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SA7024 (sa7024-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SA7024 (sa7024-il)
Reynolds number: 500,000
Max Cl/Cd: 105.74 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7024-il-500000.txt
Download as CSV file: xf-sa7024-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3818   0.09341   0.09116  -0.0248   1.0000   0.0118
  -8.000  -0.3885   0.08872   0.08653  -0.0253   1.0000   0.0121
  -7.750  -0.3900   0.08588   0.08372  -0.0240   1.0000   0.0129
  -7.500  -0.3916   0.08356   0.08143  -0.0233   1.0000   0.0131
  -7.250  -0.3978   0.08138   0.07930  -0.0220   1.0000   0.0132
  -7.000  -0.3998   0.07896   0.07692  -0.0218   1.0000   0.0134
  -6.750  -0.4003   0.07619   0.07419  -0.0224   1.0000   0.0137
  -6.500  -0.4005   0.07327   0.07130  -0.0234   1.0000   0.0138
  -6.250  -0.3998   0.07024   0.06829  -0.0246   1.0000   0.0141
  -6.000  -0.3953   0.06688   0.06494  -0.0267   0.9998   0.0144
  -5.750  -0.3589   0.06070   0.05870  -0.0375   0.9966   0.0152
  -5.500  -0.3181   0.05377   0.05166  -0.0489   0.9936   0.0164
  -5.250  -0.2745   0.04666   0.04436  -0.0590   0.9897   0.0180
  -5.000  -0.2287   0.04139   0.03880  -0.0660   0.9867   0.0189
  -4.750  -0.1935   0.03124   0.02816  -0.0750   0.9839   0.0205
  -4.500  -0.1621   0.02919   0.02604  -0.0777   0.9807   0.0221
  -4.250  -0.1281   0.02644   0.02302  -0.0802   0.9764   0.0255
  -3.000   0.0564   0.01299   0.00758  -0.0891   0.9601   0.0195
  -2.750   0.0936   0.01125   0.00569  -0.0908   0.9579   0.0181
  -2.500   0.1254   0.01013   0.00446  -0.0913   0.9521   0.0177
  -2.250   0.1593   0.00930   0.00354  -0.0923   0.9465   0.0180
  -2.000   0.1929   0.00875   0.00292  -0.0933   0.9401   0.0190
  -1.750   0.2260   0.00816   0.00220  -0.0941   0.9317   0.0224
  -1.500   0.2574   0.00787   0.00188  -0.0945   0.9207   0.0312
  -1.250   0.2875   0.00705   0.00164  -0.0952   0.9085   0.2103
  -1.000   0.3162   0.00658   0.00155  -0.0954   0.8947   0.3553
  -0.750   0.3431   0.00602   0.00153  -0.0953   0.8796   0.5512
  -0.500   0.3644   0.00531   0.00156  -0.0936   0.8635   0.8023
  -0.250   0.3959   0.00500   0.00144  -0.0937   0.8474   1.0000
   0.000   0.4225   0.00507   0.00139  -0.0932   0.8281   1.0000
   0.250   0.4490   0.00516   0.00134  -0.0927   0.8082   1.0000
   0.500   0.4753   0.00526   0.00131  -0.0921   0.7867   1.0000
   0.750   0.5014   0.00539   0.00130  -0.0916   0.7649   1.0000
   1.000   0.5276   0.00551   0.00130  -0.0911   0.7426   1.0000
   1.250   0.5538   0.00566   0.00133  -0.0906   0.7209   1.0000
   1.500   0.5798   0.00580   0.00136  -0.0901   0.6981   1.0000
   1.750   0.6058   0.00596   0.00141  -0.0896   0.6748   1.0000
   2.000   0.6317   0.00613   0.00147  -0.0890   0.6503   1.0000
   2.250   0.6573   0.00633   0.00154  -0.0885   0.6242   1.0000
   2.500   0.6830   0.00653   0.00164  -0.0880   0.5975   1.0000
   2.750   0.7086   0.00674   0.00174  -0.0875   0.5704   1.0000
   3.000   0.7342   0.00696   0.00186  -0.0870   0.5442   1.0000
   3.250   0.7598   0.00719   0.00199  -0.0865   0.5177   1.0000
   3.500   0.7854   0.00743   0.00216  -0.0861   0.4908   1.0000
   3.750   0.8110   0.00767   0.00232  -0.0856   0.4645   1.0000
   4.000   0.8362   0.00796   0.00249  -0.0851   0.4356   1.0000
   4.250   0.8612   0.00827   0.00269  -0.0846   0.4040   1.0000
   4.500   0.8862   0.00860   0.00291  -0.0841   0.3711   1.0000
   4.750   0.9111   0.00895   0.00317  -0.0836   0.3407   1.0000
   5.000   0.9361   0.00929   0.00342  -0.0832   0.3133   1.0000
   5.250   0.9600   0.00975   0.00371  -0.0826   0.2736   1.0000
   5.500   0.9832   0.01032   0.00405  -0.0819   0.2271   1.0000
   5.750   1.0072   0.01079   0.00439  -0.0814   0.1939   1.0000
   6.000   1.0305   0.01135   0.00480  -0.0808   0.1585   1.0000
   6.250   1.0540   0.01189   0.00521  -0.0802   0.1280   1.0000
   6.500   1.0772   0.01246   0.00567  -0.0795   0.1001   1.0000
   6.750   1.0990   0.01322   0.00622  -0.0787   0.0655   1.0000
   7.000   1.1195   0.01415   0.00693  -0.0777   0.0323   1.0000
   7.250   1.1390   0.01526   0.00789  -0.0764   0.0106   1.0000
   7.500   1.1615   0.01595   0.00872  -0.0754   0.0085   1.0000
   7.750   1.1834   0.01669   0.00957  -0.0744   0.0074   1.0000
   8.000   1.2037   0.01763   0.01062  -0.0732   0.0066   1.0000
   8.250   1.2213   0.01889   0.01204  -0.0715   0.0061   1.0000
   8.500   1.2366   0.02038   0.01371  -0.0695   0.0059   1.0000
   8.750   1.2493   0.02217   0.01569  -0.0672   0.0058   1.0000
   9.000   1.2625   0.02394   0.01763  -0.0651   0.0058   1.0000
   9.250   1.2758   0.02576   0.01962  -0.0631   0.0058   1.0000
   9.500   1.2898   0.02750   0.02151  -0.0612   0.0058   1.0000
   9.750   1.3033   0.02929   0.02348  -0.0593   0.0059   1.0000
  10.000   1.3161   0.03106   0.02546  -0.0574   0.0060   1.0000
  10.250   1.3278   0.03283   0.02742  -0.0553   0.0061   1.0000
  10.500   1.3363   0.03489   0.02972  -0.0529   0.0063   1.0000
  10.750   1.3332   0.03900   0.03430  -0.0490   0.0070   1.0000
  11.000   1.3138   0.04432   0.04013  -0.0441   0.0077   1.0000
  11.250   1.2953   0.04854   0.04468  -0.0405   0.0082   1.0000
  11.500   1.2758   0.05289   0.04929  -0.0381   0.0084   1.0000
  11.750   1.2560   0.05757   0.05421  -0.0372   0.0086   1.0000
  12.000   1.2354   0.06283   0.05968  -0.0377   0.0088   1.0000
  12.250   1.2151   0.06868   0.06573  -0.0396   0.0089   1.0000
  12.500   1.1964   0.07497   0.07220  -0.0426   0.0090   1.0000
  12.750   1.1760   0.08239   0.07978  -0.0470   0.0090   1.0000
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