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SG6042 (sg6042-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SG6042 (sg6042-il)
Reynolds number: 500,000
Max Cl/Cd: 123.58 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6042-il-500000.txt
Download as CSV file: xf-sg6042-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3107   0.08689   0.08466  -0.0561   0.9887   0.0192
  -8.250  -0.2975   0.08064   0.07842  -0.0643   0.9858   0.0193
  -8.000  -0.2887   0.07693   0.07472  -0.0665   0.9828   0.0198
  -7.750  -0.2752   0.07407   0.07187  -0.0693   0.9781   0.0202
  -7.500  -0.2585   0.06962   0.06742  -0.0759   0.9744   0.0206
  -7.250  -0.2422   0.06475   0.06255  -0.0834   0.9678   0.0217
  -7.000  -0.2194   0.05708   0.05480  -0.0962   0.9627   0.0223
  -6.750  -0.2042   0.04331   0.04059  -0.1108   0.9540   0.0245
  -6.500  -0.1791   0.04299   0.04032  -0.1121   0.9517   0.0254
  -6.250  -0.1509   0.03934   0.03651  -0.1162   0.9495   0.0267
  -6.000  -0.1382   0.02299   0.01868  -0.1203   0.9426   0.0189
  -5.750  -0.1141   0.01921   0.01437  -0.1208   0.9383   0.0184
  -5.500  -0.0835   0.01686   0.01159  -0.1217   0.9359   0.0186
  -5.250  -0.0503   0.01550   0.00989  -0.1229   0.9341   0.0194
  -5.000  -0.0180   0.01406   0.00838  -0.1242   0.9324   0.0207
  -4.750   0.0041   0.01339   0.00764  -0.1230   0.9261   0.0215
  -4.500   0.0346   0.01260   0.00674  -0.1235   0.9227   0.0224
  -4.250   0.0665   0.01189   0.00593  -0.1242   0.9200   0.0233
  -4.000   0.0957   0.01118   0.00516  -0.1245   0.9164   0.0247
  -3.750   0.1211   0.01077   0.00475  -0.1241   0.9107   0.0267
  -3.500   0.1512   0.01034   0.00428  -0.1244   0.9066   0.0284
  -3.250   0.1826   0.00986   0.00374  -0.1251   0.9032   0.0309
  -3.000   0.2073   0.00959   0.00348  -0.1244   0.8968   0.0353
  -2.750   0.2361   0.00917   0.00312  -0.1245   0.8920   0.0530
  -2.500   0.2668   0.00888   0.00288  -0.1251   0.8881   0.0812
  -2.250   0.2917   0.00868   0.00277  -0.1245   0.8817   0.1070
  -2.000   0.3200   0.00836   0.00261  -0.1246   0.8763   0.1635
  -1.750   0.3471   0.00780   0.00249  -0.1248   0.8708   0.3080
  -1.500   0.3711   0.00711   0.00247  -0.1244   0.8640   0.5259
  -1.250   0.3981   0.00680   0.00249  -0.1241   0.8588   0.6564
  -1.000   0.4232   0.00671   0.00251  -0.1233   0.8520   0.7099
  -0.750   0.4502   0.00664   0.00248  -0.1228   0.8455   0.7460
  -0.500   0.4761   0.00658   0.00247  -0.1221   0.8383   0.7793
  -0.250   0.5018   0.00652   0.00244  -0.1213   0.8306   0.8093
   0.000   0.5272   0.00648   0.00244  -0.1205   0.8234   0.8362
   0.250   0.5512   0.00642   0.00243  -0.1194   0.8156   0.8667
   0.500   0.5731   0.00636   0.00242  -0.1176   0.8074   0.9033
   0.750   0.5969   0.00627   0.00236  -0.1162   0.7986   0.9464
   1.000   0.6382   0.00621   0.00229  -0.1190   0.7890   0.9884
   1.250   0.6691   0.00624   0.00224  -0.1196   0.7789   1.0000
   1.500   0.6952   0.00629   0.00222  -0.1192   0.7672   1.0000
   1.750   0.7208   0.00634   0.00223  -0.1187   0.7548   1.0000
   2.000   0.7466   0.00640   0.00224  -0.1182   0.7417   1.0000
   2.250   0.7722   0.00648   0.00226  -0.1177   0.7270   1.0000
   2.500   0.7973   0.00658   0.00229  -0.1170   0.7096   1.0000
   2.750   0.8218   0.00671   0.00232  -0.1162   0.6899   1.0000
   3.000   0.8461   0.00686   0.00239  -0.1154   0.6686   1.0000
   3.250   0.8700   0.00704   0.00247  -0.1145   0.6469   1.0000
   3.500   0.8933   0.00725   0.00259  -0.1135   0.6212   1.0000
   3.750   0.9158   0.00749   0.00272  -0.1124   0.5937   1.0000
   4.000   0.9376   0.00778   0.00287  -0.1111   0.5637   1.0000
   4.250   0.9584   0.00812   0.00306  -0.1097   0.5294   1.0000
   4.500   0.9783   0.00851   0.00328  -0.1082   0.4922   1.0000
   4.750   0.9981   0.00893   0.00352  -0.1067   0.4533   1.0000
   5.000   1.0174   0.00939   0.00380  -0.1051   0.4142   1.0000
   5.250   1.0370   0.00986   0.00410  -0.1036   0.3765   1.0000
   5.500   1.0562   0.01036   0.00441  -0.1021   0.3403   1.0000
   5.750   1.0758   0.01086   0.00474  -0.1007   0.3051   1.0000
   6.000   1.0954   0.01135   0.00509  -0.0993   0.2736   1.0000
   6.250   1.1150   0.01184   0.00545  -0.0979   0.2452   1.0000
   6.500   1.1344   0.01235   0.00582  -0.0965   0.2195   1.0000
   6.750   1.1539   0.01284   0.00621  -0.0951   0.1956   1.0000
   7.000   1.1728   0.01335   0.00662  -0.0937   0.1751   1.0000
   7.250   1.1914   0.01382   0.00702  -0.0921   0.1577   1.0000
   7.500   1.2095   0.01430   0.00744  -0.0905   0.1427   1.0000
   7.750   1.2273   0.01480   0.00788  -0.0888   0.1293   1.0000
   8.000   1.2448   0.01531   0.00835  -0.0871   0.1176   1.0000
   8.250   1.2615   0.01587   0.00886  -0.0853   0.1069   1.0000
   8.500   1.2796   0.01635   0.00933  -0.0838   0.0983   1.0000
   8.750   1.2968   0.01688   0.00987  -0.0821   0.0907   1.0000
   9.000   1.3127   0.01748   0.01044  -0.0803   0.0835   1.0000
   9.250   1.3299   0.01800   0.01101  -0.0787   0.0780   1.0000
   9.500   1.3457   0.01862   0.01161  -0.0769   0.0723   1.0000
   9.750   1.3611   0.01926   0.01228  -0.0751   0.0677   1.0000
  10.000   1.3775   0.01983   0.01290  -0.0735   0.0633   1.0000
  10.250   1.3884   0.02077   0.01382  -0.0712   0.0587   1.0000
  10.500   1.4058   0.02128   0.01442  -0.0698   0.0559   1.0000
  10.750   1.4204   0.02199   0.01516  -0.0681   0.0525   1.0000
  11.000   1.4288   0.02312   0.01629  -0.0657   0.0485   1.0000
  11.250   1.4452   0.02373   0.01701  -0.0643   0.0461   1.0000
  11.500   1.4585   0.02456   0.01788  -0.0626   0.0433   1.0000
  11.750   1.4645   0.02592   0.01926  -0.0602   0.0402   1.0000
  12.000   1.4768   0.02686   0.02030  -0.0586   0.0383   1.0000
  12.250   1.4889   0.02783   0.02135  -0.0570   0.0361   1.0000
  12.500   1.4978   0.02906   0.02262  -0.0552   0.0341   1.0000
  12.750   1.4972   0.03109   0.02471  -0.0526   0.0321   1.0000
  13.000   1.5088   0.03219   0.02593  -0.0512   0.0310   1.0000
  13.250   1.5179   0.03350   0.02734  -0.0498   0.0296   1.0000
  13.500   1.5258   0.03495   0.02886  -0.0484   0.0283   1.0000
  13.750   1.5298   0.03679   0.03075  -0.0468   0.0272   1.0000
  14.000   1.5268   0.03935   0.03340  -0.0450   0.0261   1.0000
  14.250   1.5290   0.04152   0.03569  -0.0437   0.0254   1.0000
  14.500   1.5350   0.04337   0.03767  -0.0427   0.0247   1.0000
  14.750   1.5393   0.04546   0.03987  -0.0418   0.0239   1.0000
  15.000   1.5425   0.04773   0.04226  -0.0411   0.0231   1.0000
  15.250   1.5447   0.05017   0.04479  -0.0406   0.0224   1.0000
  15.500   1.5439   0.05308   0.04780  -0.0402   0.0219   1.0000
  15.750   1.5403   0.05643   0.05122  -0.0400   0.0212   1.0000
  16.000   1.5303   0.06075   0.05566  -0.0400   0.0207   1.0000
  16.250   1.5279   0.06428   0.05933  -0.0404   0.0203   1.0000
  16.500   1.5280   0.06761   0.06281  -0.0410   0.0199   1.0000
  16.750   1.5251   0.07148   0.06683  -0.0418   0.0195   1.0000
  17.000   1.5211   0.07565   0.07114  -0.0429   0.0191   1.0000
  17.250   1.5161   0.08008   0.07571  -0.0443   0.0187   1.0000
  17.500   1.5101   0.08483   0.08059  -0.0460   0.0184   1.0000
  17.750   1.5034   0.08984   0.08573  -0.0480   0.0181   1.0000
  18.000   1.4957   0.09514   0.09115  -0.0503   0.0178   1.0000
  18.250   1.4869   0.10074   0.09689  -0.0529   0.0176   1.0000
  18.500   1.4775   0.10656   0.10283  -0.0557   0.0174   1.0000
  18.750   1.4677   0.11259   0.10897  -0.0587   0.0171   1.0000
  19.000   1.4575   0.11873   0.11523  -0.0620   0.0169   1.0000
  19.250   1.4468   0.12500   0.12161  -0.0654   0.0167   1.0000
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