   0.8784   0.01795   0.00991  -0.1486   0.7581   1.0000
   2.750   0.9179   0.01768   0.00959  -0.1504   0.7526   1.0000
   3.000   0.9374   0.01791   0.00982  -0.1487   0.7410   1.0000
   3.250   0.9654   0.01793   0.00984  -0.1485   0.7314   1.0000
   3.500   0.9979   0.01781   0.00969  -0.1490   0.7221   1.0000
   3.750   1.0204   0.01794   0.00983  -0.1478   0.7096   1.0000
   4.000   1.0460   0.01798   0.00990  -0.1471   0.6970   1.0000
   4.250   1.0733   0.01799   0.00990  -0.1467   0.6840   1.0000
   4.500   1.1006   0.01801   0.00992  -0.1463   0.6700   1.0000
   4.750   1.1265   0.01807   0.00997  -0.1456   0.6543   1.0000
   5.000   1.1511   0.01817   0.01008  -0.1447   0.6370   1.0000
   5.250   1.1752   0.01829   0.01019  -0.1437   0.6179   1.0000
   5.500   1.2000   0.01843   0.01028  -0.1429   0.5974   1.0000
   5.750   1.2217   0.01867   0.01051  -0.1415   0.5748   1.0000
   6.000   1.2431   0.01895   0.01071  -0.1401   0.5500   1.0000
   6.250   1.2616   0.01932   0.01102  -0.1382   0.5234   1.0000
   6.500   1.2792   0.01976   0.01136  -0.1362   0.4959   1.0000
   6.750   1.2953   0.02029   0.01179  -0.1340   0.4674   1.0000
   7.000   1.3096   0.02090   0.01230  -0.1315   0.4385   1.0000
   7.250   1.3225   0.02159   0.01288  -0.1290   0.4094   1.0000
   7.500   1.3343   0.02237   0.01355  -0.1263   0.3804   1.0000
   7.750   1.3451   0.02322   0.01431  -0.1236   0.3530   1.0000
   8.000   1.3548   0.02416   0.01513  -0.1208   0.3263   1.0000
   8.250   1.3646   0.02514   0.01603  -0.1182   0.3004   1.0000
   8.500   1.3736   0.02620   0.01700  -0.1156   0.2768   1.0000
   8.750   1.3825   0.02731   0.01806  -0.1130   0.2540   1.0000
   9.000   1.3905   0.02852   0.01919  -0.1105   0.2338   1.0000
   9.250   1.3995   0.02972   0.02035  -0.1082   0.2148   1.0000
   9.500   1.4081   0.03099   0.02159  -0.1059   0.1977   1.0000
   9.750   1.4166   0.03230   0.02290  -0.1037   0.1827   1.0000
  10.000   1.4247   0.03368   0.02429  -0.1016   0.1693   1.0000
  10.250   1.4323   0.03514   0.02575  -0.0996   0.1578   1.0000
  10.500   1.4403   0.03662   0.02726  -0.0976   0.1471   1.0000
  10.750   1.4487   0.03811   0.02882  -0.0958   0.1375   1.0000
  11.000   1.4551   0.03979   0.03052  -0.0939   0.1296   1.0000
  11.250   1.4631   0.04140   0.03223  -0.0923   0.1216   1.0000
  11.500   1.4692   0.04319   0.03406  -0.0906   0.1151   1.0000
  11.750   1.4761   0.04496   0.03594  -0.0890   0.1084   1.0000
  12.000   1.4810   0.04697   0.03797  -0.0874   0.1031   1.0000
  12.500   1.4914   0.05103   0.04224  -0.0847   0.0928   1.0000
  12.750   1.4977   0.05307   0.04443  -0.0834   0.0880   1.0000
  13.000   1.5025   0.05527   0.04676  -0.0823   0.0838   1.0000
  13.250   1.5045   0.05777   0.04927  -0.0811   0.0804   1.0000
  13.500   1.5100   0.06005   0.05177  -0.0802   0.0764   1.0000
  13.750   1.5135   0.06255   0.05442  -0.0793   0.0729   1.0000
  14.000   1.5151   0.06527   0.05721  -0.0786   0.0701   1.0000
  14.250   1.5178   0.06801   0.06009  -0.0779   0.0672   1.0000
  14.500   1.5201   0.07085   0.06315  -0.0774   0.0642   1.0000
  14.750   1.5210   0.07387   0.06631  -0.0771   0.0617   1.0000
  15.000   1.5208   0.07705   0.06956  -0.0769   0.0596   1.0000
  15.250   1.5210   0.08035   0.07304  -0.0768   0.0574   1.0000
  15.500   1.5200   0.08391   0.07686  -0.0769   0.0552   1.0000
  15.750   1.5183   0.08759   0.08071  -0.0772   0.0532   1.0000
  16.000   1.5161   0.09132   0.08457  -0.0778   0.0516   1.0000
  16.250   1.5147   0.09497   0.08827  -0.0784   0.0501   1.0000
  16.500   1.5099   0.09940   0.09296  -0.0794   0.0486   1.0000
  16.750   1.5033   0.10425   0.09808  -0.0808   0.0471   1.0000
  17.000   1.4966   0.10918   0.10324  -0.0824   0.0458   1.0000
  17.250   1.4902   0.11413   0.10837  -0.0844   0.0447   1.0000
  17.500   1.4844   0.11900   0.11339  -0.0865   0.0436   1.0000
  17.750   1.4809   0.12344   0.11791  -0.0885   0.0425   1.0000
  18.000   1.4767   0.12808   0.12263  -0.0906   0.0416   1.0000
  18.250   1.4607   0.13555   0.13041  -0.0949   0.0410   1.0000
  18.500   1.4424   0.14383   0.13897  -0.1000   0.0405   1.0000
  18.750   1.4207   0.15336   0.14877  -0.1064   0.0401   1.0000
  19.000   1.3915   0.16540   0.16106  -0.1148   0.0400   1.0000
<< Back to SG6043 (sg6043-il)

Polar data table (+)

Polar graphs


<< Back to SG6043 (sg6043-il)