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CH10 (smoothed) (ch10sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: CH10 (smoothed) (ch10sm-il)
Reynolds number: 100,000
Max Cl/Cd: 38.08 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ch10sm-il-100000-n5.txt
Download as CSV file: xf-ch10sm-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.2254   0.11328   0.10740  -0.1531   0.8610   0.0391
 -10.250   0.2271   0.11256   0.10669  -0.1544   0.8554   0.0397
 -10.000   0.2266   0.11213   0.10628  -0.1556   0.8495   0.0400
  -9.750   0.2460   0.10672   0.10085  -0.1554   0.8470   0.0408
  -9.500   0.2595   0.10376   0.09785  -0.1564   0.8443   0.0418
  -9.250   0.2636   0.10211   0.09622  -0.1558   0.8383   0.0427
  -9.000   0.2714   0.10005   0.09416  -0.1563   0.8337   0.0437
  -8.750   0.2814   0.09777   0.09185  -0.1575   0.8303   0.0450
  -8.500   0.2864   0.09612   0.09021  -0.1577   0.8255   0.0462
  -8.250   0.2876   0.09504   0.08916  -0.1578   0.8196   0.0473
  -8.000   0.2905   0.09397   0.08809  -0.1593   0.8154   0.0479
  -7.750   0.2866   0.09344   0.08759  -0.1589   0.8094   0.0481
  -7.500   0.2813   0.09283   0.08703  -0.1579   0.8030   0.0482
  -7.250   0.2841   0.09137   0.08556  -0.1590   0.7993   0.0483
  -7.000   0.3154   0.08517   0.07931  -0.1587   0.7987   0.0497
  -6.750   0.3114   0.08434   0.07854  -0.1552   0.7920   0.0508
  -6.500   0.3143   0.08292   0.07713  -0.1540   0.7873   0.0528
  -6.250   0.3202   0.08129   0.07548  -0.1544   0.7841   0.0553
  -6.000   0.3053   0.08156   0.07585  -0.1506   0.7764   0.0566
  -5.750   0.3041   0.08126   0.07557  -0.1534   0.7707   0.0580
  -5.500   0.3258   0.07878   0.07302  -0.1612   0.7679   0.0584
  -5.250   0.2972   0.07976   0.07413  -0.1536   0.7576   0.0585
  -5.000   0.3148   0.07647   0.07082  -0.1570   0.7548   0.0587
  -4.750   0.3272   0.07296   0.06729  -0.1545   0.7533   0.0596
  -4.500   0.2870   0.07474   0.06921  -0.1453   0.7417   0.0593
  -4.250   0.3025   0.07190   0.06635  -0.1450   0.7396   0.0603
  -4.000   0.2758   0.07273   0.06728  -0.1383   0.7300   0.0603
  -3.750   0.2870   0.07069   0.06522  -0.1388   0.7260   0.0613
  -3.500   0.3166   0.06740   0.06186  -0.1438   0.7241   0.0623
  -3.250   0.4039   0.05832   0.05244  -0.1683   0.7231   0.0480
  -3.000   0.3811   0.05942   0.05366  -0.1624   0.7122   0.0490
  -2.750   0.4127   0.05663   0.05077  -0.1659   0.7102   0.0460
  -2.500   0.4968   0.04979   0.04362  -0.1843   0.7099   0.0434
  -2.250   0.6289   0.04018   0.03311  -0.2132   0.7114   0.0461
  -2.000   0.7269   0.03446   0.02614  -0.2301   0.7122   0.0485
  -1.750   0.7638   0.03361   0.02520  -0.2326   0.7103   0.0521
  -1.500   0.8136   0.03195   0.02301  -0.2373   0.7092   0.0559
  -1.250   0.8583   0.03077   0.02152  -0.2408   0.7081   0.0613
  -0.750   0.8867   0.03173   0.02224  -0.2377   0.6970   0.0692
  -0.500   0.9211   0.03117   0.02161  -0.2392   0.6950   0.0766
  -0.250   0.9578   0.03060   0.02085  -0.2408   0.6934   0.0857
   0.000   0.9967   0.02993   0.02016  -0.2429   0.6922   0.0969
   0.250   1.0373   0.02931   0.01947  -0.2453   0.6911   0.1121
   0.750   1.0533   0.03152   0.02175  -0.2403   0.6785   0.1370
   1.000   1.0913   0.03099   0.02128  -0.2422   0.6772   0.1847
   1.250   1.1311   0.03035   0.02090  -0.2445   0.6761   0.3187
   1.750   1.1405   0.03306   0.02399  -0.2387   0.6630   0.4783
   2.000   1.1746   0.03248   0.02365  -0.2395   0.6617   0.6243
   2.250   1.2010   0.03154   0.02298  -0.2385   0.6604   1.0000
   2.750   1.2051   0.03503   0.02638  -0.2323   0.6466   1.0000
   3.000   1.2252   0.03567   0.02691  -0.2315   0.6430   1.0000
   4.000   1.2505   0.04239   0.03352  -0.2223   0.6173   1.0000
   4.250   1.2811   0.04207   0.03311  -0.2225   0.6159   1.0000
   4.500   1.3136   0.04160   0.03257  -0.2230   0.6149   1.0000
   5.000   1.2751   0.04992   0.04104  -0.2142   0.5910   1.0000
   5.250   1.2965   0.05029   0.04137  -0.2135   0.5878   1.0000
   5.500   1.3241   0.05005   0.04109  -0.2133   0.5861   1.0000
   5.750   1.3538   0.04962   0.04063  -0.2133   0.5848   1.0000
   6.000   1.3853   0.04902   0.04000  -0.2135   0.5839   1.0000
   6.500   1.3437   0.05827   0.04942  -0.2055   0.5585   1.0000
   6.750   1.3683   0.05818   0.04932  -0.2050   0.5563   1.0000
   7.000   1.3960   0.05776   0.04892  -0.2047   0.5548   1.0000
   7.250   1.4258   0.05712   0.04827  -0.2046   0.5537   1.0000
   7.750   1.4099   0.06400   0.05529  -0.1992   0.5341   1.0000
   8.000   1.4570   0.06131   0.05262  -0.2001   0.5369   1.0000
   8.500   1.4536   0.06680   0.05825  -0.1957   0.5202   1.0000
   8.750   1.4987   0.06422   0.05568  -0.1963   0.5223   1.0000
   9.250   1.4970   0.06954   0.06117  -0.1922   0.5060   1.0000
   9.750   1.4710   0.07811   0.06993  -0.1874   0.4832   1.0000
  10.000   1.4925   0.07809   0.06998  -0.1866   0.4802   1.0000
  10.250   1.5195   0.07738   0.06934  -0.1861   0.4785   1.0000
  10.500   1.5491   0.07633   0.06838  -0.1857   0.4772   1.0000
  11.000   1.5566   0.08074   0.07297  -0.1827   0.4625   1.0000
  11.500   1.5645   0.08516   0.07759  -0.1799   0.4479   1.0000
  11.750   1.5943   0.08396   0.07651  -0.1794   0.4465   1.0000
  12.250   1.6021   0.08841   0.08117  -0.1768   0.4318   1.0000
  12.750   1.6103   0.09284   0.08585  -0.1744   0.4172   1.0000
  13.000   1.6421   0.09123   0.08436  -0.1739   0.4157   1.0000
  13.500   1.6364   0.09759   0.09096  -0.1714   0.3984   1.0000
  14.000   1.6589   0.10000   0.09365  -0.1696   0.3864   1.0000
  14.500   1.6676   0.10441   0.09833  -0.1677   0.3719   1.0000
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