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SA7024 (sa7024-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: SA7024 (sa7024-il)
Reynolds number: 100,000
Max Cl/Cd: 59.02 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7024-il-100000-n5.txt
Download as CSV file: xf-sa7024-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7024                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3814   0.09325   0.08844  -0.0246   1.0000   0.0458
  -7.500  -0.3894   0.09132   0.08663  -0.0262   1.0000   0.0473
  -7.250  -0.3928   0.08880   0.08421  -0.0299   1.0000   0.0479
  -7.000  -0.3893   0.08546   0.08091  -0.0338   1.0000   0.0482
  -6.750  -0.3834   0.08163   0.07711  -0.0379   1.0000   0.0483
  -6.500  -0.3758   0.07762   0.07309  -0.0413   1.0000   0.0484
  -6.250  -0.3737   0.07313   0.06869  -0.0398   1.0000   0.0491
  -6.000  -0.3719   0.07105   0.06670  -0.0342   1.0000   0.0512
  -5.750  -0.3651   0.06856   0.06423  -0.0337   1.0000   0.0550
  -5.500  -0.3397   0.06319   0.05849  -0.0475   1.0000   0.0615
  -5.000  -0.3178   0.05197   0.04727  -0.0466   1.0000   0.0334
  -4.500  -0.2790   0.04259   0.03744  -0.0514   1.0000   0.0289
  -4.250  -0.2493   0.03620   0.03045  -0.0551   1.0000   0.0260
  -4.000  -0.2202   0.03223   0.02580  -0.0564   1.0000   0.0244
  -3.750  -0.1835   0.02952   0.02258  -0.0591   0.9965   0.0238
  -3.500  -0.1455   0.02629   0.01881  -0.0621   0.9926   0.0234
  -3.250  -0.1081   0.02378   0.01580  -0.0644   0.9879   0.0233
  -3.000  -0.0701   0.02180   0.01339  -0.0665   0.9836   0.0233
  -2.750  -0.0343   0.02022   0.01149  -0.0680   0.9782   0.0236
  -2.500   0.0015   0.01875   0.00979  -0.0696   0.9726   0.0243
  -2.250   0.0374   0.01755   0.00850  -0.0713   0.9668   0.0266
  -2.000   0.0729   0.01690   0.00777  -0.0729   0.9593   0.0329
  -1.750   0.1091   0.01612   0.00684  -0.0745   0.9520   0.0380
  -1.500   0.1468   0.01535   0.00606  -0.0763   0.9448   0.0563
  -1.250   0.1801   0.01391   0.00575  -0.0781   0.9369   0.3356
  -0.750   0.2470   0.01198   0.00533  -0.0789   0.9209   1.0000
  -0.500   0.2831   0.01195   0.00505  -0.0803   0.9110   1.0000
  -0.250   0.3199   0.01191   0.00478  -0.0818   0.9010   1.0000
   0.000   0.3546   0.01188   0.00458  -0.0830   0.8893   1.0000
   0.250   0.3882   0.01185   0.00441  -0.0838   0.8760   1.0000
   0.750   0.4534   0.01182   0.00415  -0.0850   0.8457   1.0000
   1.000   0.4845   0.01183   0.00407  -0.0853   0.8283   1.0000
   1.250   0.5155   0.01185   0.00400  -0.0856   0.8105   1.0000
   1.500   0.5458   0.01189   0.00397  -0.0856   0.7917   1.0000
   1.750   0.5745   0.01197   0.00397  -0.0854   0.7708   1.0000
   2.000   0.6032   0.01206   0.00399  -0.0852   0.7492   1.0000
   2.250   0.6311   0.01219   0.00403  -0.0848   0.7263   1.0000
   2.500   0.6579   0.01234   0.00411  -0.0843   0.7017   1.0000
   2.750   0.6844   0.01252   0.00425  -0.0837   0.6765   1.0000
   3.000   0.7105   0.01273   0.00439  -0.0830   0.6509   1.0000
   3.250   0.7363   0.01297   0.00455  -0.0823   0.6251   1.0000
   3.500   0.7616   0.01323   0.00475  -0.0816   0.5985   1.0000
   3.750   0.7866   0.01352   0.00497  -0.0808   0.5708   1.0000
   4.000   0.8112   0.01383   0.00529  -0.0800   0.5417   1.0000
   4.250   0.8354   0.01418   0.00557  -0.0791   0.5120   1.0000
   4.500   0.8593   0.01456   0.00589  -0.0782   0.4823   1.0000
   4.750   0.8830   0.01497   0.00624  -0.0774   0.4526   1.0000
   5.000   0.9065   0.01541   0.00664  -0.0765   0.4232   1.0000
   5.250   0.9296   0.01587   0.00716  -0.0756   0.3932   1.0000
   5.500   0.9526   0.01637   0.00764  -0.0747   0.3631   1.0000
   5.750   0.9748   0.01693   0.00816  -0.0737   0.3309   1.0000
   6.000   0.9967   0.01754   0.00872  -0.0727   0.2972   1.0000
   6.250   1.0182   0.01820   0.00933  -0.0717   0.2641   1.0000
   6.500   1.0394   0.01891   0.01001  -0.0708   0.2337   1.0000
   6.750   1.0607   0.01966   0.01083  -0.0698   0.2043   1.0000
   7.000   1.0806   0.02054   0.01163  -0.0687   0.1685   1.0000
   7.250   1.0995   0.02157   0.01250  -0.0677   0.1288   1.0000
   7.500   1.1169   0.02282   0.01349  -0.0666   0.0858   1.0000
   7.750   1.1339   0.02418   0.01466  -0.0653   0.0528   1.0000
   8.000   1.1494   0.02577   0.01617  -0.0638   0.0296   1.0000
   8.250   1.1638   0.02752   0.01800  -0.0619   0.0205   1.0000
   8.500   1.1765   0.02936   0.02004  -0.0598   0.0172   1.0000
   8.750   1.1891   0.03108   0.02203  -0.0578   0.0156   1.0000
   9.000   1.2001   0.03292   0.02418  -0.0556   0.0144   1.0000
   9.250   1.2097   0.03486   0.02635  -0.0534   0.0135   1.0000
   9.500   1.2180   0.03693   0.02863  -0.0512   0.0129   1.0000
   9.750   1.2241   0.03921   0.03111  -0.0489   0.0123   1.0000
  10.000   1.2268   0.04172   0.03383  -0.0463   0.0117   1.0000
  10.250   1.2261   0.04493   0.03729  -0.0438   0.0112   1.0000
  10.500   1.2282   0.04744   0.04006  -0.0416   0.0108   1.0000
  10.750   1.2284   0.05001   0.04293  -0.0396   0.0103   1.0000
  11.000   1.2253   0.05299   0.04621  -0.0380   0.0099   1.0000
  11.250   1.2191   0.05638   0.04990  -0.0368   0.0096   1.0000
  11.500   1.2106   0.06020   0.05399  -0.0363   0.0095   1.0000
  11.750   1.1994   0.06461   0.05868  -0.0366   0.0094   1.0000
  12.000   1.1866   0.06955   0.06388  -0.0378   0.0093   1.0000
  12.250   1.1719   0.07522   0.06979  -0.0401   0.0093   1.0000
  12.500   1.1557   0.08171   0.07651  -0.0434   0.0094   1.0000
  12.750   1.1381   0.08905   0.08406  -0.0477   0.0094   1.0000
  13.000   1.1198   0.09724   0.09244  -0.0529   0.0097   1.0000
  13.250   1.1008   0.10629   0.10165  -0.0587   0.0100   1.0000
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