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SA7038 (sa7038-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SA7038 (sa7038-il)
Reynolds number: 50,000
Max Cl/Cd: 39.67 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sa7038-il-50000-n5.txt
Download as CSV file: xf-sa7038-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3585   0.09563   0.08881  -0.0341   1.0000   0.0591
  -8.000  -0.3626   0.09222   0.08552  -0.0348   1.0000   0.0554
  -7.750  -0.3781   0.08872   0.08215  -0.0369   1.0000   0.0503
  -7.500  -0.3793   0.08599   0.07951  -0.0359   1.0000   0.0493
  -7.250  -0.3828   0.08292   0.07654  -0.0361   1.0000   0.0486
  -7.000  -0.3868   0.07971   0.07341  -0.0368   1.0000   0.0480
  -6.750  -0.3903   0.07632   0.07009  -0.0376   1.0000   0.0473
  -6.500  -0.3929   0.07276   0.06656  -0.0387   1.0000   0.0470
  -6.250  -0.3937   0.06903   0.06284  -0.0398   1.0000   0.0462
  -6.000  -0.3926   0.06509   0.05885  -0.0411   1.0000   0.0461
  -5.750  -0.3888   0.06104   0.05471  -0.0424   1.0000   0.0458
  -5.500  -0.3821   0.05692   0.05043  -0.0437   1.0000   0.0458
  -5.250  -0.3721   0.05285   0.04614  -0.0450   1.0000   0.0456
  -5.000  -0.3588   0.04877   0.04176  -0.0463   1.0000   0.0452
  -4.750  -0.3423   0.04477   0.03736  -0.0474   1.0000   0.0447
  -4.500  -0.3230   0.04112   0.03326  -0.0483   1.0000   0.0442
  -4.250  -0.3017   0.03788   0.02953  -0.0488   1.0000   0.0441
  -4.000  -0.2789   0.03507   0.02622  -0.0490   1.0000   0.0444
  -3.750  -0.2554   0.03273   0.02338  -0.0489   1.0000   0.0449
  -3.500  -0.2302   0.03069   0.02089  -0.0489   0.9995   0.0459
  -3.250  -0.1920   0.02876   0.01848  -0.0509   0.9938   0.0477
  -3.000  -0.1550   0.02731   0.01662  -0.0526   0.9873   0.0520
  -2.750  -0.1186   0.02617   0.01538  -0.0545   0.9807   0.0594
  -2.500  -0.0821   0.02506   0.01402  -0.0560   0.9735   0.0669
  -2.250  -0.0446   0.02409   0.01297  -0.0580   0.9661   0.0877
  -2.000  -0.0061   0.02263   0.01211  -0.0608   0.9591   0.1905
  -1.750   0.0253   0.02102   0.01191  -0.0621   0.9516   0.4776
  -1.500   0.0482   0.02008   0.01195  -0.0593   0.9436   0.7661
  -1.250   0.0954   0.01980   0.01144  -0.0626   0.9335   1.0000
  -1.000   0.1330   0.02000   0.01120  -0.0647   0.9233   1.0000
  -0.750   0.1745   0.02018   0.01098  -0.0675   0.9143   1.0000
  -0.500   0.2083   0.02034   0.01084  -0.0688   0.9023   1.0000
  -0.250   0.2427   0.02049   0.01074  -0.0702   0.8905   1.0000
   0.000   0.2780   0.02062   0.01064  -0.0716   0.8791   1.0000
   0.250   0.3139   0.02072   0.01055  -0.0730   0.8680   1.0000
   0.500   0.3514   0.02075   0.01042  -0.0746   0.8576   1.0000
   0.750   0.3823   0.02083   0.01036  -0.0750   0.8446   1.0000
   1.000   0.4133   0.02090   0.01032  -0.0753   0.8314   1.0000
   1.250   0.4443   0.02094   0.01027  -0.0756   0.8180   1.0000
   1.500   0.4751   0.02096   0.01023  -0.0757   0.8043   1.0000
   1.750   0.5056   0.02096   0.01018  -0.0758   0.7903   1.0000
   2.000   0.5359   0.02096   0.01013  -0.0757   0.7759   1.0000
   2.250   0.5659   0.02095   0.01011  -0.0756   0.7612   1.0000
   2.500   0.5958   0.02094   0.01006  -0.0753   0.7461   1.0000
   2.750   0.6256   0.02093   0.01002  -0.0750   0.7307   1.0000
   3.000   0.6521   0.02103   0.01012  -0.0743   0.7127   1.0000
   3.250   0.6797   0.02110   0.01022  -0.0737   0.6948   1.0000
   3.500   0.7080   0.02115   0.01025  -0.0732   0.6770   1.0000
   3.750   0.7361   0.02122   0.01030  -0.0726   0.6587   1.0000
   4.000   0.7613   0.02143   0.01053  -0.0717   0.6380   1.0000
   4.250   0.7883   0.02158   0.01071  -0.0709   0.6184   1.0000
   4.500   0.8132   0.02185   0.01099  -0.0700   0.5972   1.0000
   4.750   0.8387   0.02210   0.01124  -0.0691   0.5763   1.0000
   5.000   0.8629   0.02244   0.01159  -0.0682   0.5545   1.0000
   5.250   0.8876   0.02278   0.01198  -0.0672   0.5329   1.0000
   5.500   0.9106   0.02321   0.01244  -0.0662   0.5102   1.0000
   5.750   0.9345   0.02362   0.01284  -0.0652   0.4885   1.0000
   6.000   0.9563   0.02414   0.01342  -0.0640   0.4652   1.0000
   6.250   0.9787   0.02467   0.01396  -0.0629   0.4431   1.0000
   6.500   1.0002   0.02526   0.01464  -0.0618   0.4207   1.0000
   6.750   1.0213   0.02589   0.01532  -0.0606   0.3984   1.0000
   7.000   1.0420   0.02656   0.01602  -0.0594   0.3768   1.0000
   7.250   1.0615   0.02731   0.01684  -0.0582   0.3547   1.0000
   7.500   1.0808   0.02807   0.01768  -0.0569   0.3337   1.0000
   7.750   1.0992   0.02893   0.01863  -0.0555   0.3128   1.0000
   8.000   1.1170   0.02982   0.01958  -0.0541   0.2928   1.0000
   8.250   1.1343   0.03079   0.02061  -0.0527   0.2737   1.0000
   8.500   1.1501   0.03184   0.02177  -0.0512   0.2542   1.0000
   8.750   1.1654   0.03294   0.02293  -0.0497   0.2364   1.0000
   9.000   1.1791   0.03410   0.02419  -0.0480   0.2189   1.0000
   9.250   1.1915   0.03539   0.02562  -0.0463   0.2018   1.0000
   9.500   1.2018   0.03673   0.02707  -0.0444   0.1852   1.0000
   9.750   1.2112   0.03818   0.02861  -0.0425   0.1702   1.0000
  10.000   1.2183   0.03970   0.03023  -0.0404   0.1566   1.0000
  10.250   1.2246   0.04137   0.03201  -0.0383   0.1443   1.0000
  10.500   1.2289   0.04316   0.03390  -0.0362   0.1328   1.0000
  10.750   1.2323   0.04507   0.03586  -0.0342   0.1228   1.0000
  11.000   1.2361   0.04719   0.03812  -0.0325   0.1134   1.0000
  11.250   1.2375   0.04960   0.04074  -0.0309   0.1047   1.0000
  11.500   1.2378   0.05196   0.04319  -0.0295   0.0974   1.0000
  11.750   1.2376   0.05482   0.04634  -0.0283   0.0904   1.0000
  12.000   1.2385   0.05757   0.04913  -0.0273   0.0849   1.0000
  12.250   1.2329   0.06111   0.05301  -0.0267   0.0794   1.0000
  12.500   1.2306   0.06406   0.05594  -0.0264   0.0745   1.0000
  12.750   1.2229   0.06841   0.06063  -0.0265   0.0709   1.0000
  13.000   1.2134   0.07313   0.06565  -0.0271   0.0678   1.0000
  13.250   1.2048   0.07763   0.07032  -0.0281   0.0649   1.0000
  13.500   1.2008   0.08143   0.07408  -0.0288   0.0613   1.0000
  13.750   1.1821   0.08813   0.08112  -0.0316   0.0602   1.0000
  14.000   1.1623   0.09549   0.08876  -0.0351   0.0595   1.0000
  14.250   1.1411   0.10369   0.09719  -0.0395   0.0595   1.0000
  14.500   1.1170   0.11315   0.10685  -0.0449   0.0600   1.0000
  14.750   1.0922   0.12363   0.11745  -0.0511   0.0608   1.0000
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