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SA7024 (sa7024-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SA7024 (sa7024-il)
Reynolds number: 50,000
Max Cl/Cd: 38.8 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7024-il-50000.txt
Download as CSV file: xf-sa7024-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3969   0.10038   0.09385  -0.0181   1.0000   0.1904
  -7.250  -0.3832   0.09585   0.08935  -0.0168   1.0000   0.1982
  -7.000  -0.3993   0.09546   0.08914  -0.0176   1.0000   0.2046
  -6.750  -0.3858   0.09104   0.08475  -0.0153   1.0000   0.2143
  -6.250  -0.3972   0.08758   0.08155  -0.0191   1.0000   0.2331
  -6.000  -0.3878   0.08382   0.07784  -0.0164   1.0000   0.2460
  -5.750  -0.3806   0.08050   0.07459  -0.0144   1.0000   0.2581
  -5.500  -0.3804   0.07808   0.07221  -0.0149   1.0000   0.2736
  -5.250  -0.3788   0.07559   0.06981  -0.0155   1.0000   0.2893
  -4.750  -0.3701   0.07023   0.06459  -0.0122   1.0000   0.3310
  -4.500  -0.3663   0.06764   0.06209  -0.0090   1.0000   0.3588
  -4.000  -0.3577   0.06209   0.05672   0.0015   1.0000   0.4209
  -3.250  -0.1770   0.03771   0.02986  -0.0568   1.0000   0.1335
  -3.000  -0.1429   0.03377   0.02527  -0.0588   1.0000   0.1191
  -2.750  -0.1112   0.03060   0.02150  -0.0599   1.0000   0.1121
  -2.500  -0.0792   0.02838   0.01845  -0.0602   1.0000   0.1084
  -2.250  -0.0517   0.02625   0.01602  -0.0600   1.0000   0.1096
  -2.000  -0.0260   0.02466   0.01424  -0.0595   1.0000   0.1156
  -1.750  -0.0003   0.02342   0.01284  -0.0589   1.0000   0.1304
  -1.500   0.0261   0.02222   0.01147  -0.0580   1.0000   0.1506
  -1.250   0.0612   0.01849   0.00990  -0.0587   1.0000   0.4863
  -1.000   0.0719   0.01696   0.00902  -0.0538   1.0000   1.0000
  -0.750   0.0949   0.01726   0.00875  -0.0534   1.0000   1.0000
  -0.500   0.1169   0.01760   0.00864  -0.0530   1.0000   1.0000
  -0.250   0.1382   0.01799   0.00871  -0.0527   1.0000   1.0000
   0.000   0.1589   0.01844   0.00888  -0.0523   1.0000   1.0000
   0.250   0.1789   0.01894   0.00915  -0.0520   1.0000   1.0000
   0.500   0.1985   0.01949   0.00948  -0.0518   1.0000   1.0000
   0.750   0.2174   0.02012   0.00994  -0.0515   1.0000   1.0000
   1.000   0.2357   0.02081   0.01050  -0.0514   1.0000   1.0000
   1.250   0.2534   0.02157   0.01116  -0.0512   1.0000   1.0000
   1.500   0.2706   0.02242   0.01192  -0.0512   1.0000   1.0000
   1.750   0.3124   0.02364   0.01304  -0.0559   0.9872   1.0000
   2.000   0.3696   0.02486   0.01420  -0.0629   0.9655   1.0000
   2.250   0.4270   0.02584   0.01517  -0.0694   0.9441   1.0000
   2.500   0.4759   0.02654   0.01593  -0.0740   0.9207   1.0000
   2.750   0.5269   0.02709   0.01654  -0.0786   0.8977   1.0000
   3.000   0.5834   0.02733   0.01691  -0.0835   0.8755   1.0000
   3.250   0.6296   0.02746   0.01723  -0.0863   0.8508   1.0000
   3.500   0.6806   0.02728   0.01724  -0.0892   0.8266   1.0000
   3.750   0.7311   0.02681   0.01697  -0.0913   0.8027   1.0000
   4.000   0.7812   0.02607   0.01651  -0.0926   0.7786   1.0000
   4.250   0.8200   0.02560   0.01622  -0.0922   0.7514   1.0000
   4.500   0.8528   0.02533   0.01610  -0.0909   0.7216   1.0000
   4.750   0.8828   0.02517   0.01606  -0.0891   0.6897   1.0000
   5.000   0.9138   0.02492   0.01597  -0.0872   0.6568   1.0000
   5.250   0.9395   0.02504   0.01616  -0.0850   0.6211   1.0000
   5.500   0.9665   0.02513   0.01623  -0.0827   0.5850   1.0000
   5.750   0.9896   0.02553   0.01665  -0.0804   0.5462   1.0000
   6.000   1.0119   0.02608   0.01718  -0.0781   0.5063   1.0000
   6.250   1.0335   0.02671   0.01784  -0.0757   0.4650   1.0000
   6.500   1.0541   0.02743   0.01846  -0.0733   0.4223   1.0000
   6.750   1.0737   0.02829   0.01915  -0.0709   0.3784   1.0000
   7.000   1.0909   0.02945   0.02025  -0.0684   0.3339   1.0000
   7.250   1.1076   0.03080   0.02150  -0.0660   0.2900   1.0000
   7.500   1.1250   0.03259   0.02318  -0.0638   0.2492   1.0000
   7.750   1.1419   0.03451   0.02492  -0.0618   0.2119   1.0000
   8.000   1.1572   0.03670   0.02716  -0.0596   0.1794   1.0000
   8.250   1.1743   0.03964   0.03027  -0.0576   0.1526   1.0000
   8.500   1.1869   0.04241   0.03311  -0.0553   0.1269   1.0000
   8.750   1.1991   0.04552   0.03619  -0.0532   0.1055   1.0000
   9.000   1.2073   0.04875   0.03974  -0.0509   0.0911   1.0000
   9.250   1.2222   0.05286   0.04383  -0.0497   0.0817   1.0000
   9.500   1.2227   0.05740   0.04915  -0.0469   0.0799   1.0000
   9.750   1.2185   0.06214   0.05449  -0.0444   0.0786   1.0000
  10.000   1.2099   0.06691   0.05973  -0.0422   0.0780   1.0000
  10.250   1.1967   0.07164   0.06484  -0.0402   0.0780   1.0000
  10.500   1.1789   0.07622   0.06969  -0.0384   0.0784   1.0000
  10.750   1.1588   0.08082   0.07448  -0.0372   0.0791   1.0000
  11.000   1.1387   0.08588   0.07969  -0.0372   0.0799   1.0000
  11.250   1.1200   0.09153   0.08546  -0.0385   0.0807   1.0000
  11.500   1.1043   0.09772   0.09172  -0.0406   0.0814   1.0000
  11.750   1.0038   0.12455   0.11851  -0.0654   0.1172   1.0000
  12.000   0.9854   0.13662   0.13048  -0.0731   0.1359   1.0000
  12.250   0.9828   0.14312   0.13696  -0.0755   0.1351   1.0000
  12.500   0.9871   0.14921   0.14304  -0.0765   0.1334   1.0000
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