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SA7024 (sa7024-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SA7024 (sa7024-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.37 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7024-il-1000000.txt
Download as CSV file: xf-sa7024-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3903   0.09762   0.09599  -0.0211   1.0000   0.0070
  -8.500  -0.3882   0.09435   0.09274  -0.0218   1.0000   0.0071
  -6.500  -0.3708   0.06443   0.06298  -0.0386   0.9960   0.0077
  -6.250  -0.3394   0.05929   0.05780  -0.0477   0.9941   0.0080
  -6.000  -0.3088   0.05375   0.05220  -0.0563   0.9907   0.0083
  -5.750  -0.2729   0.04722   0.04556  -0.0660   0.9876   0.0085
  -5.500  -0.2347   0.04064   0.03882  -0.0746   0.9853   0.0090
  -5.250  -0.1955   0.03412   0.03206  -0.0818   0.9835   0.0096
  -5.000  -0.1626   0.02885   0.02651  -0.0852   0.9794   0.0107
  -4.750  -0.1275   0.02654   0.02398  -0.0868   0.9759   0.0117
  -4.500  -0.0917   0.02251   0.01951  -0.0899   0.9731   0.0118
  -3.000   0.0955   0.00891   0.00424  -0.0958   0.9396   0.0130
  -2.750   0.1265   0.00856   0.00380  -0.0961   0.9296   0.0122
  -2.250   0.1826   0.00734   0.00236  -0.0957   0.9006   0.0116
  -2.000   0.2100   0.00694   0.00183  -0.0954   0.8845   0.0120
  -1.750   0.2374   0.00658   0.00128  -0.0950   0.8679   0.0141
  -1.500   0.2645   0.00648   0.00108  -0.0946   0.8507   0.0158
  -1.250   0.2915   0.00642   0.00094  -0.0943   0.8334   0.0184
  -1.000   0.3183   0.00617   0.00081  -0.0940   0.8148   0.0825
  -0.750   0.3447   0.00583   0.00075  -0.0938   0.7952   0.2086
  -0.500   0.3709   0.00550   0.00075  -0.0936   0.7749   0.3530
  -0.250   0.3970   0.00533   0.00077  -0.0933   0.7527   0.4571
   0.000   0.4226   0.00497   0.00082  -0.0930   0.7304   0.6310
   0.250   0.4456   0.00423   0.00087  -0.0915   0.7095   1.0000
   0.500   0.4723   0.00435   0.00087  -0.0912   0.6877   1.0000
   0.750   0.4989   0.00448   0.00089  -0.0909   0.6662   1.0000
   1.000   0.5255   0.00462   0.00091  -0.0905   0.6440   1.0000
   1.250   0.5522   0.00476   0.00095  -0.0902   0.6213   1.0000
   1.500   0.5786   0.00492   0.00099  -0.0899   0.5970   1.0000
   1.750   0.6050   0.00509   0.00104  -0.0895   0.5705   1.0000
   2.000   0.6314   0.00528   0.00111  -0.0892   0.5439   1.0000
   2.250   0.6578   0.00546   0.00118  -0.0889   0.5184   1.0000
   2.500   0.6844   0.00563   0.00127  -0.0886   0.4949   1.0000
   2.750   0.7108   0.00583   0.00137  -0.0883   0.4695   1.0000
   3.000   0.7372   0.00603   0.00147  -0.0880   0.4460   1.0000
   3.250   0.7636   0.00624   0.00159  -0.0878   0.4218   1.0000
   3.500   0.7897   0.00647   0.00173  -0.0875   0.3954   1.0000
   3.750   0.8155   0.00674   0.00188  -0.0871   0.3655   1.0000
   4.000   0.8412   0.00703   0.00204  -0.0867   0.3336   1.0000
   4.250   0.8671   0.00730   0.00221  -0.0864   0.3077   1.0000
   4.500   0.8924   0.00764   0.00241  -0.0860   0.2749   1.0000
   4.750   0.9171   0.00805   0.00266  -0.0856   0.2353   1.0000
   5.000   0.9416   0.00849   0.00292  -0.0851   0.1984   1.0000
   5.250   0.9666   0.00887   0.00317  -0.0846   0.1704   1.0000
   5.500   0.9908   0.00935   0.00348  -0.0841   0.1360   1.0000
   5.750   1.0148   0.00984   0.00381  -0.0836   0.1048   1.0000
   6.000   1.0377   0.01048   0.00425  -0.0829   0.0672   1.0000
   6.250   1.0605   0.01114   0.00472  -0.0822   0.0370   1.0000
   6.500   1.0830   0.01185   0.00529  -0.0814   0.0132   1.0000
   6.750   1.1066   0.01243   0.00583  -0.0806   0.0057   1.0000
   7.000   1.1310   0.01286   0.00632  -0.0800   0.0049   1.0000
   7.250   1.1547   0.01340   0.00692  -0.0793   0.0042   1.0000
   7.500   1.1774   0.01408   0.00772  -0.0784   0.0037   1.0000
   7.750   1.1988   0.01494   0.00873  -0.0773   0.0035   1.0000
   8.000   1.2188   0.01595   0.00988  -0.0759   0.0034   1.0000
   8.250   1.2377   0.01705   0.01113  -0.0745   0.0033   1.0000
   8.500   1.2562   0.01815   0.01234  -0.0730   0.0034   1.0000
   8.750   1.2738   0.01934   0.01365  -0.0714   0.0034   1.0000
   9.000   1.2916   0.02045   0.01488  -0.0699   0.0034   1.0000
   9.250   1.3090   0.02160   0.01613  -0.0684   0.0035   1.0000
   9.500   1.3260   0.02275   0.01742  -0.0668   0.0035   1.0000
   9.750   1.3421   0.02399   0.01879  -0.0652   0.0036   1.0000
  10.000   1.3564   0.02549   0.02047  -0.0632   0.0038   1.0000
  10.250   1.3551   0.03038   0.02587  -0.0589   0.0048   1.0000
  10.500   1.3443   0.03638   0.03235  -0.0545   0.0055   1.0000
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