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

SA7024 (sa7024-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SA7024 (sa7024-il)
Reynolds number: 200,000
Max Cl/Cd: 80.53 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7024-il-200000.txt
Download as CSV file: xf-sa7024-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3780   0.08792   0.08454  -0.0237   1.0000   0.0340
  -7.250  -0.3803   0.08551   0.08219  -0.0233   1.0000   0.0349
  -7.000  -0.3846   0.08317   0.07992  -0.0228   1.0000   0.0356
  -6.750  -0.3848   0.08030   0.07711  -0.0237   1.0000   0.0366
  -6.500  -0.3835   0.07729   0.07414  -0.0254   1.0000   0.0377
  -6.250  -0.3796   0.07388   0.07077  -0.0290   1.0000   0.0393
  -6.000  -0.3646   0.06965   0.06649  -0.0382   1.0000   0.0408
  -5.750  -0.3506   0.06569   0.06242  -0.0428   1.0000   0.0412
  -5.500  -0.3465   0.05939   0.05608  -0.0453   1.0000   0.0419
  -5.250  -0.3443   0.05668   0.05347  -0.0425   1.0000   0.0430
  -5.000  -0.3368   0.05439   0.05120  -0.0412   1.0000   0.0445
  -4.750  -0.3241   0.05151   0.04827  -0.0419   1.0000   0.0465
  -4.500  -0.3047   0.04774   0.04436  -0.0445   1.0000   0.0502
  -4.250  -0.2733   0.04155   0.03767  -0.0508   1.0000   0.0557
  -4.000  -0.2599   0.03936   0.03553  -0.0500   1.0000   0.0581
  -3.750  -0.2167   0.03527   0.03103  -0.0559   0.9967   0.0700
  -3.500  -0.1746   0.03214   0.02754  -0.0606   0.9930   0.0830
  -3.250  -0.1348   0.02957   0.02468  -0.0643   0.9884   0.0965
  -3.000  -0.0861   0.02325   0.01744  -0.0664   0.9865   0.0516
  -2.750  -0.0428   0.01924   0.01270  -0.0682   0.9845   0.0363
  -2.500  -0.0019   0.01705   0.01003  -0.0700   0.9811   0.0328
  -2.250   0.0367   0.01563   0.00838  -0.0717   0.9755   0.0323
  -2.000   0.0787   0.01451   0.00719  -0.0743   0.9712   0.0344
  -1.750   0.1165   0.01389   0.00653  -0.0762   0.9642   0.0404
  -1.500   0.1584   0.01296   0.00557  -0.0789   0.9588   0.0478
  -1.250   0.1968   0.01129   0.00499  -0.0815   0.9534   0.3403
  -1.000   0.2290   0.01005   0.00497  -0.0824   0.9467   0.6826
  -0.750   0.2745   0.00934   0.00466  -0.0849   0.9434   1.0000
  -0.500   0.3124   0.00920   0.00435  -0.0867   0.9338   1.0000
  -0.250   0.3530   0.00903   0.00404  -0.0889   0.9260   1.0000
   0.000   0.3925   0.00885   0.00375  -0.0909   0.9173   1.0000
   0.250   0.4270   0.00872   0.00353  -0.0918   0.9054   1.0000
   0.500   0.4607   0.00860   0.00333  -0.0926   0.8923   1.0000
   0.750   0.4929   0.00852   0.00316  -0.0930   0.8777   1.0000
   1.000   0.5240   0.00846   0.00302  -0.0931   0.8617   1.0000
   1.250   0.5517   0.00847   0.00297  -0.0926   0.8420   1.0000
   1.500   0.5797   0.00850   0.00290  -0.0922   0.8220   1.0000
   1.750   0.6064   0.00857   0.00289  -0.0915   0.7999   1.0000
   2.000   0.6332   0.00867   0.00288  -0.0908   0.7781   1.0000
   2.250   0.6590   0.00879   0.00292  -0.0901   0.7544   1.0000
   2.500   0.6847   0.00895   0.00301  -0.0893   0.7302   1.0000
   2.750   0.7102   0.00913   0.00310  -0.0885   0.7052   1.0000
   3.000   0.7353   0.00933   0.00320  -0.0877   0.6786   1.0000
   3.250   0.7601   0.00955   0.00332  -0.0868   0.6508   1.0000
   3.500   0.7847   0.00979   0.00347  -0.0859   0.6222   1.0000
   3.750   0.8092   0.01006   0.00368  -0.0851   0.5930   1.0000
   4.000   0.8335   0.01035   0.00388  -0.0842   0.5638   1.0000
   4.250   0.8576   0.01067   0.00411  -0.0834   0.5342   1.0000
   4.500   0.8815   0.01101   0.00436  -0.0825   0.5039   1.0000
   4.750   0.9052   0.01137   0.00469  -0.0816   0.4725   1.0000
   5.000   0.9284   0.01177   0.00499  -0.0807   0.4379   1.0000
   5.250   0.9513   0.01220   0.00533  -0.0798   0.4030   1.0000
   5.500   0.9741   0.01267   0.00570  -0.0789   0.3685   1.0000
   5.750   0.9968   0.01316   0.00612  -0.0780   0.3346   1.0000
   6.000   1.0194   0.01369   0.00658  -0.0771   0.3012   1.0000
   6.250   1.0413   0.01428   0.00712  -0.0762   0.2666   1.0000
   6.500   1.0626   0.01495   0.00764  -0.0752   0.2278   1.0000
   6.750   1.0834   0.01568   0.00820  -0.0743   0.1812   1.0000
   7.000   1.1040   0.01650   0.00884  -0.0734   0.1416   1.0000
   7.250   1.1244   0.01738   0.00961  -0.0723   0.1096   1.0000
   7.500   1.1439   0.01839   0.01046  -0.0713   0.0745   1.0000
   7.750   1.1560   0.02056   0.01238  -0.0689   0.0316   1.0000
   8.000   1.1682   0.02259   0.01451  -0.0664   0.0232   1.0000
   8.250   1.1855   0.02384   0.01589  -0.0647   0.0195   1.0000
   8.500   1.1988   0.02555   0.01767  -0.0628   0.0168   1.0000
   8.750   1.2087   0.02817   0.02045  -0.0603   0.0156   1.0000
   9.000   1.2247   0.03007   0.02254  -0.0585   0.0150   1.0000
   9.250   1.2404   0.03234   0.02503  -0.0568   0.0146   1.0000
   9.500   1.2551   0.03496   0.02792  -0.0550   0.0143   1.0000
   9.750   1.2674   0.03795   0.03125  -0.0531   0.0142   1.0000
  10.000   1.2754   0.04126   0.03492  -0.0509   0.0142   1.0000
  10.250   1.2783   0.04478   0.03882  -0.0484   0.0143   1.0000
  10.500   1.2746   0.04835   0.04275  -0.0453   0.0145   1.0000
  10.750   1.2647   0.05178   0.04655  -0.0419   0.0147   1.0000
  11.000   1.2511   0.05537   0.05042  -0.0390   0.0148   1.0000
  11.250   1.2353   0.05931   0.05461  -0.0370   0.0150   1.0000
  11.500   1.2177   0.06370   0.05925  -0.0361   0.0151   1.0000
  11.750   1.1991   0.06865   0.06442  -0.0365   0.0152   1.0000
  12.000   1.1796   0.07425   0.07018  -0.0381   0.0153   1.0000
  12.250   1.1596   0.08061   0.07674  -0.0410   0.0154   1.0000
  12.500   1.1395   0.08773   0.08402  -0.0450   0.0156   1.0000
  12.750   1.0125   0.09454   0.09121  -0.0451   0.0154   1.0000
  13.000   0.9873   0.10282   0.09965  -0.0501   0.0155   1.0000
<< Back to SA7024 (sa7024-il)

Polar data table (+)

Polar graphs


<< Back to SA7024 (sa7024-il)