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SG6042 (sg6042-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SG6042 (sg6042-il)
Reynolds number: 200,000
Max Cl/Cd: 82.33 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sg6042-il-200000-n5.txt
Download as CSV file: xf-sg6042-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3181   0.08596   0.08244  -0.0538   0.9860   0.0188
  -8.000  -0.3081   0.08228   0.07877  -0.0569   0.9813   0.0181
  -7.500  -0.3045   0.06485   0.06136  -0.0770   0.9628   0.0153
  -7.250  -0.2934   0.05804   0.05445  -0.0853   0.9551   0.0152
  -7.000  -0.2784   0.05082   0.04705  -0.0929   0.9488   0.0150
  -6.750  -0.2672   0.04308   0.03898  -0.0982   0.9415   0.0149
  -6.500  -0.2533   0.03346   0.02861  -0.1030   0.9354   0.0150
  -6.250  -0.2269   0.02861   0.02310  -0.1060   0.9330   0.0159
  -6.000  -0.2061   0.02777   0.02218  -0.1056   0.9272   0.0166
  -5.750  -0.1797   0.02503   0.01896  -0.1065   0.9235   0.0177
  -5.500  -0.1496   0.02218   0.01554  -0.1077   0.9211   0.0182
  -5.250  -0.1169   0.02015   0.01302  -0.1090   0.9194   0.0190
  -5.000  -0.0857   0.01877   0.01142  -0.1100   0.9171   0.0198
  -4.750  -0.0629   0.01819   0.01079  -0.1092   0.9111   0.0210
  -4.500  -0.0322   0.01739   0.00984  -0.1098   0.9080   0.0228
  -4.250   0.0002   0.01644   0.00873  -0.1107   0.9056   0.0238
  -4.000   0.0335   0.01559   0.00785  -0.1120   0.9036   0.0252
  -3.750   0.0575   0.01513   0.00736  -0.1113   0.8978   0.0269
  -3.500   0.0870   0.01466   0.00681  -0.1116   0.8938   0.0298
  -3.250   0.1193   0.01411   0.00626  -0.1126   0.8909   0.0336
  -3.000   0.1532   0.01357   0.00568  -0.1138   0.8885   0.0398
  -2.750   0.1771   0.01326   0.00540  -0.1130   0.8821   0.0509
  -2.500   0.2074   0.01292   0.00508  -0.1135   0.8778   0.0700
  -2.250   0.2404   0.01255   0.00477  -0.1146   0.8745   0.0959
  -2.000   0.2672   0.01220   0.00461  -0.1146   0.8689   0.1429
  -1.750   0.2950   0.01171   0.00443  -0.1148   0.8633   0.2306
  -1.500   0.3256   0.01104   0.00425  -0.1157   0.8593   0.3875
  -1.250   0.3492   0.01051   0.00432  -0.1149   0.8532   0.5685
  -1.000   0.3749   0.01029   0.00433  -0.1141   0.8472   0.6655
  -0.750   0.4047   0.01010   0.00424  -0.1140   0.8427   0.7262
  -0.500   0.4260   0.01004   0.00427  -0.1123   0.8342   0.7697
  -0.250   0.4526   0.00990   0.00418  -0.1114   0.8285   0.8175
   0.000   0.4722   0.00981   0.00419  -0.1091   0.8204   0.8704
   0.250   0.5025   0.00964   0.00406  -0.1089   0.8140   0.9329
   0.500   0.5462   0.00954   0.00393  -0.1121   0.8057   1.0000
   0.750   0.5762   0.00953   0.00381  -0.1124   0.7975   1.0000
   1.000   0.6013   0.00958   0.00380  -0.1119   0.7866   1.0000
   1.250   0.6288   0.00961   0.00377  -0.1117   0.7767   1.0000
   1.500   0.6573   0.00964   0.00371  -0.1117   0.7664   1.0000
   1.750   0.6831   0.00969   0.00372  -0.1112   0.7535   1.0000
   2.000   0.7092   0.00974   0.00371  -0.1107   0.7396   1.0000
   2.250   0.7355   0.00981   0.00371  -0.1103   0.7245   1.0000
   2.500   0.7619   0.00988   0.00371  -0.1098   0.7074   1.0000
   2.750   0.7874   0.00998   0.00374  -0.1092   0.6881   1.0000
   3.000   0.8127   0.01011   0.00379  -0.1085   0.6673   1.0000
   3.250   0.8376   0.01028   0.00384  -0.1078   0.6442   1.0000
   3.500   0.8615   0.01048   0.00394  -0.1069   0.6174   1.0000
   3.750   0.8842   0.01074   0.00406  -0.1057   0.5872   1.0000
   4.000   0.9058   0.01106   0.00421  -0.1044   0.5546   1.0000
   4.250   0.9267   0.01141   0.00441  -0.1030   0.5213   1.0000
   4.500   0.9468   0.01181   0.00466  -0.1015   0.4874   1.0000
   4.750   0.9661   0.01225   0.00494  -0.0999   0.4526   1.0000
   5.250   1.0027   0.01325   0.00560  -0.0964   0.3823   1.0000
   5.500   1.0205   0.01379   0.00599  -0.0947   0.3478   1.0000
   5.750   1.0379   0.01436   0.00640  -0.0929   0.3142   1.0000
   6.000   1.0557   0.01493   0.00683  -0.0913   0.2845   1.0000
   6.250   1.0733   0.01551   0.00728  -0.0896   0.2562   1.0000
   6.500   1.0910   0.01609   0.00776  -0.0880   0.2313   1.0000
   6.750   1.1084   0.01666   0.00824  -0.0863   0.2093   1.0000
   7.000   1.1251   0.01724   0.00874  -0.0846   0.1903   1.0000
   7.250   1.1422   0.01781   0.00928  -0.0829   0.1732   1.0000
   7.500   1.1590   0.01840   0.00983  -0.0812   0.1578   1.0000
   7.750   1.1757   0.01901   0.01041  -0.0795   0.1449   1.0000
   8.000   1.1920   0.01965   0.01102  -0.0777   0.1335   1.0000
   8.250   1.2086   0.02028   0.01166  -0.0761   0.1227   1.0000
   8.500   1.2250   0.02092   0.01232  -0.0745   0.1135   1.0000
   8.750   1.2402   0.02164   0.01303  -0.0727   0.1055   1.0000
   9.000   1.2560   0.02233   0.01376  -0.0710   0.0978   1.0000
   9.250   1.2706   0.02310   0.01455  -0.0693   0.0913   1.0000
   9.500   1.2854   0.02386   0.01536  -0.0676   0.0849   1.0000
   9.750   1.2990   0.02471   0.01624  -0.0658   0.0796   1.0000
  10.000   1.3135   0.02551   0.01712  -0.0642   0.0741   1.0000
  10.250   1.3248   0.02652   0.01812  -0.0623   0.0696   1.0000
  10.500   1.3392   0.02736   0.01911  -0.0607   0.0654   1.0000
  10.750   1.3514   0.02835   0.02015  -0.0591   0.0613   1.0000
  11.000   1.3612   0.02953   0.02136  -0.0572   0.0581   1.0000
  11.250   1.3739   0.03054   0.02250  -0.0557   0.0548   1.0000
  11.500   1.3845   0.03170   0.02374  -0.0541   0.0515   1.0000
  11.750   1.3914   0.03317   0.02524  -0.0522   0.0488   1.0000
  12.000   1.4021   0.03440   0.02663  -0.0508   0.0463   1.0000
  12.250   1.4114   0.03576   0.02811  -0.0493   0.0437   1.0000
  12.500   1.4184   0.03732   0.02975  -0.0478   0.0415   1.0000
  12.750   1.4220   0.03924   0.03171  -0.0462   0.0396   1.0000
  13.000   1.4295   0.04088   0.03354  -0.0449   0.0379   1.0000
  13.250   1.4356   0.04269   0.03549  -0.0437   0.0362   1.0000
  13.500   1.4401   0.04467   0.03759  -0.0426   0.0346   1.0000
  13.750   1.4424   0.04692   0.03994  -0.0416   0.0333   1.0000
  14.000   1.4414   0.04959   0.04268  -0.0406   0.0321   1.0000
  14.250   1.4449   0.05191   0.04519  -0.0399   0.0310   1.0000
  14.500   1.4465   0.05452   0.04797  -0.0393   0.0299   1.0000
  14.750   1.4467   0.05735   0.05096  -0.0389   0.0289   1.0000
  15.000   1.4459   0.06041   0.05416  -0.0388   0.0281   1.0000
  15.250   1.4439   0.06373   0.05762  -0.0389   0.0274   1.0000
  15.500   1.4405   0.06736   0.06137  -0.0393   0.0268   1.0000
  15.750   1.4355   0.07135   0.06547  -0.0400   0.0262   1.0000
  16.000   1.4293   0.07563   0.06987  -0.0408   0.0257   1.0000
  16.250   1.4248   0.07989   0.07435  -0.0419   0.0253   1.0000
  16.500   1.4190   0.08450   0.07916  -0.0433   0.0248   1.0000
  16.750   1.4119   0.08946   0.08432  -0.0451   0.0243   1.0000
  17.000   1.4038   0.09475   0.08980  -0.0472   0.0238   1.0000
  17.250   1.3948   0.10033   0.09555  -0.0497   0.0234   1.0000
  17.500   1.3851   0.10624   0.10164  -0.0526   0.0230   1.0000
  17.750   1.3747   0.11243   0.10799  -0.0558   0.0227   1.0000
  18.000   1.3638   0.11887   0.11460  -0.0593   0.0224   1.0000
  18.250   1.3522   0.12558   0.12147  -0.0632   0.0221   1.0000
  18.500   1.3400   0.13261   0.12865  -0.0674   0.0219   1.0000
  18.750   1.3275   0.13990   0.13609  -0.0719   0.0217   1.0000
  19.000   1.3142   0.14754   0.14387  -0.0767   0.0215   1.0000
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