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S4061-096-84 (s4061-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S4061-096-84 (s4061-il)
Reynolds number: 1,000,000
Max Cl/Cd: 139.27 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4061-il-1000000.txt
Download as CSV file: xf-s4061-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3110   0.07990   0.07831  -0.0479   0.9558   0.0122
  -8.500  -0.2613   0.06689   0.06511  -0.0419   0.8704   0.0130
  -6.500  -0.3085   0.01771   0.01334  -0.0842   0.8242   0.0093
  -6.250  -0.2821   0.01677   0.01223  -0.0842   0.8178   0.0092
  -6.000  -0.2574   0.01482   0.00999  -0.0841   0.8119   0.0091
  -5.750  -0.2308   0.01370   0.00866  -0.0840   0.8059   0.0092
  -5.500  -0.2057   0.01182   0.00655  -0.0838   0.7997   0.0096
  -5.250  -0.1787   0.01111   0.00574  -0.0837   0.7939   0.0101
  -5.000  -0.1510   0.01061   0.00518  -0.0837   0.7877   0.0105
  -4.750  -0.1234   0.01018   0.00465  -0.0837   0.7817   0.0110
  -4.500  -0.0954   0.00975   0.00416  -0.0837   0.7756   0.0113
  -4.250  -0.0674   0.00939   0.00372  -0.0836   0.7693   0.0117
  -4.000  -0.0393   0.00908   0.00332  -0.0836   0.7634   0.0121
  -3.750  -0.0111   0.00863   0.00281  -0.0836   0.7570   0.0130
  -3.500   0.0170   0.00837   0.00248  -0.0836   0.7509   0.0143
  -3.250   0.0455   0.00814   0.00220  -0.0836   0.7446   0.0157
  -3.000   0.0739   0.00787   0.00189  -0.0836   0.7382   0.0201
  -2.750   0.1020   0.00749   0.00165  -0.0836   0.7321   0.0533
  -2.500   0.1304   0.00730   0.00152  -0.0837   0.7254   0.0766
  -2.250   0.1586   0.00715   0.00142  -0.0838   0.7192   0.1010
  -2.000   0.1870   0.00698   0.00133  -0.0839   0.7125   0.1297
  -1.750   0.2152   0.00685   0.00126  -0.0839   0.7060   0.1608
  -1.500   0.2437   0.00669   0.00120  -0.0840   0.6994   0.1968
  -1.250   0.2719   0.00655   0.00115  -0.0841   0.6925   0.2408
  -1.000   0.3004   0.00642   0.00111  -0.0842   0.6858   0.2799
  -0.750   0.3286   0.00629   0.00108  -0.0843   0.6787   0.3297
  -0.500   0.3568   0.00613   0.00107  -0.0844   0.6718   0.3906
  -0.250   0.3848   0.00595   0.00107  -0.0845   0.6642   0.4641
   0.000   0.4127   0.00577   0.00107  -0.0845   0.6567   0.5435
   0.250   0.4400   0.00554   0.00110  -0.0845   0.6483   0.6475
   0.500   0.4661   0.00526   0.00114  -0.0840   0.6394   0.7693
   0.750   0.4876   0.00488   0.00118  -0.0822   0.6306   0.9460
   1.000   0.5246   0.00489   0.00115  -0.0841   0.6209   1.0000
   1.250   0.5528   0.00496   0.00117  -0.0841   0.6120   1.0000
   1.750   0.6091   0.00512   0.00122  -0.0842   0.5925   1.0000
   2.000   0.6372   0.00521   0.00126  -0.0842   0.5825   1.0000
   2.250   0.6652   0.00532   0.00131  -0.0841   0.5721   1.0000
   2.500   0.6933   0.00540   0.00137  -0.0842   0.5612   1.0000
   2.750   0.7212   0.00551   0.00143  -0.0842   0.5501   1.0000
   3.000   0.7491   0.00562   0.00149  -0.0842   0.5383   1.0000
   3.250   0.7768   0.00575   0.00158  -0.0841   0.5256   1.0000
   3.500   0.8044   0.00589   0.00167  -0.0841   0.5119   1.0000
   3.750   0.8319   0.00604   0.00176  -0.0841   0.4975   1.0000
   4.000   0.8593   0.00620   0.00187  -0.0840   0.4820   1.0000
   4.250   0.8865   0.00637   0.00200  -0.0840   0.4652   1.0000
   4.500   0.9136   0.00656   0.00213  -0.0839   0.4468   1.0000
   4.750   0.9402   0.00680   0.00228  -0.0837   0.4269   1.0000
   5.000   0.9668   0.00703   0.00246  -0.0836   0.4059   1.0000
   5.250   0.9928   0.00733   0.00265  -0.0834   0.3811   1.0000
   5.500   1.0182   0.00770   0.00288  -0.0831   0.3495   1.0000
   5.750   1.0431   0.00811   0.00315  -0.0828   0.3153   1.0000
   6.000   1.0679   0.00852   0.00343  -0.0825   0.2851   1.0000
   6.250   1.0919   0.00901   0.00375  -0.0820   0.2523   1.0000
   6.500   1.1159   0.00947   0.00408  -0.0816   0.2236   1.0000
   6.750   1.1401   0.00990   0.00441  -0.0812   0.1993   1.0000
   7.000   1.1638   0.01037   0.00475  -0.0807   0.1759   1.0000
   7.250   1.1875   0.01082   0.00511  -0.0803   0.1549   1.0000
   7.500   1.2106   0.01130   0.00550  -0.0797   0.1343   1.0000
   7.750   1.2328   0.01187   0.00593  -0.0790   0.1119   1.0000
   8.000   1.2553   0.01236   0.00634  -0.0784   0.0952   1.0000
   8.250   1.2772   0.01290   0.00680  -0.0777   0.0789   1.0000
   8.500   1.2981   0.01349   0.00730  -0.0768   0.0638   1.0000
   8.750   1.3188   0.01408   0.00783  -0.0759   0.0506   1.0000
   9.000   1.3385   0.01472   0.00840  -0.0749   0.0384   1.0000
   9.250   1.3554   0.01555   0.00913  -0.0735   0.0236   1.0000
   9.500   1.3712   0.01642   0.00993  -0.0719   0.0149   1.0000
   9.750   1.3892   0.01705   0.01059  -0.0706   0.0129   1.0000
  10.000   1.4048   0.01782   0.01139  -0.0689   0.0114   1.0000
  10.250   1.4211   0.01840   0.01204  -0.0674   0.0109   1.0000
  10.500   1.4338   0.01905   0.01274  -0.0652   0.0104   1.0000
  10.750   1.4450   0.01977   0.01352  -0.0629   0.0101   1.0000
  11.000   1.4552   0.02060   0.01441  -0.0607   0.0096   1.0000
  11.250   1.4642   0.02156   0.01543  -0.0585   0.0093   1.0000
  11.500   1.4701   0.02279   0.01676  -0.0561   0.0089   1.0000
  11.750   1.4730   0.02430   0.01838  -0.0536   0.0086   1.0000
  12.000   1.4780   0.02576   0.01993  -0.0516   0.0084   1.0000
  12.250   1.4882   0.02687   0.02111  -0.0503   0.0083   1.0000
  12.500   1.4958   0.02824   0.02257  -0.0488   0.0081   1.0000
  12.750   1.5030   0.02971   0.02411  -0.0475   0.0078   1.0000
  13.000   1.5076   0.03146   0.02595  -0.0461   0.0077   1.0000
  13.250   1.5113   0.03336   0.02795  -0.0449   0.0076   1.0000
  13.500   1.5158   0.03527   0.02995  -0.0439   0.0073   1.0000
  13.750   1.5183   0.03744   0.03222  -0.0430   0.0072   1.0000
  14.000   1.5188   0.03991   0.03478  -0.0422   0.0071   1.0000
  14.250   1.5197   0.04242   0.03738  -0.0417   0.0069   1.0000
  14.500   1.5177   0.04535   0.04040  -0.0413   0.0068   1.0000
  14.750   1.5160   0.04839   0.04355  -0.0411   0.0068   1.0000
  15.000   1.5112   0.05191   0.04718  -0.0412   0.0066   1.0000
  15.250   1.5053   0.05577   0.05114  -0.0415   0.0065   1.0000
  15.500   1.4976   0.06003   0.05551  -0.0422   0.0064   1.0000
  15.750   1.4859   0.06503   0.06064  -0.0432   0.0063   1.0000
  16.000   1.4743   0.07025   0.06599  -0.0445   0.0062   1.0000
  16.250   1.4625   0.07563   0.07152  -0.0460   0.0062   1.0000
  16.500   1.4544   0.08072   0.07673  -0.0477   0.0061   1.0000
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