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CH10 (smoothed) (ch10sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: CH10 (smoothed) (ch10sm-il)
Reynolds number: 200,000
Max Cl/Cd: 73.16 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ch10sm-il-200000.txt
Download as CSV file: xf-ch10sm-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CH10 (smoothed)                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.2781   0.10238   0.09810  -0.1646   0.8691   0.0325
  -9.750   0.2819   0.10141   0.09713  -0.1666   0.8639   0.0330
  -9.500   0.2843   0.10066   0.09635  -0.1694   0.8599   0.0332
  -9.250   0.2971   0.09651   0.09222  -0.1686   0.8553   0.0335
  -9.000   0.3099   0.09340   0.08909  -0.1680   0.8510   0.0341
  -8.750   0.3211   0.09106   0.08673  -0.1685   0.8473   0.0349
  -8.500   0.3329   0.08877   0.08439  -0.1697   0.8443   0.0360
  -8.250   0.3385   0.08718   0.08285  -0.1697   0.8386   0.0373
  -8.000   0.3450   0.08569   0.08135  -0.1712   0.8336   0.0392
  -7.750   0.3449   0.08559   0.08124  -0.1753   0.8291   0.0399
  -7.500   0.3390   0.08536   0.08109  -0.1750   0.8218   0.0400
  -7.250   0.3641   0.07962   0.07531  -0.1732   0.8201   0.0409
  -7.000   0.3773   0.07722   0.07288  -0.1733   0.8169   0.0418
  -6.750   0.3904   0.07502   0.07064  -0.1744   0.8141   0.0430
  -6.500   0.3908   0.07400   0.06967  -0.1730   0.8081   0.0441
  -6.250   0.3944   0.07268   0.06836  -0.1728   0.8033   0.0455
  -6.000   0.4087   0.07141   0.06707  -0.1799   0.7996   0.0478
  -5.750   0.4201   0.07039   0.06608  -0.1869   0.7933   0.0483
  -5.500   0.4214   0.06728   0.06300  -0.1827   0.7892   0.0489
  -5.250   0.4342   0.06488   0.06058  -0.1802   0.7865   0.0501
  -5.000   0.4546   0.06266   0.05830  -0.1817   0.7842   0.0526
  -4.750   0.4636   0.06133   0.05699  -0.1828   0.7794   0.0551
  -4.250   0.5174   0.05522   0.05081  -0.1985   0.7707   0.0598
  -4.000   0.5385   0.05307   0.04862  -0.1984   0.7688   0.0615
  -3.750   0.5447   0.05211   0.04769  -0.1973   0.7634   0.0633
  -3.500   0.6218   0.04615   0.04147  -0.2207   0.7590   0.0717
  -3.250   0.6311   0.04494   0.04032  -0.2169   0.7562   0.0735
  -3.000   0.6640   0.04303   0.03834  -0.2196   0.7544   0.0784
  -2.750   0.7431   0.03756   0.03253  -0.2372   0.7530   0.0887
  -2.500   0.7500   0.03721   0.03223  -0.2349   0.7472   0.0915
  -2.250   0.8578   0.02837   0.02224  -0.2575   0.7454   0.0732
  -2.000   0.9068   0.02536   0.01868  -0.2628   0.7428   0.0646
  -1.750   0.9497   0.02379   0.01664  -0.2662   0.7407   0.0668
  -1.500   0.9901   0.02279   0.01522  -0.2687   0.7388   0.0716
  -1.250   1.0285   0.02182   0.01413  -0.2712   0.7371   0.0782
  -1.000   1.0390   0.02238   0.01467  -0.2684   0.7311   0.0837
  -0.750   1.0684   0.02189   0.01414  -0.2690   0.7276   0.0918
  -0.500   1.1023   0.02147   0.01360  -0.2703   0.7252   0.1019
  -0.250   1.1379   0.02099   0.01308  -0.2720   0.7232   0.1164
   0.000   1.1750   0.02055   0.01264  -0.2739   0.7215   0.1360
   0.250   1.1822   0.02129   0.01354  -0.2707   0.7150   0.1526
   0.500   1.2127   0.02101   0.01353  -0.2717   0.7117   0.2312
   0.750   1.2469   0.02059   0.01357  -0.2732   0.7094   0.4472
   1.000   1.2810   0.02033   0.01347  -0.2745   0.7074   0.5681
   1.250   1.3018   0.02054   0.01391  -0.2734   0.7037   0.6791
   1.500   1.3096   0.02072   0.01445  -0.2697   0.6983   1.0000
   1.750   1.3395   0.02080   0.01438  -0.2703   0.6954   1.0000
   2.000   1.3733   0.02074   0.01418  -0.2716   0.6932   1.0000
   2.250   1.4092   0.02064   0.01392  -0.2732   0.6912   1.0000
   2.500   1.4133   0.02171   0.01506  -0.2694   0.6849   1.0000
   2.750   1.4379   0.02196   0.01526  -0.2691   0.6812   1.0000
   3.000   1.4705   0.02190   0.01511  -0.2701   0.6787   1.0000
   3.250   1.5059   0.02177   0.01488  -0.2716   0.6766   1.0000
   3.500   1.5176   0.02257   0.01571  -0.2691   0.6717   1.0000
   3.750   1.5330   0.02314   0.01630  -0.2672   0.6668   1.0000
   4.000   1.5642   0.02310   0.01622  -0.2680   0.6640   1.0000
   4.250   1.5999   0.02293   0.01598  -0.2696   0.6618   1.0000
   4.500   1.6237   0.02327   0.01631  -0.2692   0.6583   1.0000
   4.750   1.6246   0.02430   0.01744  -0.2648   0.6519   1.0000
   5.000   1.6551   0.02427   0.01740  -0.2655   0.6489   1.0000
   5.250   1.6921   0.02403   0.01710  -0.2673   0.6465   1.0000
   5.500   1.7118   0.02447   0.01756  -0.2662   0.6425   1.0000
   5.750   1.7118   0.02546   0.01868  -0.2617   0.6362   1.0000
   6.000   1.7442   0.02533   0.01852  -0.2627   0.6331   1.0000
   6.250   1.7844   0.02498   0.01813  -0.2651   0.6307   1.0000
   6.500   1.7766   0.02621   0.01949  -0.2591   0.6242   1.0000
   6.750   1.7929   0.02656   0.01990  -0.2573   0.6195   1.0000
   7.000   1.8311   0.02622   0.01955  -0.2594   0.6166   1.0000
   7.250   1.8803   0.02570   0.01899  -0.2634   0.6142   1.0000
   7.500   1.8410   0.02778   0.02126  -0.2521   0.6057   1.0000
   7.750   1.8739   0.02753   0.02104  -0.2531   0.6022   1.0000
   8.000   1.9243   0.02684   0.02032  -0.2572   0.5995   1.0000
   8.250   1.8875   0.02904   0.02269  -0.2467   0.5912   1.0000
   8.500   1.9164   0.02887   0.02256  -0.2470   0.5871   1.0000
   8.750   1.9681   0.02799   0.02168  -0.2512   0.5843   1.0000
   9.000   1.9285   0.03055   0.02441  -0.2407   0.5757   1.0000
   9.250   1.9594   0.03026   0.02416  -0.2413   0.5715   1.0000
   9.500   2.0135   0.02920   0.02311  -0.2456   0.5685   1.0000
   9.750   1.9645   0.03238   0.02649  -0.2342   0.5591   1.0000
  10.000   2.0044   0.03163   0.02577  -0.2361   0.5552   1.0000
  10.250   1.9946   0.03338   0.02763  -0.2309   0.5481   1.0000
  10.500   2.0048   0.03408   0.02841  -0.2286   0.5418   1.0000
  10.750   2.0577   0.03261   0.02696  -0.2322   0.5380   1.0000
  11.000   2.0126   0.03635   0.03089  -0.2226   0.5282   1.0000
  11.250   2.0501   0.03515   0.02966  -0.2236   0.5210   1.0000
  11.500   2.0295   0.03764   0.03228  -0.2176   0.5110   1.0000
  11.750   2.0219   0.03942   0.03412  -0.2133   0.5007   1.0000
  12.000   2.0292   0.04004   0.03474  -0.2107   0.4892   1.0000
  12.250   2.0294   0.04137   0.03610  -0.2075   0.4774   1.0000
  12.500   2.0089   0.04471   0.03956  -0.2026   0.4659   1.0000
  12.750   2.0026   0.04700   0.04190  -0.1993   0.4538   1.0000
  13.000   2.0005   0.04903   0.04397  -0.1965   0.4414   1.0000
  13.250   1.9987   0.05113   0.04608  -0.1938   0.4285   1.0000
  13.500   1.9940   0.05360   0.04856  -0.1910   0.4148   1.0000
  13.750   1.9861   0.05650   0.05148  -0.1882   0.4006   1.0000
  14.000   1.9763   0.05975   0.05475  -0.1854   0.3857   1.0000
  14.250   1.9668   0.06305   0.05807  -0.1828   0.3704   1.0000
  14.500   1.9569   0.06649   0.06152  -0.1803   0.3549   1.0000
  14.750   1.9461   0.07014   0.06519  -0.1779   0.3391   1.0000
  15.000   1.9344   0.07396   0.06902  -0.1756   0.3228   1.0000
  15.250   1.9215   0.07802   0.07309  -0.1735   0.3054   1.0000
  15.500   1.9072   0.08233   0.07737  -0.1714   0.2866   1.0000
  15.750   1.8904   0.08701   0.08199  -0.1694   0.2666   1.0000
  16.000   1.8716   0.09204   0.08697  -0.1676   0.2442   1.0000
  16.250   1.8493   0.09763   0.09244  -0.1659   0.2202   1.0000
  16.500   1.8246   0.10366   0.09834  -0.1645   0.1928   1.0000
  16.750   1.7973   0.11021   0.10470  -0.1635   0.1603   1.0000
  17.000   1.7683   0.11708   0.11134  -0.1628   0.1273   1.0000
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