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S4061-096-84 (s4061-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S4061-096-84 (s4061-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.22 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4061-il-1000000-n5.txt
Download as CSV file: xf-s4061-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3380   0.09680   0.09497  -0.0377   0.9182   0.0050
  -9.000  -0.5612   0.02585   0.02277  -0.0809   0.8325   0.0043
  -8.500  -0.5228   0.02088   0.01714  -0.0821   0.8188   0.0044
  -8.250  -0.5001   0.01926   0.01525  -0.0823   0.8122   0.0044
  -8.000  -0.4760   0.01794   0.01370  -0.0824   0.8062   0.0045
  -7.750  -0.4511   0.01681   0.01238  -0.0825   0.7998   0.0047
  -7.500  -0.4258   0.01577   0.01114  -0.0825   0.7939   0.0048
  -7.250  -0.3997   0.01487   0.01006  -0.0825   0.7877   0.0050
  -7.000  -0.3734   0.01410   0.00912  -0.0825   0.7815   0.0051
  -6.750  -0.3466   0.01340   0.00828  -0.0825   0.7757   0.0053
  -6.500  -0.3196   0.01280   0.00755  -0.0824   0.7695   0.0054
  -6.250  -0.2924   0.01228   0.00690  -0.0824   0.7637   0.0056
  -6.000  -0.2649   0.01181   0.00633  -0.0824   0.7577   0.0057
  -5.750  -0.2373   0.01142   0.00584  -0.0824   0.7515   0.0058
  -5.500  -0.2098   0.01083   0.00515  -0.0824   0.7457   0.0060
  -5.250  -0.1823   0.01029   0.00451  -0.0824   0.7393   0.0062
  -5.000  -0.1544   0.00991   0.00404  -0.0825   0.7334   0.0064
  -4.750  -0.1263   0.00959   0.00367  -0.0825   0.7271   0.0067
  -4.500  -0.0982   0.00934   0.00335  -0.0825   0.7208   0.0070
  -4.250  -0.0699   0.00910   0.00307  -0.0825   0.7147   0.0075
  -4.000  -0.0417   0.00888   0.00278  -0.0826   0.7080   0.0080
  -3.750  -0.0133   0.00868   0.00252  -0.0826   0.7020   0.0083
  -3.500   0.0150   0.00844   0.00223  -0.0826   0.6951   0.0089
  -3.250   0.0434   0.00826   0.00199  -0.0826   0.6888   0.0098
  -3.000   0.0719   0.00811   0.00180  -0.0827   0.6821   0.0108
  -2.500   0.1286   0.00773   0.00145  -0.0828   0.6688   0.0302
  -2.000   0.1852   0.00740   0.00123  -0.0830   0.6551   0.0706
  -1.750   0.2136   0.00729   0.00115  -0.0830   0.6479   0.0893
  -1.500   0.2420   0.00718   0.00108  -0.0831   0.6410   0.1119
  -1.250   0.2703   0.00705   0.00103  -0.0832   0.6335   0.1454
  -1.000   0.2987   0.00696   0.00098  -0.0833   0.6263   0.1720
  -0.750   0.3271   0.00688   0.00095  -0.0834   0.6185   0.1980
  -0.500   0.3554   0.00679   0.00093  -0.0835   0.6111   0.2322
  -0.250   0.3837   0.00673   0.00092  -0.0836   0.6025   0.2644
   0.000   0.4120   0.00666   0.00092  -0.0837   0.5940   0.2997
   0.250   0.4401   0.00661   0.00092  -0.0837   0.5840   0.3372
   0.500   0.4681   0.00656   0.00094  -0.0838   0.5720   0.3825
   0.750   0.4962   0.00650   0.00097  -0.0839   0.5601   0.4309
   1.000   0.5241   0.00641   0.00101  -0.0840   0.5491   0.4943
   1.250   0.5517   0.00633   0.00106  -0.0840   0.5378   0.5634
   1.500   0.5791   0.00624   0.00113  -0.0840   0.5257   0.6402
   1.750   0.6059   0.00611   0.00121  -0.0838   0.5128   0.7311
   2.000   0.6306   0.00592   0.00130  -0.0830   0.5003   0.8423
   2.250   0.6611   0.00576   0.00134  -0.0833   0.4865   1.0000
   2.500   0.6889   0.00590   0.00141  -0.0833   0.4727   1.0000
   2.750   0.7165   0.00605   0.00149  -0.0833   0.4578   1.0000
   3.000   0.7440   0.00621   0.00159  -0.0833   0.4422   1.0000
   3.250   0.7714   0.00639   0.00170  -0.0832   0.4255   1.0000
   3.500   0.7985   0.00660   0.00182  -0.0832   0.4064   1.0000
   3.750   0.8255   0.00681   0.00194  -0.0831   0.3872   1.0000
   4.000   0.8523   0.00704   0.00210  -0.0830   0.3667   1.0000
   4.250   0.8789   0.00731   0.00226  -0.0829   0.3444   1.0000
   4.500   0.9051   0.00761   0.00245  -0.0827   0.3202   1.0000
   4.750   0.9313   0.00790   0.00265  -0.0825   0.2968   1.0000
   5.000   0.9570   0.00823   0.00287  -0.0823   0.2723   1.0000
   5.250   0.9827   0.00857   0.00310  -0.0821   0.2497   1.0000
   5.500   1.0078   0.00896   0.00338  -0.0818   0.2231   1.0000
   5.750   1.0319   0.00946   0.00370  -0.0814   0.1910   1.0000
   6.000   1.0565   0.00988   0.00400  -0.0810   0.1664   1.0000
   6.250   1.0810   0.01028   0.00430  -0.0807   0.1463   1.0000
   6.500   1.1059   0.01064   0.00460  -0.0804   0.1310   1.0000
   6.750   1.1303   0.01104   0.00492  -0.0800   0.1147   1.0000
   7.000   1.1539   0.01149   0.00528  -0.0795   0.0977   1.0000
   7.250   1.1771   0.01197   0.00566  -0.0789   0.0807   1.0000
   7.500   1.2003   0.01244   0.00607  -0.0784   0.0665   1.0000
   7.750   1.2225   0.01297   0.00652  -0.0777   0.0521   1.0000
   8.000   1.2443   0.01351   0.00698  -0.0770   0.0400   1.0000
   8.250   1.2664   0.01400   0.00744  -0.0763   0.0322   1.0000
   8.500   1.2880   0.01453   0.00793  -0.0755   0.0249   1.0000
   8.750   1.3080   0.01514   0.00850  -0.0745   0.0160   1.0000
   9.000   1.3278   0.01575   0.00908  -0.0735   0.0111   1.0000
   9.250   1.3481   0.01628   0.00963  -0.0726   0.0095   1.0000
   9.500   1.3679   0.01681   0.01019  -0.0715   0.0085   1.0000
   9.750   1.3875   0.01730   0.01073  -0.0705   0.0081   1.0000
  10.000   1.4060   0.01784   0.01131  -0.0693   0.0077   1.0000
  10.250   1.4230   0.01840   0.01191  -0.0678   0.0073   1.0000
  10.500   1.4363   0.01902   0.01257  -0.0658   0.0070   1.0000
  10.750   1.4481   0.01970   0.01330  -0.0636   0.0067   1.0000
  11.000   1.4590   0.02047   0.01414  -0.0614   0.0064   1.0000
  11.250   1.4686   0.02139   0.01514  -0.0592   0.0062   1.0000
  11.500   1.4799   0.02224   0.01605  -0.0575   0.0061   1.0000
  11.750   1.4914   0.02312   0.01699  -0.0558   0.0060   1.0000
  12.000   1.5019   0.02412   0.01806  -0.0542   0.0059   1.0000
  12.250   1.5119   0.02520   0.01921  -0.0527   0.0058   1.0000
  12.500   1.5211   0.02638   0.02048  -0.0512   0.0057   1.0000
  12.750   1.5295   0.02767   0.02185  -0.0498   0.0055   1.0000
  13.000   1.5374   0.02905   0.02330  -0.0484   0.0055   1.0000
  13.250   1.5440   0.03060   0.02493  -0.0472   0.0053   1.0000
  13.500   1.5496   0.03230   0.02672  -0.0460   0.0053   1.0000
  13.750   1.5569   0.03390   0.02838  -0.0451   0.0051   1.0000
  14.000   1.5604   0.03590   0.03048  -0.0441   0.0050   1.0000
  14.250   1.5657   0.03781   0.03247  -0.0434   0.0049   1.0000
  14.500   1.5682   0.04008   0.03482  -0.0427   0.0048   1.0000
  14.750   1.5696   0.04252   0.03735  -0.0422   0.0047   1.0000
  15.000   1.5694   0.04525   0.04020  -0.0418   0.0047   1.0000
  15.250   1.5669   0.04836   0.04340  -0.0417   0.0045   1.0000
  15.500   1.5642   0.05163   0.04678  -0.0418   0.0044   1.0000
  15.750   1.5591   0.05537   0.05064  -0.0421   0.0044   1.0000
  16.000   1.5523   0.05951   0.05490  -0.0428   0.0044   1.0000
  16.250   1.5418   0.06436   0.05988  -0.0439   0.0043   1.0000
  16.500   1.5323   0.06931   0.06496  -0.0453   0.0042   1.0000
  16.750   1.5264   0.07388   0.06965  -0.0468   0.0042   1.0000
  17.000   1.5192   0.07879   0.07468  -0.0485   0.0042   1.0000
  17.250   1.5116   0.08396   0.07997  -0.0504   0.0042   1.0000
  17.500   1.5031   0.08943   0.08556  -0.0527   0.0042   1.0000
  17.750   1.4922   0.09545   0.09171  -0.0553   0.0041   1.0000
  18.000   1.4797   0.10193   0.09831  -0.0583   0.0041   1.0000
  18.250   1.4690   0.10829   0.10480  -0.0613   0.0041   1.0000
  18.500   1.4567   0.11499   0.11162  -0.0646   0.0041   1.0000
  18.750   1.4437   0.12202   0.11878  -0.0683   0.0041   1.0000
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