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

SG6050 (sg6050-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SG6050 (sg6050-il)
Reynolds number: 200,000
Max Cl/Cd: 74.66 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6050-il-200000.txt
Download as CSV file: xf-sg6050-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6050                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.7211   0.07937   0.07530  -0.0623   1.0000   0.0258
 -14.000  -0.7727   0.06691   0.06246  -0.0710   1.0000   0.0251
 -13.750  -0.7970   0.05949   0.05478  -0.0762   1.0000   0.0250
 -13.500  -0.8103   0.05409   0.04919  -0.0799   1.0000   0.0251
 -13.250  -0.8192   0.04967   0.04460  -0.0826   1.0000   0.0253
 -13.000  -0.8259   0.04594   0.04071  -0.0844   1.0000   0.0256
 -12.750  -0.8317   0.04279   0.03741  -0.0852   1.0000   0.0259
 -12.500  -0.8378   0.04017   0.03464  -0.0847   1.0000   0.0263
 -12.250  -0.8460   0.03808   0.03241  -0.0827   1.0000   0.0267
 -12.000  -0.8604   0.03665   0.03088  -0.0783   1.0000   0.0271
 -11.750  -0.8764   0.03562   0.02976  -0.0729   1.0000   0.0274
 -11.500  -0.8993   0.03513   0.02921  -0.0660   1.0000   0.0276
 -11.250  -0.8881   0.03324   0.02704  -0.0657   0.9967   0.0286
 -11.000  -0.8593   0.03151   0.02534  -0.0682   0.9925   0.0303
 -10.750  -0.8296   0.03001   0.02360  -0.0705   0.9871   0.0333
 -10.500  -0.7966   0.02885   0.02246  -0.0733   0.9833   0.0369
 -10.250  -0.7673   0.02770   0.02120  -0.0751   0.9770   0.0420
 -10.000  -0.7329   0.02681   0.02021  -0.0777   0.9728   0.0494
  -9.750  -0.6986   0.02605   0.01931  -0.0802   0.9688   0.0572
  -9.500  -0.6666   0.02580   0.01887  -0.0820   0.9625   0.0638
  -9.250  -0.6325   0.02497   0.01808  -0.0843   0.9588   0.0698
  -9.000  -0.6013   0.02473   0.01755  -0.0856   0.9528   0.0756
  -8.750  -0.5717   0.02392   0.01685  -0.0869   0.9470   0.0821
  -8.500  -0.5393   0.02347   0.01616  -0.0884   0.9427   0.0886
  -8.250  -0.5137   0.02267   0.01542  -0.0886   0.9353   0.0938
  -8.000  -0.4846   0.02208   0.01468  -0.0891   0.9295   0.0984
  -7.750  -0.4569   0.02125   0.01371  -0.0894   0.9240   0.1023
  -7.500  -0.4322   0.02046   0.01295  -0.0891   0.9165   0.1065
  -7.250  -0.4048   0.01990   0.01231  -0.0891   0.9111   0.1111
  -7.000  -0.3792   0.01950   0.01176  -0.0888   0.9041   0.1148
  -6.750  -0.3547   0.01862   0.01095  -0.0884   0.8978   0.1198
  -6.500  -0.3286   0.01813   0.01040  -0.0881   0.8929   0.1253
  -6.250  -0.3033   0.01770   0.00990  -0.0878   0.8855   0.1307
  -6.000  -0.2784   0.01708   0.00934  -0.0875   0.8798   0.1388
  -5.750  -0.2529   0.01658   0.00884  -0.0872   0.8745   0.1492
  -5.500  -0.2277   0.01605   0.00839  -0.0870   0.8677   0.1651
  -5.250  -0.2029   0.01531   0.00787  -0.0868   0.8625   0.2039
  -5.000  -0.1783   0.01473   0.00778  -0.0867   0.8570   0.3054
  -4.750  -0.1507   0.01484   0.00789  -0.0867   0.8506   0.3520
  -4.500  -0.1228   0.01493   0.00789  -0.0865   0.8456   0.3759
  -4.250  -0.0948   0.01502   0.00789  -0.0865   0.8403   0.3936
  -4.000  -0.0671   0.01506   0.00789  -0.0866   0.8339   0.4088
  -3.750  -0.0391   0.01503   0.00779  -0.0865   0.8290   0.4224
  -3.500  -0.0110   0.01502   0.00771  -0.0866   0.8237   0.4349
  -3.250   0.0169   0.01500   0.00767  -0.0866   0.8172   0.4467
  -3.000   0.0449   0.01488   0.00753  -0.0866   0.8122   0.4576
  -2.750   0.0732   0.01485   0.00745  -0.0867   0.8068   0.4688
  -2.500   0.1011   0.01484   0.00743  -0.0868   0.8003   0.4824
  -2.250   0.1292   0.01477   0.00736  -0.0867   0.7955   0.5000
  -2.000   0.1570   0.01473   0.00736  -0.0867   0.7901   0.5160
  -1.750   0.1850   0.01462   0.00731  -0.0869   0.7836   0.5254
  -1.500   0.2141   0.01453   0.00715  -0.0870   0.7788   0.5351
  -1.250   0.2423   0.01444   0.00711  -0.0872   0.7732   0.5443
  -1.000   0.2706   0.01437   0.00706  -0.0874   0.7667   0.5549
  -0.750   0.2996   0.01425   0.00693  -0.0875   0.7618   0.5676
  -0.500   0.3275   0.01418   0.00695  -0.0876   0.7557   0.5814
  -0.250   0.3555   0.01406   0.00692  -0.0877   0.7492   0.5996
   0.000   0.3841   0.01388   0.00681  -0.0877   0.7444   0.6244
   0.250   0.4103   0.01374   0.00691  -0.0874   0.7373   0.6632
   0.500   0.4346   0.01344   0.00693  -0.0863   0.7312   0.7346
   0.750   0.4526   0.01320   0.00700  -0.0830   0.7266   0.8493
   1.000   0.4739   0.01323   0.00716  -0.0809   0.7187   0.9258
   1.250   0.5136   0.01317   0.00705  -0.0829   0.7130   0.9697
   1.750   0.6025   0.01321   0.00700  -0.0901   0.6991   1.0000
   2.000   0.6278   0.01319   0.00686  -0.0896   0.6939   1.0000
   2.250   0.6500   0.01329   0.00698  -0.0888   0.6852   1.0000
   2.500   0.6762   0.01327   0.00686  -0.0884   0.6792   1.0000
   2.750   0.7005   0.01337   0.00697  -0.0879   0.6708   1.0000
   3.000   0.7276   0.01337   0.00690  -0.0878   0.6640   1.0000
   3.250   0.7534   0.01347   0.00700  -0.0875   0.6558   1.0000
   3.500   0.7809   0.01349   0.00696  -0.0874   0.6484   1.0000
   3.750   0.8073   0.01360   0.00709  -0.0873   0.6401   1.0000
   4.000   0.8352   0.01364   0.00708  -0.0873   0.6323   1.0000
   4.250   0.8616   0.01377   0.00722  -0.0871   0.6234   1.0000
   4.500   0.8898   0.01383   0.00723  -0.0872   0.6154   1.0000
   4.750   0.9158   0.01398   0.00742  -0.0870   0.6056   1.0000
   5.000   0.9443   0.01407   0.00744  -0.0871   0.5975   1.0000
   5.250   0.9697   0.01422   0.00764  -0.0868   0.5866   1.0000
   5.500   0.9962   0.01435   0.00778  -0.0866   0.5763   1.0000
   5.750   1.0236   0.01447   0.00784  -0.0865   0.5664   1.0000
   6.000   1.0485   0.01464   0.00807  -0.0861   0.5546   1.0000
   6.250   1.0741   0.01483   0.00827  -0.0858   0.5434   1.0000
   6.500   1.1003   0.01502   0.00843  -0.0856   0.5325   1.0000
   6.750   1.1250   0.01523   0.00865  -0.0851   0.5202   1.0000
   7.000   1.1488   0.01548   0.00893  -0.0845   0.5072   1.0000
   7.250   1.1727   0.01574   0.00922  -0.0839   0.4944   1.0000
   7.500   1.1963   0.01603   0.00950  -0.0833   0.4817   1.0000
   7.750   1.2192   0.01633   0.00979  -0.0826   0.4685   1.0000
   8.000   1.2412   0.01667   0.01011  -0.0817   0.4546   1.0000
   8.250   1.2616   0.01702   0.01049  -0.0805   0.4398   1.0000
   8.500   1.2811   0.01742   0.01091  -0.0793   0.4248   1.0000
   8.750   1.2996   0.01785   0.01136  -0.0779   0.4097   1.0000
   9.000   1.3167   0.01832   0.01185  -0.0762   0.3943   1.0000
   9.250   1.3321   0.01883   0.01237  -0.0743   0.3785   1.0000
   9.500   1.3448   0.01940   0.01294  -0.0720   0.3619   1.0000
   9.750   1.3538   0.02004   0.01356  -0.0691   0.3452   1.0000
  10.000   1.3598   0.02079   0.01429  -0.0658   0.3287   1.0000
  10.250   1.3661   0.02166   0.01517  -0.0628   0.3118   1.0000
  10.500   1.3724   0.02265   0.01617  -0.0601   0.2941   1.0000
  10.750   1.3777   0.02379   0.01732  -0.0575   0.2758   1.0000
  11.000   1.3814   0.02514   0.01864  -0.0550   0.2570   1.0000
  11.250   1.3832   0.02673   0.02017  -0.0525   0.2378   1.0000
  11.500   1.3845   0.02848   0.02187  -0.0503   0.2180   1.0000
  11.750   1.3851   0.03040   0.02375  -0.0482   0.1978   1.0000
  12.000   1.3835   0.03257   0.02585  -0.0462   0.1793   1.0000
  12.250   1.3812   0.03492   0.02812  -0.0444   0.1625   1.0000
  12.500   1.3801   0.03726   0.03042  -0.0428   0.1467   1.0000
  12.750   1.3785   0.03972   0.03285  -0.0414   0.1325   1.0000
  13.000   1.3757   0.04237   0.03547  -0.0400   0.1204   1.0000
  13.250   1.3740   0.04499   0.03810  -0.0388   0.1090   1.0000
  13.500   1.3723   0.04771   0.04084  -0.0378   0.0986   1.0000
  13.750   1.3697   0.05065   0.04380  -0.0370   0.0894   1.0000
  14.000   1.3642   0.05395   0.04709  -0.0362   0.0817   1.0000
  14.250   1.3612   0.05711   0.05029  -0.0356   0.0740   1.0000
  14.500   1.3574   0.06047   0.05370  -0.0352   0.0674   1.0000
  14.750   1.3495   0.06437   0.05758  -0.0349   0.0621   1.0000
  15.000   1.3467   0.06778   0.06110  -0.0348   0.0563   1.0000
  15.250   1.3365   0.07210   0.06537  -0.0347   0.0522   1.0000
  15.500   1.3343   0.07565   0.06905  -0.0349   0.0474   1.0000
  15.750   1.3245   0.08006   0.07344  -0.0351   0.0442   1.0000
  16.000   1.3220   0.08374   0.07725  -0.0354   0.0406   1.0000
  16.250   1.3163   0.08782   0.08135  -0.0360   0.0381   1.0000
  16.500   1.3120   0.09166   0.08527  -0.0363   0.0358   1.0000
<< Back to SG6050 (sg6050-il)

Polar data table (+)

Polar graphs


<< Back to SG6050 (sg6050-il)