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S4061-096-84 (s4061-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S4061-096-84 (s4061-il)
Reynolds number: 200,000
Max Cl/Cd: 84.28 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4061-il-200000.txt
Download as CSV file: xf-s4061-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4061-096-84                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3106   0.08919   0.08595  -0.0375   1.0000   0.0475
  -8.000  -0.3122   0.08671   0.08354  -0.0380   1.0000   0.0488
  -7.750  -0.3318   0.08601   0.08297  -0.0344   1.0000   0.0494
  -7.500  -0.3381   0.08379   0.08080  -0.0361   0.9953   0.0507
  -7.250  -0.3045   0.07363   0.07055  -0.0661   0.9793   0.0530
  -7.000  -0.2916   0.06915   0.06615  -0.0637   0.9761   0.0544
  -6.750  -0.2644   0.06583   0.06279  -0.0666   0.9729   0.0560
  -6.500  -0.2383   0.06156   0.05847  -0.0730   0.9654   0.0592
  -6.250  -0.2074   0.05020   0.04662  -0.0937   0.9531   0.0660
  -6.000  -0.1839   0.04729   0.04378  -0.0946   0.9471   0.0675
  -5.750  -0.1704   0.03008   0.02488  -0.1016   0.9340   0.0337
  -5.500  -0.1464   0.02721   0.02156  -0.1019   0.9269   0.0336
  -5.250  -0.1244   0.02419   0.01809  -0.1017   0.9187   0.0339
  -5.000  -0.0994   0.02241   0.01592  -0.1012   0.9118   0.0336
  -4.750  -0.0749   0.02045   0.01361  -0.1004   0.9042   0.0336
  -4.500  -0.0504   0.01849   0.01139  -0.0997   0.8978   0.0343
  -4.250  -0.0258   0.01724   0.01006  -0.0989   0.8901   0.0358
  -4.000  -0.0004   0.01637   0.00910  -0.0981   0.8843   0.0387
  -3.750   0.0247   0.01558   0.00822  -0.0973   0.8762   0.0436
  -3.500   0.0503   0.01490   0.00747  -0.0965   0.8707   0.0526
  -3.250   0.0753   0.01392   0.00666  -0.0959   0.8624   0.0846
  -3.000   0.1011   0.01348   0.00629  -0.0953   0.8566   0.1255
  -2.750   0.1272   0.01326   0.00616  -0.0950   0.8488   0.1665
  -2.500   0.1532   0.01289   0.00588  -0.0945   0.8426   0.2071
  -2.250   0.1792   0.01258   0.00570  -0.0941   0.8354   0.2534
  -2.000   0.2051   0.01222   0.00551  -0.0936   0.8286   0.3121
  -1.750   0.2307   0.01186   0.00539  -0.0931   0.8221   0.3913
  -1.500   0.2554   0.01143   0.00533  -0.0925   0.8147   0.5001
  -1.250   0.2777   0.01091   0.00527  -0.0909   0.8090   0.6453
  -1.000   0.2961   0.01034   0.00529  -0.0879   0.8010   0.8450
  -0.750   0.3427   0.01007   0.00494  -0.0910   0.7960   1.0000
  -0.500   0.3694   0.01016   0.00490  -0.0908   0.7876   1.0000
  -0.250   0.3963   0.01019   0.00476  -0.0903   0.7814   1.0000
   0.000   0.4231   0.01028   0.00475  -0.0901   0.7731   1.0000
   0.250   0.4502   0.01031   0.00465  -0.0896   0.7667   1.0000
   0.500   0.4771   0.01041   0.00467  -0.0894   0.7584   1.0000
   0.750   0.5044   0.01045   0.00459  -0.0890   0.7517   1.0000
   1.000   0.5313   0.01055   0.00463  -0.0887   0.7431   1.0000
   1.250   0.5587   0.01058   0.00456  -0.0884   0.7363   1.0000
   1.500   0.5856   0.01068   0.00463  -0.0881   0.7270   1.0000
   1.750   0.6130   0.01072   0.00457  -0.0877   0.7198   1.0000
   2.000   0.6398   0.01079   0.00462  -0.0874   0.7097   1.0000
   2.250   0.6668   0.01086   0.00463  -0.0870   0.7004   1.0000
   2.500   0.6942   0.01089   0.00460  -0.0866   0.6916   1.0000
   2.750   0.7209   0.01098   0.00468  -0.0863   0.6809   1.0000
   3.000   0.7479   0.01106   0.00472  -0.0860   0.6710   1.0000
   3.250   0.7752   0.01112   0.00473  -0.0856   0.6616   1.0000
   3.500   0.8017   0.01121   0.00484  -0.0853   0.6499   1.0000
   3.750   0.8284   0.01130   0.00493  -0.0849   0.6385   1.0000
   4.000   0.8552   0.01140   0.00501  -0.0845   0.6273   1.0000
   4.250   0.8820   0.01150   0.00509  -0.0841   0.6157   1.0000
   4.500   0.9084   0.01161   0.00520  -0.0837   0.6028   1.0000
   4.750   0.9345   0.01174   0.00534  -0.0833   0.5889   1.0000
   5.000   0.9605   0.01187   0.00550  -0.0829   0.5742   1.0000
   5.250   0.9863   0.01202   0.00565  -0.0824   0.5587   1.0000
   5.500   1.0117   0.01220   0.00583  -0.0818   0.5419   1.0000
   5.750   1.0367   0.01239   0.00605  -0.0813   0.5227   1.0000
   6.000   1.0614   0.01261   0.00627  -0.0806   0.5025   1.0000
   6.250   1.0855   0.01288   0.00653  -0.0799   0.4803   1.0000
   6.500   1.1088   0.01320   0.00680  -0.0791   0.4553   1.0000
   6.750   1.1312   0.01358   0.00715  -0.0783   0.4267   1.0000
   7.000   1.1524   0.01406   0.00755  -0.0772   0.3950   1.0000
   7.250   1.1728   0.01462   0.00802  -0.0762   0.3610   1.0000
   7.500   1.1920   0.01528   0.00856  -0.0750   0.3273   1.0000
   7.750   1.2101   0.01603   0.00920  -0.0737   0.2952   1.0000
   8.000   1.2274   0.01684   0.00989  -0.0723   0.2656   1.0000
   8.250   1.2436   0.01770   0.01064  -0.0708   0.2367   1.0000
   8.500   1.2590   0.01859   0.01142  -0.0693   0.2084   1.0000
   8.750   1.2734   0.01950   0.01223  -0.0677   0.1808   1.0000
   9.000   1.2873   0.02042   0.01309  -0.0661   0.1559   1.0000
   9.250   1.2995   0.02142   0.01402  -0.0642   0.1346   1.0000
   9.500   1.3093   0.02244   0.01498  -0.0620   0.1149   1.0000
   9.750   1.3154   0.02365   0.01610  -0.0594   0.0983   1.0000
  10.000   1.3224   0.02491   0.01735  -0.0570   0.0817   1.0000
  10.250   1.3254   0.02651   0.01888  -0.0545   0.0658   1.0000
  10.500   1.3239   0.02856   0.02087  -0.0519   0.0527   1.0000
  10.750   1.3242   0.03062   0.02295  -0.0496   0.0439   1.0000
  11.000   1.3240   0.03282   0.02520  -0.0475   0.0390   1.0000
  11.250   1.3274   0.03481   0.02727  -0.0459   0.0357   1.0000
  11.500   1.3241   0.03753   0.02999  -0.0441   0.0333   1.0000
  11.750   1.3283   0.03971   0.03230  -0.0427   0.0317   1.0000
  12.000   1.3341   0.04182   0.03454  -0.0415   0.0302   1.0000
  12.250   1.3399   0.04399   0.03681  -0.0404   0.0289   1.0000
  12.500   1.3459   0.04619   0.03908  -0.0394   0.0278   1.0000
  12.750   1.3517   0.04856   0.04148  -0.0384   0.0266   1.0000
  13.000   1.3608   0.05127   0.04429  -0.0372   0.0254   1.0000
  13.250   1.3656   0.05370   0.04694  -0.0365   0.0248   1.0000
  13.500   1.3702   0.05638   0.04982  -0.0358   0.0241   1.0000
  13.750   1.3740   0.05933   0.05298  -0.0352   0.0237   1.0000
  14.000   1.3752   0.06262   0.05649  -0.0348   0.0233   1.0000
  14.250   1.3736   0.06622   0.06033  -0.0346   0.0229   1.0000
  14.500   1.3692   0.07022   0.06456  -0.0347   0.0227   1.0000
  14.750   1.3616   0.07476   0.06935  -0.0352   0.0226   1.0000
  15.000   1.3512   0.07969   0.07452  -0.0362   0.0225   1.0000
  15.250   1.3377   0.08528   0.08037  -0.0378   0.0225   1.0000
  15.500   1.3214   0.09154   0.08689  -0.0401   0.0226   1.0000
  15.750   1.3030   0.09846   0.09407  -0.0432   0.0226   1.0000
  16.000   1.2824   0.10622   0.10208  -0.0472   0.0228   1.0000
  16.250   1.2599   0.11484   0.11094  -0.0521   0.0230   1.0000
  16.500   1.2358   0.12439   0.12071  -0.0581   0.0233   1.0000
  16.750   1.2101   0.13506   0.13159  -0.0651   0.0236   1.0000
  17.000   1.1819   0.14734   0.14405  -0.0735   0.0241   1.0000
  17.250   1.1504   0.16176   0.15860  -0.0833   0.0247   1.0000
  17.500   1.1225   0.17623   0.17312  -0.0924   0.0254   1.0000
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