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SA7024 (sa7024-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SA7024 (sa7024-il)
Reynolds number: 50,000
Max Cl/Cd: 42.26 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7024-il-50000-n5.txt
Download as CSV file: xf-sa7024-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3868   0.09629   0.08967  -0.0224   1.0000   0.1097
  -7.250  -0.3944   0.09451   0.08803  -0.0234   1.0000   0.1138
  -7.000  -0.4030   0.09274   0.08644  -0.0298   1.0000   0.1159
  -6.750  -0.3928   0.08829   0.08202  -0.0266   1.0000   0.1173
  -6.500  -0.3864   0.08493   0.07871  -0.0263   1.0000   0.1189
  -6.250  -0.3813   0.08170   0.07554  -0.0271   1.0000   0.1202
  -6.000  -0.3675   0.07339   0.06713  -0.0379   1.0000   0.0631
  -5.500  -0.3405   0.06343   0.05697  -0.0447   1.0000   0.0475
  -5.250  -0.3297   0.05990   0.05343  -0.0451   1.0000   0.0462
  -5.000  -0.3152   0.05594   0.04938  -0.0469   1.0000   0.0448
  -4.750  -0.2973   0.05170   0.04490  -0.0493   1.0000   0.0433
  -4.500  -0.2762   0.04732   0.04026  -0.0519   1.0000   0.0419
  -4.250  -0.2521   0.04297   0.03553  -0.0544   1.0000   0.0405
  -4.000  -0.2260   0.03891   0.03100  -0.0565   1.0000   0.0395
  -3.750  -0.1988   0.03534   0.02688  -0.0580   1.0000   0.0387
  -3.500  -0.1731   0.03270   0.02379  -0.0587   1.0000   0.0396
  -3.250  -0.1476   0.03059   0.02128  -0.0591   1.0000   0.0423
  -3.000  -0.1210   0.02859   0.01879  -0.0592   1.0000   0.0449
  -2.750  -0.0946   0.02679   0.01651  -0.0589   1.0000   0.0466
  -2.500  -0.0690   0.02525   0.01458  -0.0583   1.0000   0.0477
  -2.250  -0.0448   0.02387   0.01294  -0.0576   1.0000   0.0496
  -2.000  -0.0209   0.02283   0.01176  -0.0569   1.0000   0.0530
  -1.750   0.0043   0.02202   0.01069  -0.0563   1.0000   0.0586
  -1.500   0.0302   0.02127   0.00980  -0.0562   1.0000   0.0683
  -1.250   0.0581   0.02021   0.00911  -0.0567   1.0000   0.1344
  -1.000   0.0757   0.01746   0.00912  -0.0547   1.0000   0.7132
  -0.750   0.1158   0.01732   0.00861  -0.0572   0.9875   1.0000
  -0.500   0.1577   0.01766   0.00845  -0.0603   0.9760   1.0000
  -0.250   0.1986   0.01796   0.00836  -0.0633   0.9638   1.0000
   0.000   0.2388   0.01821   0.00830  -0.0660   0.9511   1.0000
   0.250   0.2786   0.01843   0.00825  -0.0685   0.9382   1.0000
   0.500   0.3179   0.01862   0.00824  -0.0709   0.9250   1.0000
   0.750   0.3569   0.01876   0.00824  -0.0731   0.9115   1.0000
   1.000   0.3958   0.01888   0.00824  -0.0752   0.8978   1.0000
   1.250   0.4346   0.01895   0.00824  -0.0771   0.8836   1.0000
   1.500   0.4718   0.01900   0.00824  -0.0786   0.8685   1.0000
   1.750   0.5080   0.01902   0.00823  -0.0798   0.8526   1.0000
   2.000   0.5440   0.01901   0.00824  -0.0808   0.8363   1.0000
   2.250   0.5777   0.01902   0.00825  -0.0813   0.8185   1.0000
   2.500   0.6090   0.01906   0.00832  -0.0814   0.7987   1.0000
   2.750   0.6425   0.01904   0.00832  -0.0817   0.7798   1.0000
   3.000   0.6710   0.01914   0.00851  -0.0812   0.7571   1.0000
   3.250   0.7006   0.01921   0.00861  -0.0808   0.7344   1.0000
   3.500   0.7300   0.01930   0.00871  -0.0803   0.7106   1.0000
   3.750   0.7575   0.01946   0.00890  -0.0795   0.6849   1.0000
   4.000   0.7841   0.01967   0.00922  -0.0786   0.6579   1.0000
   4.250   0.8101   0.01992   0.00950  -0.0776   0.6303   1.0000
   4.500   0.8354   0.02023   0.00982  -0.0765   0.6017   1.0000
   4.750   0.8597   0.02060   0.01023  -0.0754   0.5715   1.0000
   5.000   0.8834   0.02101   0.01067  -0.0741   0.5403   1.0000
   5.250   0.9068   0.02147   0.01114  -0.0729   0.5088   1.0000
   5.500   0.9293   0.02199   0.01180  -0.0716   0.4764   1.0000
   5.750   0.9512   0.02258   0.01243  -0.0702   0.4434   1.0000
   6.000   0.9728   0.02323   0.01308  -0.0689   0.4110   1.0000
   6.250   0.9935   0.02396   0.01387  -0.0676   0.3772   1.0000
   6.500   1.0133   0.02476   0.01468  -0.0661   0.3435   1.0000
   6.750   1.0322   0.02564   0.01560  -0.0646   0.3081   1.0000
   7.000   1.0498   0.02663   0.01665  -0.0631   0.2735   1.0000
   7.250   1.0670   0.02772   0.01781  -0.0616   0.2386   1.0000
   7.500   1.0832   0.02897   0.01905  -0.0600   0.2071   1.0000
   7.750   1.0987   0.03038   0.02049  -0.0585   0.1761   1.0000
   8.000   1.1131   0.03199   0.02214  -0.0568   0.1475   1.0000
   8.250   1.1253   0.03376   0.02391  -0.0551   0.1200   1.0000
   8.500   1.1358   0.03589   0.02604  -0.0531   0.0962   1.0000
   8.750   1.1425   0.03820   0.02824  -0.0511   0.0748   1.0000
   9.000   1.1489   0.04052   0.03069  -0.0492   0.0548   1.0000
   9.250   1.1542   0.04296   0.03323  -0.0473   0.0431   1.0000
   9.500   1.1576   0.04569   0.03604  -0.0451   0.0376   1.0000
   9.750   1.1637   0.04834   0.03915  -0.0430   0.0327   1.0000
  10.000   1.1648   0.05096   0.04189  -0.0411   0.0298   1.0000
  10.250   1.1646   0.05410   0.04516  -0.0394   0.0278   1.0000
  10.500   1.1670   0.05748   0.04897  -0.0379   0.0264   1.0000
  10.750   1.1652   0.06126   0.05312  -0.0367   0.0256   1.0000
  11.000   1.1593   0.06537   0.05758  -0.0360   0.0251   1.0000
  11.250   1.1496   0.06996   0.06248  -0.0360   0.0248   1.0000
  11.500   1.1373   0.07501   0.06782  -0.0371   0.0247   1.0000
  11.750   1.1225   0.08077   0.07384  -0.0391   0.0246   1.0000
  12.000   1.1061   0.08723   0.08053  -0.0423   0.0248   1.0000
  12.250   1.0886   0.09453   0.08803  -0.0466   0.0250   1.0000
  12.500   1.0710   0.10260   0.09628  -0.0516   0.0254   1.0000
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