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SA7038 (sa7038-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: SA7038 (sa7038-il)
Reynolds number: 1,000,000
Max Cl/Cd: 107.75 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7038-il-1000000-n5.txt
Download as CSV file: xf-sa7038-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7038                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3727   0.09108   0.08946  -0.0329   1.0000   0.0052
  -9.000  -0.3768   0.08661   0.08501  -0.0343   1.0000   0.0049
  -8.750  -0.3760   0.08364   0.08207  -0.0351   1.0000   0.0054
  -8.500  -0.3686   0.07863   0.07707  -0.0398   0.9899   0.0053
  -8.250  -0.3589   0.07182   0.07027  -0.0478   0.9838   0.0053
  -8.000  -0.3479   0.06414   0.06259  -0.0588   0.9727   0.0053
  -7.750  -0.3425   0.05268   0.05104  -0.0753   0.9537   0.0053
  -7.500  -0.3829   0.02837   0.02586  -0.0862   0.9275   0.0057
  -7.250  -0.3743   0.02257   0.01946  -0.0862   0.9183   0.0059
  -7.000  -0.3550   0.02010   0.01663  -0.0859   0.9120   0.0060
  -6.750  -0.3331   0.01820   0.01442  -0.0856   0.9051   0.0061
  -6.500  -0.3099   0.01678   0.01274  -0.0853   0.8988   0.0062
  -6.250  -0.2853   0.01563   0.01138  -0.0850   0.8914   0.0063
  -6.000  -0.2601   0.01470   0.01025  -0.0847   0.8847   0.0064
  -5.750  -0.2339   0.01407   0.00947  -0.0845   0.8776   0.0065
  -5.500  -0.2074   0.01364   0.00891  -0.0842   0.8708   0.0066
  -5.250  -0.1819   0.01239   0.00746  -0.0840   0.8632   0.0066
  -5.000  -0.1559   0.01153   0.00646  -0.0837   0.8553   0.0067
  -4.750  -0.1298   0.01067   0.00545  -0.0834   0.8461   0.0067
  -4.500  -0.1035   0.00993   0.00458  -0.0831   0.8360   0.0069
  -4.250  -0.0768   0.00939   0.00393  -0.0829   0.8254   0.0070
  -4.000  -0.0499   0.00897   0.00342  -0.0827   0.8144   0.0073
  -3.750  -0.0226   0.00866   0.00303  -0.0825   0.8026   0.0076
  -3.500   0.0049   0.00840   0.00270  -0.0824   0.7906   0.0080
  -3.250   0.0324   0.00819   0.00241  -0.0822   0.7776   0.0084
  -3.000   0.0600   0.00801   0.00215  -0.0821   0.7638   0.0089
  -2.750   0.0875   0.00788   0.00192  -0.0819   0.7481   0.0092
  -2.500   0.1149   0.00778   0.00173  -0.0817   0.7303   0.0095
  -2.250   0.1424   0.00770   0.00155  -0.0816   0.7124   0.0097
  -2.000   0.1700   0.00764   0.00142  -0.0815   0.6951   0.0101
  -1.750   0.1976   0.00758   0.00126  -0.0813   0.6784   0.0112
  -1.500   0.2253   0.00755   0.00115  -0.0812   0.6618   0.0124
  -1.250   0.2528   0.00747   0.00105  -0.0811   0.6453   0.0250
  -1.000   0.2802   0.00732   0.00098  -0.0810   0.6282   0.0672
  -0.750   0.3075   0.00719   0.00094  -0.0810   0.6101   0.1180
  -0.500   0.3346   0.00700   0.00091  -0.0810   0.5913   0.1997
  -0.250   0.3615   0.00677   0.00091  -0.0810   0.5724   0.3051
   0.000   0.3883   0.00650   0.00094  -0.0811   0.5541   0.4324
   0.250   0.4153   0.00634   0.00097  -0.0810   0.5361   0.5265
   0.500   0.4424   0.00631   0.00101  -0.0809   0.5183   0.5831
   0.750   0.4694   0.00627   0.00106  -0.0808   0.5012   0.6423
   1.000   0.4962   0.00624   0.00112  -0.0806   0.4843   0.7022
   1.250   0.5225   0.00620   0.00120  -0.0802   0.4675   0.7654
   1.500   0.5475   0.00615   0.00128  -0.0795   0.4500   0.8357
   1.750   0.5694   0.00611   0.00136  -0.0780   0.4326   0.9105
   2.000   0.5999   0.00616   0.00141  -0.0785   0.4129   0.9827
   2.250   0.6299   0.00632   0.00147  -0.0790   0.3941   1.0000
   2.500   0.6568   0.00650   0.00156  -0.0789   0.3767   1.0000
   2.750   0.6839   0.00666   0.00165  -0.0787   0.3622   1.0000
   3.000   0.7108   0.00683   0.00175  -0.0786   0.3469   1.0000
   3.250   0.7375   0.00702   0.00186  -0.0784   0.3295   1.0000
   3.500   0.7641   0.00723   0.00198  -0.0782   0.3108   1.0000
   3.750   0.7904   0.00747   0.00212  -0.0780   0.2908   1.0000
   4.000   0.8169   0.00767   0.00227  -0.0778   0.2758   1.0000
   4.250   0.8434   0.00789   0.00242  -0.0776   0.2598   1.0000
   4.500   0.8697   0.00811   0.00258  -0.0774   0.2445   1.0000
   4.750   0.8961   0.00833   0.00274  -0.0772   0.2318   1.0000
   5.000   0.9223   0.00856   0.00293  -0.0770   0.2182   1.0000
   5.250   0.9482   0.00882   0.00312  -0.0767   0.2033   1.0000
   5.500   0.9741   0.00907   0.00332  -0.0765   0.1907   1.0000
   5.750   0.9995   0.00936   0.00355  -0.0762   0.1740   1.0000
   6.000   1.0248   0.00967   0.00380  -0.0758   0.1579   1.0000
   6.250   1.0499   0.00998   0.00405  -0.0755   0.1440   1.0000
   6.500   1.0749   0.01030   0.00432  -0.0751   0.1307   1.0000
   6.750   1.0990   0.01071   0.00463  -0.0746   0.1132   1.0000
   7.000   1.1224   0.01119   0.00500  -0.0740   0.0917   1.0000
   7.250   1.1461   0.01161   0.00535  -0.0735   0.0779   1.0000
   7.500   1.1689   0.01212   0.00576  -0.0728   0.0619   1.0000
   7.750   1.1925   0.01253   0.00613  -0.0723   0.0518   1.0000
   8.000   1.2156   0.01298   0.00653  -0.0717   0.0421   1.0000
   8.250   1.2381   0.01346   0.00698  -0.0710   0.0333   1.0000
   8.500   1.2604   0.01395   0.00744  -0.0702   0.0258   1.0000
   8.750   1.2824   0.01446   0.00792  -0.0694   0.0198   1.0000
   9.000   1.3036   0.01501   0.00845  -0.0686   0.0143   1.0000
   9.250   1.3240   0.01561   0.00903  -0.0676   0.0090   1.0000
   9.500   1.3428   0.01634   0.00974  -0.0663   0.0041   1.0000
   9.750   1.3626   0.01695   0.01040  -0.0652   0.0030   1.0000
  10.000   1.3827   0.01748   0.01098  -0.0642   0.0027   1.0000
  10.250   1.4019   0.01804   0.01160  -0.0630   0.0024   1.0000
  10.500   1.4204   0.01862   0.01224  -0.0618   0.0023   1.0000
  10.750   1.4375   0.01928   0.01295  -0.0603   0.0021   1.0000
  11.000   1.4529   0.01993   0.01367  -0.0585   0.0020   1.0000
  11.250   1.4656   0.02061   0.01442  -0.0564   0.0019   1.0000
  11.500   1.4756   0.02144   0.01535  -0.0538   0.0018   1.0000
  11.750   1.4858   0.02228   0.01628  -0.0515   0.0017   1.0000
  12.000   1.4934   0.02332   0.01742  -0.0489   0.0016   1.0000
  12.250   1.5019   0.02432   0.01851  -0.0467   0.0016   1.0000
  12.500   1.5117   0.02527   0.01953  -0.0447   0.0016   1.0000
  12.750   1.5189   0.02644   0.02080  -0.0427   0.0016   1.0000
  13.000   1.5257   0.02768   0.02213  -0.0407   0.0016   1.0000
  13.250   1.5320   0.02902   0.02356  -0.0389   0.0015   1.0000
  13.500   1.5349   0.03070   0.02535  -0.0371   0.0015   1.0000
  13.750   1.5389   0.03238   0.02713  -0.0356   0.0015   1.0000
  14.000   1.5415   0.03427   0.02912  -0.0342   0.0015   1.0000
  14.250   1.5437   0.03630   0.03125  -0.0331   0.0015   1.0000
  14.500   1.5412   0.03894   0.03402  -0.0322   0.0014   1.0000
  14.750   1.5413   0.04148   0.03668  -0.0317   0.0014   1.0000
  15.000   1.5382   0.04453   0.03985  -0.0314   0.0014   1.0000
  15.250   1.5330   0.04803   0.04348  -0.0316   0.0014   1.0000
  15.500   1.5262   0.05196   0.04755  -0.0322   0.0014   1.0000
  15.750   1.5215   0.05585   0.05155  -0.0331   0.0013   1.0000
  16.000   1.5084   0.06122   0.05707  -0.0349   0.0013   1.0000
  16.250   1.5002   0.06611   0.06209  -0.0367   0.0013   1.0000
  16.500   1.4881   0.07188   0.06800  -0.0391   0.0013   1.0000
  16.750   1.4702   0.07896   0.07524  -0.0423   0.0013   1.0000
  17.000   1.4558   0.08567   0.08209  -0.0456   0.0013   1.0000
  17.250   1.4379   0.09332   0.08988  -0.0494   0.0013   1.0000
  17.500   1.4178   0.10162   0.09833  -0.0537   0.0013   1.0000
  17.750   1.3974   0.11025   0.10710  -0.0583   0.0013   1.0000
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