Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

SA7038 (sa7038-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SA7038 (sa7038-il)
Reynolds number: 200,000
Max Cl/Cd: 76.54 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7038-il-200000.txt
Download as CSV file: xf-sa7038-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3525   0.08751   0.08417  -0.0341   1.0000   0.0438
  -7.750  -0.3635   0.08528   0.08203  -0.0339   1.0000   0.0448
  -7.500  -0.3807   0.08370   0.08055  -0.0320   1.0000   0.0452
  -7.250  -0.4004   0.08184   0.07878  -0.0317   1.0000   0.0457
  -7.000  -0.4122   0.07877   0.07576  -0.0346   1.0000   0.0461
  -6.750  -0.4190   0.07510   0.07205  -0.0377   1.0000   0.0464
  -6.500  -0.4221   0.07162   0.06848  -0.0393   1.0000   0.0466
  -6.250  -0.4296   0.06565   0.06250  -0.0400   1.0000   0.0473
  -6.000  -0.4187   0.06289   0.05985  -0.0384   0.9984   0.0485
  -5.750  -0.3915   0.05964   0.05658  -0.0418   0.9945   0.0505
  -5.500  -0.3598   0.05452   0.05130  -0.0487   0.9890   0.0550
  -5.250  -0.3210   0.04662   0.04292  -0.0593   0.9838   0.0616
  -5.000  -0.2939   0.04456   0.04090  -0.0610   0.9782   0.0668
  -4.750  -0.2568   0.03935   0.03523  -0.0670   0.9731   0.0758
  -4.500  -0.2215   0.03661   0.03233  -0.0702   0.9690   0.0816
  -4.250  -0.1798   0.02857   0.02277  -0.0720   0.9629   0.0471
  -4.000  -0.1408   0.02392   0.01743  -0.0737   0.9598   0.0354
  -3.750  -0.1010   0.02091   0.01405  -0.0761   0.9574   0.0341
  -3.500  -0.0701   0.01925   0.01212  -0.0764   0.9507   0.0341
  -3.250  -0.0306   0.01804   0.01070  -0.0784   0.9465   0.0350
  -3.000   0.0104   0.01636   0.00901  -0.0810   0.9438   0.0393
  -2.750   0.0427   0.01549   0.00812  -0.0817   0.9366   0.0424
  -2.500   0.0835   0.01452   0.00710  -0.0840   0.9322   0.0492
  -2.250   0.1241   0.01283   0.00614  -0.0867   0.9291   0.2132
  -2.000   0.1505   0.01196   0.00601  -0.0868   0.9199   0.4074
  -1.750   0.1824   0.01102   0.00590  -0.0872   0.9153   0.6358
  -1.500   0.2014   0.01049   0.00587  -0.0842   0.9056   0.7917
  -1.250   0.2448   0.01004   0.00557  -0.0857   0.9019   0.9430
  -1.000   0.2973   0.00979   0.00516  -0.0905   0.8958   1.0000
  -0.750   0.3267   0.00963   0.00483  -0.0903   0.8869   1.0000
  -0.500   0.3516   0.00953   0.00461  -0.0894   0.8752   1.0000
  -0.250   0.3775   0.00944   0.00440  -0.0886   0.8637   1.0000
   0.000   0.4039   0.00934   0.00419  -0.0878   0.8524   1.0000
   0.250   0.4305   0.00925   0.00398  -0.0871   0.8407   1.0000
   0.500   0.4570   0.00918   0.00380  -0.0864   0.8283   1.0000
   0.750   0.4831   0.00914   0.00366  -0.0856   0.8144   1.0000
   1.000   0.5090   0.00913   0.00356  -0.0848   0.7991   1.0000
   1.250   0.5349   0.00914   0.00348  -0.0841   0.7826   1.0000
   1.500   0.5610   0.00917   0.00342  -0.0834   0.7654   1.0000
   1.750   0.5872   0.00922   0.00337  -0.0827   0.7478   1.0000
   2.000   0.6135   0.00930   0.00334  -0.0821   0.7301   1.0000
   2.250   0.6393   0.00942   0.00337  -0.0815   0.7105   1.0000
   2.500   0.6652   0.00955   0.00340  -0.0808   0.6908   1.0000
   2.750   0.6911   0.00971   0.00346  -0.0802   0.6713   1.0000
   3.000   0.7165   0.00989   0.00357  -0.0796   0.6499   1.0000
   3.250   0.7420   0.01009   0.00366  -0.0789   0.6294   1.0000
   3.500   0.7672   0.01030   0.00380  -0.0783   0.6071   1.0000
   3.750   0.7923   0.01054   0.00393  -0.0776   0.5857   1.0000
   4.000   0.8173   0.01078   0.00413  -0.0770   0.5631   1.0000
   4.250   0.8420   0.01106   0.00432  -0.0763   0.5413   1.0000
   4.500   0.8666   0.01133   0.00453  -0.0756   0.5187   1.0000
   4.750   0.8909   0.01164   0.00476  -0.0750   0.4961   1.0000
   5.000   0.9149   0.01197   0.00503  -0.0742   0.4731   1.0000
   5.250   0.9388   0.01230   0.00532  -0.0735   0.4494   1.0000
   5.500   0.9623   0.01267   0.00561  -0.0728   0.4266   1.0000
   5.750   0.9857   0.01304   0.00594  -0.0720   0.4035   1.0000
   6.000   1.0089   0.01345   0.00632  -0.0712   0.3809   1.0000
   6.250   1.0316   0.01389   0.00669  -0.0704   0.3586   1.0000
   6.500   1.0543   0.01433   0.00711  -0.0696   0.3362   1.0000
   6.750   1.0762   0.01484   0.00755  -0.0687   0.3150   1.0000
   7.000   1.0982   0.01531   0.00804  -0.0678   0.2923   1.0000
   7.250   1.1192   0.01588   0.00853  -0.0668   0.2710   1.0000
   7.500   1.1404   0.01641   0.00906  -0.0659   0.2490   1.0000
   7.750   1.1605   0.01704   0.00962  -0.0648   0.2292   1.0000
   8.000   1.1810   0.01762   0.01023  -0.0638   0.2092   1.0000
   8.250   1.2001   0.01831   0.01089  -0.0626   0.1904   1.0000
   8.500   1.2188   0.01903   0.01159  -0.0614   0.1726   1.0000
   8.750   1.2373   0.01973   0.01232  -0.0601   0.1546   1.0000
   9.000   1.2543   0.02055   0.01312  -0.0587   0.1380   1.0000
   9.250   1.2696   0.02148   0.01402  -0.0571   0.1225   1.0000
   9.500   1.2830   0.02253   0.01502  -0.0552   0.1074   1.0000
   9.750   1.2960   0.02357   0.01612  -0.0533   0.0933   1.0000
  10.000   1.3057   0.02468   0.01723  -0.0509   0.0812   1.0000
  10.250   1.3137   0.02583   0.01836  -0.0484   0.0703   1.0000
  10.500   1.3256   0.02672   0.01933  -0.0466   0.0604   1.0000
  10.750   1.3344   0.02790   0.02061  -0.0444   0.0526   1.0000
  11.000   1.3362   0.02962   0.02233  -0.0417   0.0467   1.0000
  11.250   1.3436   0.03101   0.02385  -0.0398   0.0401   1.0000
  11.500   1.3419   0.03322   0.02614  -0.0372   0.0345   1.0000
  11.750   1.3410   0.03538   0.02835  -0.0352   0.0291   1.0000
  12.000   1.3384   0.03797   0.03109  -0.0332   0.0255   1.0000
  12.250   1.3391   0.04026   0.03352  -0.0318   0.0229   1.0000
  12.500   1.3351   0.04317   0.03651  -0.0306   0.0213   1.0000
  12.750   1.3281   0.04689   0.04031  -0.0292   0.0201   1.0000
  13.000   1.3292   0.04965   0.04329  -0.0285   0.0192   1.0000
  13.250   1.3285   0.05279   0.04662  -0.0280   0.0184   1.0000
  13.500   1.3266   0.05616   0.05018  -0.0278   0.0177   1.0000
  13.750   1.3243   0.05971   0.05390  -0.0278   0.0173   1.0000
  14.000   1.3201   0.06357   0.05795  -0.0281   0.0168   1.0000
  14.250   1.3146   0.06775   0.06232  -0.0288   0.0164   1.0000
  14.500   1.3078   0.07227   0.06702  -0.0299   0.0162   1.0000
  14.750   1.2996   0.07716   0.07210  -0.0314   0.0160   1.0000
  15.000   1.2894   0.08257   0.07772  -0.0334   0.0158   1.0000
  15.250   1.2771   0.08857   0.08393  -0.0359   0.0158   1.0000
  15.500   1.2634   0.09513   0.09071  -0.0391   0.0158   1.0000
  15.750   1.2474   0.10243   0.09824  -0.0430   0.0158   1.0000
  16.000   1.2295   0.11049   0.10653  -0.0477   0.0159   1.0000
  16.250   1.2087   0.11970   0.11597  -0.0533   0.0162   1.0000
  16.500   1.1856   0.13003   0.12652  -0.0600   0.0164   1.0000
  16.750   1.1566   0.14265   0.13938  -0.0684   0.0169   1.0000
  17.000   1.1185   0.15924   0.15617  -0.0794   0.0179   1.0000
<< Back to SA7038 (sa7038-il)

Polar data table (+)

Polar graphs


<< Back to SA7038 (sa7038-il)