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SG6042 (sg6042-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SG6042 (sg6042-il)
Reynolds number: 50,000
Max Cl/Cd: 39.99 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6042-il-50000.txt
Download as CSV file: xf-sg6042-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3995   0.10409   0.09793  -0.0205   1.0000   0.2207
  -7.000  -0.3854   0.10006   0.09390  -0.0183   1.0000   0.2314
  -6.750  -0.4141   0.10004   0.09405  -0.0154   1.0000   0.2360
  -6.500  -0.4081   0.09675   0.09081  -0.0128   1.0000   0.2481
  -6.250  -0.4377   0.09648   0.09070  -0.0122   1.0000   0.2527
  -6.000  -0.4325   0.09341   0.08768  -0.0089   1.0000   0.2671
  -5.750  -0.4316   0.09060   0.08494  -0.0062   1.0000   0.2801
  -5.500  -0.4358   0.08818   0.08260  -0.0042   1.0000   0.2926
  -5.250  -0.4405   0.08584   0.08034  -0.0022   1.0000   0.3075
  -5.000  -0.4427   0.08348   0.07804   0.0001   1.0000   0.3248
  -4.750  -0.4478   0.08141   0.07604   0.0018   1.0000   0.3459
  -4.500  -0.4484   0.07884   0.07354   0.0048   1.0000   0.3685
  -4.250  -0.4522   0.07687   0.07165   0.0074   1.0000   0.3979
  -3.250  -0.2949   0.04719   0.03986  -0.0480   1.0000   0.1685
  -3.000  -0.2503   0.04217   0.03377  -0.0529   1.0000   0.1412
  -2.750  -0.2204   0.03900   0.03018  -0.0542   1.0000   0.1347
  -2.500  -0.1888   0.03642   0.02696  -0.0553   1.0000   0.1315
  -2.250  -0.1622   0.03473   0.02495  -0.0555   1.0000   0.1362
  -2.000  -0.1344   0.03320   0.02292  -0.0555   1.0000   0.1406
  -1.750  -0.1083   0.03175   0.02123  -0.0553   1.0000   0.1475
  -1.500  -0.0839   0.03069   0.02001  -0.0548   1.0000   0.1621
  -1.250  -0.0602   0.02976   0.01908  -0.0541   1.0000   0.1855
  -1.000  -0.0346   0.02884   0.01825  -0.0536   1.0000   0.2278
  -0.750  -0.0042   0.02754   0.01750  -0.0541   1.0000   0.3246
  -0.500   0.0010   0.02471   0.01694  -0.0475   1.0000   1.0000
  -0.250   0.0238   0.02526   0.01689  -0.0473   1.0000   1.0000
   0.000   0.0455   0.02585   0.01709  -0.0473   1.0000   1.0000
   0.250   0.0666   0.02649   0.01740  -0.0472   1.0000   1.0000
   0.500   0.0873   0.02718   0.01781  -0.0472   1.0000   1.0000
   0.750   0.1074   0.02790   0.01831  -0.0472   1.0000   1.0000
   1.000   0.1272   0.02868   0.01888  -0.0472   1.0000   1.0000
   1.250   0.1465   0.02951   0.01954  -0.0472   1.0000   1.0000
   1.500   0.1654   0.03040   0.02028  -0.0472   1.0000   1.0000
   1.750   0.1838   0.03133   0.02109  -0.0473   1.0000   1.0000
   2.000   0.2287   0.03313   0.02272  -0.0522   0.9868   1.0000
   2.250   0.2762   0.03481   0.02428  -0.0575   0.9686   1.0000
   2.500   0.3196   0.03624   0.02562  -0.0618   0.9508   1.0000
   2.750   0.3659   0.03767   0.02698  -0.0663   0.9333   1.0000
   3.000   0.4028   0.03877   0.02804  -0.0690   0.9149   1.0000
   3.250   0.4386   0.03979   0.02905  -0.0714   0.8962   1.0000
   3.500   0.4781   0.04079   0.03007  -0.0742   0.8776   1.0000
   3.750   0.5215   0.04170   0.03101  -0.0773   0.8594   1.0000
   4.000   0.5572   0.04245   0.03181  -0.0791   0.8397   1.0000
   4.250   0.5909   0.04309   0.03251  -0.0803   0.8190   1.0000
   4.500   0.6355   0.04342   0.03295  -0.0826   0.7994   1.0000
   4.750   0.6735   0.04367   0.03330  -0.0838   0.7788   1.0000
   5.000   0.7092   0.04374   0.03350  -0.0844   0.7569   1.0000
   5.250   0.7641   0.04281   0.03277  -0.0865   0.7374   1.0000
   5.500   0.7945   0.04258   0.03269  -0.0857   0.7134   1.0000
   5.750   0.8550   0.04035   0.03073  -0.0870   0.6936   1.0000
   6.000   0.9035   0.03827   0.02887  -0.0866   0.6706   1.0000
   6.250   0.9909   0.03350   0.02446  -0.0894   0.6470   1.0000
   6.500   1.0440   0.03090   0.02203  -0.0891   0.6120   1.0000
   6.750   1.0927   0.02896   0.02009  -0.0886   0.5668   1.0000
   7.000   1.1235   0.02852   0.01948  -0.0866   0.5155   1.0000
   7.250   1.1512   0.02879   0.01936  -0.0847   0.4627   1.0000
   7.500   1.1702   0.02982   0.02012  -0.0824   0.4154   1.0000
   7.750   1.1887   0.03111   0.02113  -0.0803   0.3734   1.0000
   8.000   1.2081   0.03263   0.02245  -0.0786   0.3378   1.0000
   8.250   1.2283   0.03428   0.02393  -0.0772   0.3074   1.0000
   8.500   1.2518   0.03603   0.02553  -0.0763   0.2812   1.0000
   8.750   1.2688   0.03795   0.02758  -0.0747   0.2601   1.0000
   9.000   1.2890   0.03999   0.02968  -0.0735   0.2417   1.0000
   9.250   1.3083   0.04209   0.03183  -0.0723   0.2254   1.0000
   9.500   1.3259   0.04456   0.03452  -0.0709   0.2125   1.0000
   9.750   1.3414   0.04706   0.03719  -0.0694   0.2007   1.0000
  10.000   1.3610   0.04970   0.03989  -0.0684   0.1899   1.0000
  10.250   1.3642   0.05259   0.04324  -0.0654   0.1824   1.0000
  10.500   1.3752   0.05555   0.04636  -0.0636   0.1742   1.0000
  10.750   1.3697   0.05886   0.05015  -0.0600   0.1693   1.0000
  11.000   1.3891   0.06210   0.05339  -0.0595   0.1618   1.0000
  11.250   1.3688   0.06590   0.05770  -0.0548   0.1598   1.0000
  11.500   1.3459   0.06984   0.06203  -0.0505   0.1584   1.0000
  11.750   1.3184   0.07390   0.06638  -0.0462   0.1580   1.0000
  12.000   1.2867   0.07864   0.07137  -0.0430   0.1583   1.0000
  12.250   1.2512   0.08436   0.07727  -0.0413   0.1596   1.0000
  12.500   1.2160   0.09113   0.08419  -0.0412   0.1609   1.0000
  12.750   1.1841   0.09881   0.09197  -0.0427   0.1621   1.0000
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