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SA7024 (sa7024-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SA7024 (sa7024-il)
Reynolds number: 500,000
Max Cl/Cd: 93.93 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7024-il-500000-n5.txt
Download as CSV file: xf-sa7024-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3845   0.08580   0.08363  -0.0241   1.0000   0.0087
  -7.500  -0.3883   0.08315   0.08101  -0.0237   1.0000   0.0087
  -7.250  -0.3949   0.08077   0.07869  -0.0227   1.0000   0.0087
  -7.000  -0.3957   0.07769   0.07564  -0.0235   1.0000   0.0087
  -6.750  -0.3836   0.07308   0.07104  -0.0286   0.9985   0.0087
  -6.500  -0.3571   0.06713   0.06507  -0.0379   0.9950   0.0087
  -6.250  -0.3296   0.06089   0.05879  -0.0471   0.9909   0.0087
  -6.000  -0.2988   0.05419   0.05201  -0.0568   0.9862   0.0087
  -5.750  -0.2662   0.04504   0.04267  -0.0687   0.9823   0.0080
  -5.500  -0.2359   0.03739   0.03477  -0.0756   0.9754   0.0079
  -5.250  -0.2008   0.02976   0.02672  -0.0814   0.9711   0.0080
  -5.000  -0.1692   0.02507   0.02161  -0.0839   0.9663   0.0085
  -4.750  -0.1389   0.02097   0.01695  -0.0859   0.9606   0.0090
  -4.500  -0.1069   0.01751   0.01299  -0.0881   0.9570   0.0099
  -4.250  -0.0777   0.01633   0.01161  -0.0888   0.9504   0.0107
  -4.000  -0.0444   0.01420   0.00908  -0.0899   0.9451   0.0101
  -3.750  -0.0121   0.01289   0.00751  -0.0906   0.9382   0.0097
  -3.500   0.0216   0.01193   0.00636  -0.0917   0.9308   0.0094
  -3.250   0.0533   0.01111   0.00541  -0.0924   0.9209   0.0093
  -3.000   0.0848   0.01040   0.00456  -0.0930   0.9100   0.0092
  -2.750   0.1149   0.00976   0.00380  -0.0934   0.8974   0.0092
  -2.500   0.1440   0.00921   0.00314  -0.0935   0.8834   0.0093
  -2.250   0.1724   0.00878   0.00259  -0.0934   0.8680   0.0094
  -2.000   0.2003   0.00844   0.00212  -0.0932   0.8514   0.0099
  -1.750   0.2277   0.00823   0.00174  -0.0929   0.8330   0.0109
  -1.500   0.2548   0.00810   0.00149  -0.0925   0.8129   0.0125
  -1.250   0.2816   0.00804   0.00130  -0.0921   0.7932   0.0142
  -1.000   0.3084   0.00787   0.00117  -0.0918   0.7732   0.0469
  -0.750   0.3347   0.00756   0.00107  -0.0916   0.7533   0.1466
  -0.500   0.3612   0.00737   0.00102  -0.0914   0.7329   0.2304
  -0.250   0.3873   0.00715   0.00103  -0.0911   0.7121   0.3428
   0.000   0.4132   0.00690   0.00107  -0.0909   0.6905   0.4743
   0.250   0.4336   0.00610   0.00120  -0.0894   0.6690   0.7953
   0.500   0.4609   0.00587   0.00116  -0.0887   0.6445   1.0000
   0.750   0.4871   0.00603   0.00118  -0.0883   0.6198   1.0000
   1.000   0.5134   0.00619   0.00120  -0.0879   0.5964   1.0000
   1.250   0.5396   0.00636   0.00124  -0.0875   0.5746   1.0000
   1.500   0.5661   0.00652   0.00130  -0.0872   0.5527   1.0000
   1.750   0.5923   0.00669   0.00136  -0.0868   0.5305   1.0000
   2.000   0.6185   0.00689   0.00144  -0.0864   0.5075   1.0000
   2.250   0.6445   0.00710   0.00153  -0.0861   0.4809   1.0000
   2.500   0.6704   0.00733   0.00165  -0.0857   0.4533   1.0000
   2.750   0.6964   0.00756   0.00177  -0.0853   0.4282   1.0000
   3.000   0.7225   0.00779   0.00190  -0.0850   0.4046   1.0000
   3.250   0.7484   0.00803   0.00205  -0.0846   0.3818   1.0000
   3.500   0.7745   0.00826   0.00220  -0.0843   0.3600   1.0000
   3.750   0.8003   0.00852   0.00240  -0.0840   0.3363   1.0000
   4.250   0.8512   0.00913   0.00281  -0.0832   0.2844   1.0000
   4.500   0.8739   0.00979   0.00311  -0.0825   0.2197   1.0000
   4.750   0.8977   0.01031   0.00342  -0.0820   0.1762   1.0000
   5.000   0.9224   0.01072   0.00371  -0.0815   0.1493   1.0000
   5.250   0.9465   0.01121   0.00409  -0.0810   0.1185   1.0000
   5.500   0.9702   0.01174   0.00447  -0.0804   0.0895   1.0000
   5.750   0.9923   0.01251   0.00499  -0.0796   0.0483   1.0000
   6.000   1.0154   0.01313   0.00549  -0.0790   0.0256   1.0000
   6.250   1.0377   0.01387   0.00612  -0.0781   0.0062   1.0000
   6.500   1.0614   0.01440   0.00667  -0.0775   0.0040   1.0000
   6.750   1.0856   0.01486   0.00723  -0.0768   0.0036   1.0000
   7.000   1.1094   0.01534   0.00780  -0.0762   0.0033   1.0000
   7.250   1.1328   0.01589   0.00845  -0.0755   0.0031   1.0000
   7.500   1.1556   0.01649   0.00917  -0.0746   0.0029   1.0000
   7.750   1.1776   0.01719   0.00998  -0.0737   0.0027   1.0000
   8.000   1.1989   0.01797   0.01087  -0.0727   0.0026   1.0000
   8.250   1.2194   0.01881   0.01184  -0.0716   0.0025   1.0000
   8.500   1.2386   0.01978   0.01297  -0.0703   0.0024   1.0000
   8.750   1.2570   0.02080   0.01413  -0.0690   0.0023   1.0000
   9.000   1.2741   0.02193   0.01540  -0.0674   0.0023   1.0000
   9.250   1.2899   0.02317   0.01678  -0.0658   0.0023   1.0000
   9.500   1.3045   0.02449   0.01825  -0.0639   0.0022   1.0000
   9.750   1.3174   0.02594   0.01986  -0.0620   0.0022   1.0000
  10.000   1.3289   0.02745   0.02154  -0.0598   0.0022   1.0000
  10.250   1.3385   0.02909   0.02336  -0.0575   0.0022   1.0000
  10.500   1.3445   0.03077   0.02522  -0.0548   0.0022   1.0000
  10.750   1.3471   0.03255   0.02719  -0.0516   0.0022   1.0000
  11.000   1.3477   0.03448   0.02932  -0.0485   0.0022   1.0000
  11.250   1.3459   0.03669   0.03173  -0.0456   0.0022   1.0000
  11.500   1.3427   0.03909   0.03437  -0.0431   0.0022   1.0000
  11.750   1.3371   0.04190   0.03740  -0.0410   0.0022   1.0000
  12.000   1.3299   0.04504   0.04075  -0.0395   0.0022   1.0000
  12.250   1.3206   0.04870   0.04463  -0.0388   0.0022   1.0000
  12.500   1.3100   0.05287   0.04901  -0.0389   0.0022   1.0000
  12.750   1.2970   0.05778   0.05414  -0.0399   0.0023   1.0000
  13.000   1.2840   0.06318   0.05973  -0.0418   0.0023   1.0000
  13.250   1.2693   0.06940   0.06615  -0.0447   0.0023   1.0000
  13.500   1.2523   0.07661   0.07356  -0.0486   0.0023   1.0000
  13.750   1.2362   0.08422   0.08134  -0.0531   0.0023   1.0000
  14.000   1.2181   0.09282   0.09011  -0.0583   0.0023   1.0000
  14.250   1.2008   0.10179   0.09923  -0.0638   0.0023   1.0000
  14.500   1.1822   0.11155   0.10914  -0.0698   0.0023   1.0000
  14.750   1.1642   0.12172   0.11944  -0.0759   0.0024   1.0000
  15.000   1.1453   0.13256   0.13037  -0.0823   0.0024   1.0000
  15.250   1.1268   0.14386   0.14178  -0.0889   0.0024   1.0000
  15.500   1.1066   0.15642   0.15443  -0.0959   0.0025   1.0000
  15.750   1.0814   0.17186   0.16994  -0.1040   0.0025   1.0000
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