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SA7024 (sa7024-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SA7024 (sa7024-il)
Reynolds number: 200,000
Max Cl/Cd: 74.62 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7024-il-200000-n5.txt
Download as CSV file: xf-sa7024-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3840   0.09396   0.09051  -0.0271   1.0000   0.0237
  -7.750  -0.3848   0.09120   0.08781  -0.0273   1.0000   0.0237
  -7.500  -0.3876   0.08849   0.08517  -0.0274   1.0000   0.0238
  -7.250  -0.3860   0.08525   0.08198  -0.0287   1.0000   0.0238
  -7.000  -0.3830   0.08186   0.07863  -0.0305   1.0000   0.0238
  -6.750  -0.3789   0.07822   0.07502  -0.0327   1.0000   0.0238
  -6.500  -0.3735   0.07451   0.07132  -0.0349   1.0000   0.0238
  -6.250  -0.3702   0.06972   0.06658  -0.0373   1.0000   0.0240
  -6.000  -0.3697   0.06431   0.06116  -0.0395   1.0000   0.0245
  -5.750  -0.3626   0.06004   0.05686  -0.0413   0.9999   0.0248
  -5.500  -0.3282   0.05341   0.05007  -0.0498   0.9958   0.0250
  -5.250  -0.3038   0.04992   0.04654  -0.0524   0.9920   0.0196
  -5.000  -0.2550   0.03727   0.03321  -0.0639   0.9869   0.0153
  -4.750  -0.2229   0.03406   0.02981  -0.0685   0.9831   0.0171
  -4.500  -0.1900   0.03104   0.02647  -0.0716   0.9781   0.0191
  -4.250  -0.1520   0.02471   0.01928  -0.0749   0.9736   0.0167
  -4.000  -0.1145   0.02168   0.01563  -0.0770   0.9702   0.0157
  -3.750  -0.0822   0.02006   0.01365  -0.0779   0.9647   0.0153
  -3.250  -0.0123   0.01691   0.00986  -0.0809   0.9564   0.0149
  -3.000   0.0183   0.01556   0.00832  -0.0813   0.9495   0.0149
  -2.750   0.0535   0.01437   0.00694  -0.0827   0.9447   0.0150
  -2.500   0.0862   0.01325   0.00573  -0.0836   0.9380   0.0153
  -2.250   0.1210   0.01241   0.00478  -0.0849   0.9315   0.0161
  -2.000   0.1539   0.01185   0.00411  -0.0858   0.9230   0.0178
  -1.750   0.1898   0.01142   0.00359  -0.0873   0.9159   0.0220
  -1.500   0.2218   0.01098   0.00315  -0.0880   0.9054   0.0380
  -1.250   0.2539   0.01016   0.00289  -0.0891   0.8950   0.1902
  -1.000   0.2855   0.00952   0.00275  -0.0901   0.8834   0.3566
  -0.750   0.3161   0.00906   0.00265  -0.0906   0.8701   0.4863
  -0.500   0.3357   0.00807   0.00264  -0.0881   0.8550   0.7987
  -0.250   0.3744   0.00778   0.00241  -0.0897   0.8390   1.0000
   0.000   0.4038   0.00782   0.00228  -0.0897   0.8212   1.0000
   0.250   0.4318   0.00789   0.00220  -0.0895   0.8018   1.0000
   0.500   0.4595   0.00797   0.00214  -0.0892   0.7820   1.0000
   0.750   0.4866   0.00808   0.00210  -0.0888   0.7611   1.0000
   1.000   0.5133   0.00820   0.00208  -0.0883   0.7395   1.0000
   1.250   0.5397   0.00834   0.00209  -0.0878   0.7164   1.0000
   1.500   0.5657   0.00851   0.00213  -0.0872   0.6923   1.0000
   1.750   0.5916   0.00869   0.00217  -0.0866   0.6678   1.0000
   2.250   0.6429   0.00908   0.00232  -0.0855   0.6189   1.0000
   2.500   0.6684   0.00929   0.00246  -0.0849   0.5947   1.0000
   2.750   0.6937   0.00953   0.00259  -0.0843   0.5698   1.0000
   3.000   0.7188   0.00978   0.00273  -0.0836   0.5435   1.0000
   3.250   0.7436   0.01005   0.00289  -0.0830   0.5155   1.0000
   3.500   0.7684   0.01034   0.00308  -0.0823   0.4872   1.0000
   3.750   0.7932   0.01064   0.00333  -0.0817   0.4599   1.0000
   4.000   0.8178   0.01096   0.00356  -0.0811   0.4329   1.0000
   4.250   0.8424   0.01129   0.00382  -0.0805   0.4068   1.0000
   4.500   0.8668   0.01164   0.00410  -0.0799   0.3807   1.0000
   4.750   0.8911   0.01201   0.00441  -0.0793   0.3540   1.0000
   5.000   0.9151   0.01242   0.00474  -0.0786   0.3246   1.0000
   5.250   0.9385   0.01289   0.00517  -0.0779   0.2916   1.0000
   5.500   0.9615   0.01341   0.00557  -0.0772   0.2571   1.0000
   5.750   0.9832   0.01409   0.00602  -0.0764   0.2091   1.0000
   6.000   1.0050   0.01480   0.00653  -0.0756   0.1673   1.0000
   6.250   1.0279   0.01539   0.00705  -0.0749   0.1406   1.0000
   6.500   1.0493   0.01618   0.00766  -0.0741   0.1042   1.0000
   6.750   1.0704   0.01701   0.00839  -0.0732   0.0732   1.0000
   7.000   1.0911   0.01789   0.00916  -0.0723   0.0473   1.0000
   7.250   1.1104   0.01897   0.01011  -0.0711   0.0217   1.0000
   7.500   1.1299   0.02004   0.01118  -0.0699   0.0119   1.0000
   7.750   1.1503   0.02097   0.01226  -0.0687   0.0094   1.0000
   8.000   1.1698   0.02197   0.01337  -0.0675   0.0074   1.0000
   8.250   1.1879   0.02311   0.01466  -0.0662   0.0063   1.0000
   8.500   1.2058   0.02422   0.01597  -0.0648   0.0058   1.0000
   8.750   1.2223   0.02546   0.01746  -0.0632   0.0055   1.0000
   9.000   1.2370   0.02683   0.01903  -0.0614   0.0053   1.0000
   9.250   1.2500   0.02832   0.02071  -0.0595   0.0051   1.0000
   9.500   1.2614   0.02992   0.02251  -0.0574   0.0049   1.0000
   9.750   1.2711   0.03166   0.02445  -0.0552   0.0048   1.0000
  10.000   1.2785   0.03348   0.02646  -0.0528   0.0047   1.0000
  10.250   1.2831   0.03539   0.02858  -0.0501   0.0046   1.0000
  10.500   1.2859   0.03746   0.03086  -0.0473   0.0046   1.0000
  10.750   1.2869   0.03973   0.03335  -0.0447   0.0045   1.0000
  11.000   1.2860   0.04222   0.03608  -0.0424   0.0045   1.0000
  11.250   1.2828   0.04503   0.03913  -0.0403   0.0045   1.0000
  11.500   1.2779   0.04811   0.04246  -0.0388   0.0045   1.0000
  11.750   1.2706   0.05165   0.04626  -0.0377   0.0045   1.0000
  12.000   1.2615   0.05557   0.05044  -0.0374   0.0045   1.0000
  12.250   1.2503   0.06010   0.05521  -0.0380   0.0045   1.0000
  12.500   1.2379   0.06518   0.06054  -0.0394   0.0045   1.0000
  12.750   1.2232   0.07106   0.06666  -0.0418   0.0045   1.0000
  13.000   1.2081   0.07757   0.07338  -0.0451   0.0045   1.0000
  13.250   1.1917   0.08487   0.08090  -0.0493   0.0046   1.0000
  13.500   1.1740   0.09302   0.08925  -0.0543   0.0046   1.0000
  13.750   1.1562   0.10180   0.09821  -0.0598   0.0046   1.0000
  14.000   1.1373   0.11151   0.10809  -0.0660   0.0047   1.0000
  14.250   1.1185   0.12188   0.11860  -0.0724   0.0047   1.0000
  14.500   1.0984   0.13329   0.13013  -0.0794   0.0048   1.0000
  14.750   1.0769   0.14606   0.14299  -0.0868   0.0050   1.0000
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