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S6061 9% (s6061-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S6061 9% (s6061-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.96 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s6061-il-1000000.txt
Download as CSV file: xf-s6061-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6061 9%                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4492   0.07705   0.07562  -0.0176   1.0000   0.0098
  -9.250  -0.4538   0.07175   0.07034  -0.0197   1.0000   0.0099
  -5.750  -0.4217   0.01458   0.00992  -0.0437   0.9354   0.0080
  -5.500  -0.3997   0.01267   0.00772  -0.0423   0.9259   0.0075
  -5.250  -0.3763   0.01156   0.00644  -0.0413   0.9164   0.0074
  -5.000  -0.3516   0.01078   0.00555  -0.0406   0.9072   0.0076
  -4.750  -0.3266   0.01017   0.00483  -0.0399   0.8986   0.0080
  -4.500  -0.3007   0.00970   0.00427  -0.0395   0.8895   0.0088
  -4.250  -0.2742   0.00936   0.00386  -0.0391   0.8808   0.0092
  -4.000  -0.2485   0.00883   0.00319  -0.0386   0.8722   0.0098
  -3.750  -0.2217   0.00841   0.00269  -0.0383   0.8630   0.0107
  -3.500  -0.1946   0.00816   0.00239  -0.0381   0.8543   0.0123
  -3.250  -0.1675   0.00789   0.00204  -0.0378   0.8452   0.0164
  -3.000  -0.1412   0.00737   0.00173  -0.0376   0.8357   0.0674
  -2.750  -0.1144   0.00705   0.00155  -0.0375   0.8265   0.1127
  -2.500  -0.0877   0.00674   0.00140  -0.0374   0.8166   0.1678
  -2.250  -0.0611   0.00635   0.00126  -0.0373   0.8061   0.2500
  -2.000  -0.0349   0.00590   0.00114  -0.0372   0.7956   0.3561
  -1.750  -0.0086   0.00553   0.00104  -0.0371   0.7850   0.4539
  -1.500   0.0178   0.00522   0.00096  -0.0369   0.7739   0.5463
  -1.250   0.0442   0.00494   0.00092  -0.0367   0.7625   0.6333
  -1.000   0.0709   0.00477   0.00090  -0.0364   0.7511   0.6961
  -0.750   0.0979   0.00468   0.00088  -0.0361   0.7395   0.7409
  -0.500   0.1248   0.00462   0.00087  -0.0358   0.7273   0.7763
  -0.250   0.1518   0.00459   0.00087  -0.0355   0.7146   0.8062
   0.000   0.1788   0.00458   0.00087  -0.0352   0.7016   0.8309
   0.250   0.2057   0.00458   0.00088  -0.0348   0.6885   0.8530
   0.500   0.2324   0.00459   0.00090  -0.0344   0.6753   0.8733
   0.750   0.2588   0.00460   0.00092  -0.0340   0.6620   0.8928
   1.000   0.2849   0.00463   0.00094  -0.0335   0.6482   0.9116
   1.250   0.3107   0.00466   0.00097  -0.0328   0.6338   0.9296
   1.500   0.3367   0.00471   0.00100  -0.0322   0.6187   0.9479
   1.750   0.3654   0.00477   0.00102  -0.0323   0.6028   0.9652
   2.000   0.3989   0.00485   0.00105  -0.0335   0.5857   0.9783
   2.250   0.4347   0.00494   0.00110  -0.0353   0.5672   0.9874
   2.500   0.4706   0.00506   0.00115  -0.0371   0.5475   0.9945
   2.750   0.5080   0.00518   0.00120  -0.0393   0.5249   0.9998
   3.000   0.5326   0.00533   0.00126  -0.0388   0.5030   1.0000
   3.250   0.5574   0.00548   0.00136  -0.0382   0.4805   1.0000
   3.500   0.5822   0.00571   0.00146  -0.0377   0.4486   1.0000
   3.750   0.6060   0.00612   0.00161  -0.0371   0.3861   1.0000
   4.000   0.6304   0.00653   0.00179  -0.0367   0.3332   1.0000
   4.250   0.6557   0.00684   0.00197  -0.0364   0.2973   1.0000
   4.500   0.6811   0.00718   0.00216  -0.0361   0.2617   1.0000
   4.750   0.7064   0.00754   0.00238  -0.0358   0.2264   1.0000
   5.000   0.7314   0.00795   0.00262  -0.0355   0.1879   1.0000
   5.250   0.7555   0.00849   0.00294  -0.0351   0.1400   1.0000
   5.500   0.7792   0.00910   0.00330  -0.0347   0.0926   1.0000
   5.750   0.8016   0.00989   0.00380  -0.0341   0.0391   1.0000
   6.000   0.8254   0.01051   0.00427  -0.0335   0.0181   1.0000
   6.250   0.8506   0.01093   0.00474  -0.0331   0.0152   1.0000
   6.500   0.8761   0.01127   0.00515  -0.0328   0.0147   1.0000
   6.750   0.9012   0.01167   0.00560  -0.0324   0.0139   1.0000
   7.000   0.9258   0.01211   0.00609  -0.0320   0.0129   1.0000
   7.250   0.9499   0.01263   0.00666  -0.0315   0.0122   1.0000
   7.500   0.9731   0.01326   0.00736  -0.0308   0.0115   1.0000
   7.750   0.9944   0.01411   0.00832  -0.0299   0.0109   1.0000
   8.000   1.0121   0.01539   0.00974  -0.0285   0.0103   1.0000
   8.250   1.0335   0.01615   0.01058  -0.0276   0.0100   1.0000
   8.500   1.0569   0.01661   0.01109  -0.0271   0.0096   1.0000
   8.750   1.0786   0.01727   0.01182  -0.0264   0.0092   1.0000
   9.000   1.0988   0.01811   0.01273  -0.0254   0.0088   1.0000
   9.250   1.1185   0.01898   0.01368  -0.0244   0.0084   1.0000
   9.500   1.1379   0.01982   0.01461  -0.0234   0.0079   1.0000
   9.750   1.1566   0.02069   0.01554  -0.0224   0.0076   1.0000
  10.000   1.1736   0.02168   0.01658  -0.0212   0.0072   1.0000
  10.250   1.1736   0.02562   0.02078  -0.0182   0.0065   1.0000
  10.500   1.1937   0.02565   0.02088  -0.0173   0.0064   1.0000
  10.750   1.2108   0.02620   0.02152  -0.0161   0.0061   1.0000
  11.000   1.2226   0.02733   0.02279  -0.0143   0.0059   1.0000
  11.250   1.2282   0.02874   0.02433  -0.0116   0.0058   1.0000
  11.500   1.2347   0.02978   0.02548  -0.0093   0.0054   1.0000
  11.750   1.2386   0.03119   0.02701  -0.0070   0.0053   1.0000
  12.000   1.2416   0.03272   0.02867  -0.0050   0.0051   1.0000
  12.250   1.2457   0.03415   0.03020  -0.0035   0.0050   1.0000
  12.500   1.2441   0.03634   0.03254  -0.0019   0.0049   1.0000
  12.750   1.2482   0.03791   0.03418  -0.0011   0.0047   1.0000
  13.000   1.2387   0.04134   0.03781  -0.0002   0.0047   1.0000
  13.250   1.2403   0.04348   0.04002  -0.0001   0.0046   1.0000
  13.500   1.2358   0.04663   0.04329  -0.0004   0.0045   1.0000
  13.750   1.2198   0.05166   0.04854  -0.0013   0.0046   1.0000
  14.000   1.2236   0.05402   0.05092  -0.0024   0.0044   1.0000
  14.250   1.2071   0.05977   0.05687  -0.0046   0.0044   1.0000
  14.500   1.1958   0.06504   0.06224  -0.0073   0.0043   1.0000
  14.750   1.1768   0.07213   0.06952  -0.0110   0.0044   1.0000
  15.000   1.1562   0.08001   0.07754  -0.0157   0.0042   1.0000
  15.250   1.1436   0.08705   0.08473  -0.0200   0.0043   1.0000
  15.500   1.1235   0.09613   0.09398  -0.0256   0.0044   1.0000
  15.750   1.0881   0.10952   0.10760  -0.0337   0.0045   1.0000
  16.000   1.0802   0.11651   0.11464  -0.0380   0.0044   1.0000
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