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SG6042 (sg6042-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SG6042 (sg6042-il)
Reynolds number: 200,000
Max Cl/Cd: 88.96 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6042-il-200000.txt
Download as CSV file: xf-sg6042-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3914   0.09911   0.09589  -0.0258   1.0000   0.0415
  -7.750  -0.4016   0.09727   0.09410  -0.0243   1.0000   0.0421
  -7.500  -0.4135   0.09549   0.09238  -0.0226   1.0000   0.0427
  -7.250  -0.4089   0.09116   0.08807  -0.0305   0.9947   0.0447
  -7.000  -0.3859   0.08203   0.07884  -0.0543   0.9849   0.0457
  -6.750  -0.3788   0.07601   0.07282  -0.0570   0.9794   0.0464
  -6.500  -0.3646   0.07372   0.07059  -0.0545   0.9767   0.0475
  -6.250  -0.3421   0.07016   0.06700  -0.0582   0.9736   0.0490
  -6.000  -0.3273   0.06608   0.06286  -0.0622   0.9669   0.0510
  -5.750  -0.2889   0.05680   0.05285  -0.0794   0.9604   0.0569
  -5.500  -0.2782   0.05272   0.04891  -0.0788   0.9551   0.0581
  -5.250  -0.2562   0.05009   0.04630  -0.0800   0.9510   0.0600
  -5.000  -0.2122   0.04780   0.04324  -0.0863   0.9474   0.0689
  -4.750  -0.1991   0.04195   0.03751  -0.0873   0.9425   0.0713
  -4.500  -0.1745   0.04010   0.03569  -0.0881   0.9380   0.0765
  -4.250  -0.1322   0.03009   0.02434  -0.0919   0.9358   0.0482
  -4.000  -0.0942   0.02558   0.01909  -0.0936   0.9343   0.0404
  -3.750  -0.0550   0.02351   0.01660  -0.0957   0.9328   0.0413
  -3.500  -0.0338   0.02255   0.01540  -0.0943   0.9260   0.0433
  -3.250   0.0009   0.02115   0.01372  -0.0953   0.9228   0.0443
  -3.000   0.0384   0.01996   0.01235  -0.0969   0.9205   0.0462
  -2.750   0.0774   0.01893   0.01138  -0.0992   0.9188   0.0525
  -2.500   0.0995   0.01840   0.01079  -0.0979   0.9118   0.0573
  -2.250   0.1339   0.01750   0.00995  -0.0992   0.9081   0.0707
  -2.000   0.1728   0.01668   0.00928  -0.1014   0.9057   0.1114
  -1.750   0.2128   0.01577   0.00882  -0.1042   0.9039   0.2022
  -1.500   0.2290   0.01449   0.00904  -0.1026   0.8966   0.5925
  -1.250   0.2569   0.01403   0.00903  -0.1016   0.8926   0.7550
  -1.000   0.2899   0.01364   0.00877  -0.1015   0.8901   0.8330
  -0.750   0.3192   0.01335   0.00854  -0.1007   0.8864   0.9001
  -0.500   0.3678   0.01315   0.00831  -0.1045   0.8818   1.0000
  -0.250   0.4074   0.01295   0.00798  -0.1068   0.8778   1.0000
   0.000   0.4502   0.01267   0.00759  -0.1096   0.8751   1.0000
   0.250   0.4813   0.01259   0.00742  -0.1101   0.8688   1.0000
   0.500   0.5159   0.01239   0.00714  -0.1112   0.8626   1.0000
   0.750   0.5582   0.01204   0.00671  -0.1137   0.8591   1.0000
   1.000   0.5835   0.01203   0.00665  -0.1130   0.8497   1.0000
   1.250   0.6221   0.01174   0.00630  -0.1147   0.8446   1.0000
   1.500   0.6489   0.01169   0.00622  -0.1142   0.8352   1.0000
   1.750   0.6862   0.01141   0.00588  -0.1156   0.8285   1.0000
   2.000   0.7120   0.01135   0.00581  -0.1148   0.8174   1.0000
   2.250   0.7423   0.01122   0.00564  -0.1149   0.8076   1.0000
   2.500   0.7749   0.01103   0.00539  -0.1153   0.7975   1.0000
   2.750   0.8004   0.01097   0.00534  -0.1145   0.7842   1.0000
   3.000   0.8265   0.01093   0.00527  -0.1138   0.7707   1.0000
   3.250   0.8529   0.01087   0.00520  -0.1131   0.7560   1.0000
   3.500   0.8792   0.01083   0.00514  -0.1124   0.7398   1.0000
   3.750   0.9060   0.01080   0.00506  -0.1118   0.7219   1.0000
   4.000   0.9296   0.01085   0.00509  -0.1106   0.7006   1.0000
   4.250   0.9547   0.01092   0.00511  -0.1097   0.6786   1.0000
   4.500   0.9779   0.01106   0.00519  -0.1086   0.6533   1.0000
   4.750   1.0008   0.01125   0.00528  -0.1073   0.6250   1.0000
   5.000   1.0222   0.01152   0.00542  -0.1058   0.5927   1.0000
   5.250   1.0422   0.01186   0.00563  -0.1041   0.5571   1.0000
   5.500   1.0603   0.01229   0.00588  -0.1021   0.5174   1.0000
   5.750   1.0769   0.01280   0.00620  -0.0999   0.4760   1.0000
   6.000   1.0921   0.01339   0.00657  -0.0975   0.4332   1.0000
   6.250   1.1066   0.01403   0.00702  -0.0951   0.3907   1.0000
   6.500   1.1204   0.01472   0.00751  -0.0926   0.3499   1.0000
   6.750   1.1337   0.01546   0.00805  -0.0901   0.3122   1.0000
   7.000   1.1472   0.01622   0.00863  -0.0877   0.2775   1.0000
   7.250   1.1599   0.01698   0.00924  -0.0852   0.2469   1.0000
   7.500   1.1719   0.01778   0.00989  -0.0827   0.2211   1.0000
   7.750   1.1858   0.01855   0.01058  -0.0805   0.1987   1.0000
   8.000   1.1989   0.01939   0.01131  -0.0782   0.1801   1.0000
   8.250   1.2121   0.02025   0.01210  -0.0760   0.1643   1.0000
   8.500   1.2260   0.02110   0.01291  -0.0739   0.1507   1.0000
   8.750   1.2404   0.02195   0.01376  -0.0720   0.1388   1.0000
   9.000   1.2542   0.02287   0.01467  -0.0700   0.1286   1.0000
   9.250   1.2666   0.02393   0.01565  -0.0680   0.1197   1.0000
   9.500   1.2817   0.02473   0.01655  -0.0663   0.1114   1.0000
   9.750   1.2948   0.02583   0.01764  -0.0645   0.1043   1.0000
  10.000   1.3085   0.02673   0.01859  -0.0627   0.0976   1.0000
  10.250   1.3218   0.02795   0.01982  -0.0610   0.0918   1.0000
  10.500   1.3352   0.02890   0.02088  -0.0593   0.0862   1.0000
  10.750   1.3483   0.03036   0.02228  -0.0578   0.0810   1.0000
  11.000   1.3609   0.03133   0.02344  -0.0561   0.0766   1.0000
  11.250   1.3719   0.03248   0.02463  -0.0544   0.0723   1.0000
  11.500   1.3854   0.03408   0.02627  -0.0530   0.0681   1.0000
  11.750   1.3956   0.03529   0.02765  -0.0512   0.0643   1.0000
  12.000   1.4049   0.03663   0.02903  -0.0496   0.0609   1.0000
  12.250   1.4185   0.03855   0.03100  -0.0484   0.0576   1.0000
  12.500   1.4270   0.04011   0.03279  -0.0467   0.0549   1.0000
  12.750   1.4350   0.04170   0.03448  -0.0452   0.0524   1.0000
  13.000   1.4443   0.04345   0.03623  -0.0440   0.0500   1.0000
  13.250   1.4541   0.04588   0.03883  -0.0427   0.0478   1.0000
  13.500   1.4577   0.04796   0.04117  -0.0411   0.0462   1.0000
  13.750   1.4612   0.05024   0.04367  -0.0397   0.0447   1.0000
  14.000   1.4644   0.05258   0.04618  -0.0384   0.0434   1.0000
  14.250   1.4678   0.05494   0.04866  -0.0373   0.0422   1.0000
  14.500   1.4726   0.05748   0.05128  -0.0365   0.0410   1.0000
  14.750   1.4735   0.06189   0.05587  -0.0357   0.0398   1.0000
  15.000   1.4631   0.06530   0.05956  -0.0348   0.0394   1.0000
  15.250   1.4513   0.06925   0.06380  -0.0343   0.0389   1.0000
  15.500   1.4374   0.07368   0.06850  -0.0343   0.0385   1.0000
  15.750   1.4217   0.07867   0.07375  -0.0349   0.0382   1.0000
  16.000   1.4036   0.08432   0.07967  -0.0362   0.0379   1.0000
  16.250   1.3831   0.09067   0.08628  -0.0384   0.0377   1.0000
  16.500   1.3598   0.09798   0.09384  -0.0416   0.0376   1.0000
  16.750   1.3333   0.10642   0.10253  -0.0460   0.0377   1.0000
  17.000   1.3024   0.11640   0.11276  -0.0519   0.0379   1.0000
  17.250   1.2664   0.12845   0.12503  -0.0598   0.0384   1.0000
  17.500   1.2225   0.14369   0.14045  -0.0702   0.0392   1.0000
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