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CH10 (smoothed) (ch10sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: CH10 (smoothed) (ch10sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 163.97 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ch10sm-il-1000000-n5.txt
Download as CSV file: xf-ch10sm-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500   0.2402   0.09742   0.09422  -0.1559   0.7408   0.0068
 -10.250   0.2483   0.09461   0.09139  -0.1571   0.7372   0.0069
  -9.750   0.2636   0.08849   0.08527  -0.1601   0.7305   0.0073
  -7.750   0.3324   0.01694   0.01281  -0.2587   0.7025   0.0121
  -7.500   0.3673   0.01515   0.01073  -0.2627   0.6992   0.0123
  -7.250   0.3999   0.01393   0.00931  -0.2653   0.6961   0.0127
  -7.000   0.4295   0.01339   0.00865  -0.2664   0.6929   0.0130
  -6.750   0.4588   0.01297   0.00813  -0.2673   0.6899   0.0134
  -6.500   0.4887   0.01252   0.00759  -0.2683   0.6870   0.0137
  -6.250   0.5186   0.01204   0.00699  -0.2693   0.6838   0.0141
  -6.000   0.5481   0.01161   0.00643  -0.2701   0.6806   0.0144
  -5.750   0.5771   0.01125   0.00594  -0.2708   0.6775   0.0147
  -5.500   0.6062   0.01094   0.00551  -0.2714   0.6745   0.0150
  -5.250   0.6356   0.01065   0.00514  -0.2720   0.6716   0.0153
  -5.000   0.6651   0.01030   0.00470  -0.2728   0.6684   0.0157
  -4.750   0.6940   0.01007   0.00441  -0.2733   0.6652   0.0163
  -4.500   0.7222   0.00994   0.00421  -0.2736   0.6620   0.0169
  -4.250   0.7506   0.00981   0.00403  -0.2739   0.6591   0.0175
  -4.000   0.7796   0.00966   0.00382  -0.2744   0.6563   0.0181
  -3.750   0.8083   0.00952   0.00364  -0.2748   0.6533   0.0186
  -3.500   0.8368   0.00939   0.00345  -0.2751   0.6501   0.0193
  -3.250   0.8645   0.00930   0.00331  -0.2753   0.6468   0.0203
  -3.000   0.8923   0.00924   0.00321  -0.2755   0.6439   0.0214
  -2.750   0.9208   0.00916   0.00311  -0.2758   0.6413   0.0225
  -2.500   0.9490   0.00909   0.00302  -0.2761   0.6383   0.0243
  -2.250   0.9767   0.00906   0.00297  -0.2763   0.6351   0.0265
  -2.000   1.0040   0.00904   0.00293  -0.2763   0.6318   0.0288
  -1.750   1.0314   0.00904   0.00291  -0.2765   0.6289   0.0317
  -1.500   1.0596   0.00901   0.00287  -0.2767   0.6263   0.0345
  -1.250   1.0873   0.00901   0.00287  -0.2769   0.6232   0.0382
  -1.000   1.1146   0.00902   0.00287  -0.2770   0.6198   0.0421
  -0.750   1.1413   0.00905   0.00289  -0.2770   0.6165   0.0465
  -0.500   1.1679   0.00909   0.00291  -0.2769   0.6135   0.0511
  -0.250   1.1954   0.00910   0.00294  -0.2771   0.6107   0.0573
   0.000   1.2224   0.00912   0.00297  -0.2772   0.6073   0.0637
   0.250   1.2488   0.00916   0.00301  -0.2771   0.6039   0.0707
   0.500   1.2747   0.00923   0.00307  -0.2769   0.6005   0.0815
   0.750   1.3010   0.00927   0.00314  -0.2769   0.5974   0.0953
   1.000   1.3278   0.00929   0.00321  -0.2770   0.5942   0.1174
   1.250   1.3544   0.00930   0.00330  -0.2770   0.5907   0.1639
   1.500   1.3801   0.00934   0.00342  -0.2769   0.5870   0.2172
   1.750   1.4047   0.00942   0.00356  -0.2766   0.5835   0.2611
   2.000   1.4309   0.00944   0.00367  -0.2766   0.5806   0.3107
   2.250   1.4559   0.00949   0.00380  -0.2763   0.5769   0.3578
   2.500   1.4796   0.00957   0.00395  -0.2758   0.5730   0.4017
   2.750   1.5028   0.00968   0.00414  -0.2752   0.5692   0.4566
   3.000   1.5279   0.00975   0.00432  -0.2750   0.5658   0.5248
   3.500   1.5767   0.00990   0.00473  -0.2743   0.5577   0.6705
   3.750   1.5971   0.00974   0.00499  -0.2731   0.5535   1.0000
   4.000   1.6206   0.00991   0.00514  -0.2726   0.5497   1.0000
   4.250   1.6430   0.01009   0.00532  -0.2718   0.5452   1.0000
   4.500   1.6635   0.01035   0.00556  -0.2707   0.5403   1.0000
   4.750   1.6843   0.01060   0.00579  -0.2697   0.5360   1.0000
   5.000   1.7061   0.01081   0.00601  -0.2689   0.5314   1.0000
   5.250   1.7261   0.01110   0.00629  -0.2677   0.5263   1.0000
   5.500   1.7448   0.01143   0.00661  -0.2663   0.5215   1.0000
   5.750   1.7657   0.01170   0.00689  -0.2654   0.5165   1.0000
   6.000   1.7845   0.01205   0.00723  -0.2641   0.5108   1.0000
   6.250   1.8020   0.01246   0.00763  -0.2626   0.5053   1.0000
   6.500   1.8214   0.01281   0.00800  -0.2615   0.4996   1.0000
   6.750   1.8378   0.01329   0.00847  -0.2599   0.4936   1.0000
   7.000   1.8558   0.01371   0.00891  -0.2585   0.4884   1.0000
   7.250   1.8732   0.01417   0.00937  -0.2572   0.4823   1.0000
   7.500   1.8873   0.01480   0.01000  -0.2552   0.4764   1.0000
   7.750   1.9055   0.01525   0.01047  -0.2540   0.4709   1.0000
   8.000   1.9199   0.01589   0.01112  -0.2522   0.4644   1.0000
   8.250   1.9345   0.01654   0.01178  -0.2505   0.4583   1.0000
   8.500   1.9491   0.01721   0.01247  -0.2488   0.4516   1.0000
   8.750   1.9609   0.01804   0.01330  -0.2467   0.4447   1.0000
   9.000   1.9725   0.01891   0.01418  -0.2447   0.4354   1.0000
   9.250   1.9766   0.02024   0.01546  -0.2415   0.4202   1.0000
   9.500   1.9744   0.02201   0.01715  -0.2376   0.4010   1.0000
   9.750   1.9730   0.02383   0.01889  -0.2339   0.3815   1.0000
  10.000   1.9721   0.02567   0.02068  -0.2305   0.3637   1.0000
  10.250   1.9694   0.02773   0.02267  -0.2269   0.3454   1.0000
  10.500   1.9634   0.03012   0.02497  -0.2231   0.3258   1.0000
  10.750   1.9562   0.03267   0.02744  -0.2192   0.3050   1.0000
  11.000   1.9485   0.03538   0.03006  -0.2155   0.2843   1.0000
  11.250   1.9407   0.03820   0.03279  -0.2120   0.2656   1.0000
  11.500   1.9333   0.04104   0.03556  -0.2086   0.2466   1.0000
  11.750   1.9252   0.04401   0.03847  -0.2054   0.2274   1.0000
  12.000   1.9144   0.04732   0.04169  -0.2020   0.2076   1.0000
  12.250   1.9018   0.05089   0.04515  -0.1986   0.1845   1.0000
  12.500   1.8871   0.05472   0.04887  -0.1952   0.1615   1.0000
  12.750   1.8709   0.05883   0.05285  -0.1919   0.1373   1.0000
  13.000   1.8551   0.06301   0.05691  -0.1888   0.1135   1.0000
  13.250   1.8343   0.06779   0.06156  -0.1855   0.0862   1.0000
  13.500   1.8216   0.07186   0.06556  -0.1830   0.0679   1.0000
  13.750   1.8124   0.07562   0.06928  -0.1809   0.0536   1.0000
  14.000   1.8064   0.07904   0.07267  -0.1791   0.0424   1.0000
  14.250   1.8015   0.08236   0.07599  -0.1775   0.0340   1.0000
  14.500   1.7981   0.08556   0.07920  -0.1760   0.0277   1.0000
  14.750   1.7968   0.08854   0.08219  -0.1748   0.0230   1.0000
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