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CH10 (smoothed) (ch10sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: CH10 (smoothed) (ch10sm-il)
Reynolds number: 500,000
Max Cl/Cd: 135.37 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ch10sm-il-500000.txt
Download as CSV file: xf-ch10sm-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250   0.3048   0.09230   0.08899  -0.1579   0.8119   0.0166
 -11.000   0.3119   0.08991   0.08661  -0.1585   0.8080   0.0171
 -10.750   0.2460   0.10341   0.10000  -0.1570   0.8244   0.0161
 -10.500   0.2558   0.10113   0.09772  -0.1580   0.8200   0.0165
 -10.250   0.2657   0.09884   0.09539  -0.1592   0.8159   0.0170
 -10.000   0.2756   0.09650   0.09301  -0.1604   0.8120   0.0178
  -9.750   0.2841   0.09403   0.09056  -0.1622   0.8076   0.0186
  -9.500   0.2906   0.09182   0.08834  -0.1645   0.8032   0.0188
  -9.250   0.2968   0.08961   0.08609  -0.1668   0.7993   0.0189
  -9.000   0.3088   0.08646   0.08294  -0.1670   0.7957   0.0190
  -8.750   0.3214   0.08411   0.08058  -0.1672   0.7916   0.0193
  -8.500   0.3328   0.08204   0.07850  -0.1679   0.7876   0.0196
  -8.250   0.3442   0.07999   0.07640  -0.1690   0.7840   0.0200
  -8.000   0.3551   0.07790   0.07431  -0.1702   0.7803   0.0206
  -7.750   0.3655   0.07571   0.07213  -0.1714   0.7762   0.0215
  -7.500   0.3721   0.07327   0.06968  -0.1750   0.7719   0.0228
  -7.250   0.3793   0.07079   0.06717  -0.1783   0.7679   0.0229
  -7.000   0.3916   0.06805   0.06445  -0.1775   0.7645   0.0232
  -6.750   0.4046   0.06623   0.06263  -0.1775   0.7607   0.0236
  -6.500   0.4157   0.06463   0.06102  -0.1780   0.7571   0.0242
  -6.250   0.4291   0.06280   0.05915  -0.1796   0.7537   0.0253
  -6.000   0.4482   0.05979   0.05614  -0.1873   0.7497   0.0274
  -5.750   0.4702   0.05585   0.05222  -0.1951   0.7456   0.0277
  -5.500   0.4816   0.05399   0.05034  -0.1938   0.7423   0.0282
  -5.250   0.4991   0.05238   0.04870  -0.1945   0.7392   0.0287
  -5.000   0.5209   0.05040   0.04668  -0.1975   0.7360   0.0298
  -4.750   0.5464   0.04769   0.04398  -0.2029   0.7323   0.0318
  -4.500   0.5945   0.04147   0.03768  -0.2189   0.7286   0.0339
  -4.250   0.6136   0.04051   0.03670  -0.2189   0.7254   0.0347
  -4.000   0.6459   0.03834   0.03445  -0.2238   0.7224   0.0363
  -3.750   0.7746   0.02038   0.01555  -0.2648   0.7200   0.0316
  -3.500   0.8238   0.01579   0.01015  -0.2722   0.7169   0.0318
  -3.250   0.8573   0.01443   0.00842  -0.2741   0.7136   0.0326
  -3.000   0.8891   0.01352   0.00723  -0.2753   0.7107   0.0336
  -2.750   0.9197   0.01301   0.00662  -0.2763   0.7078   0.0353
  -2.500   0.9487   0.01288   0.00642  -0.2768   0.7048   0.0377
  -2.250   0.9763   0.01267   0.00614  -0.2769   0.7014   0.0398
  -2.000   1.0055   0.01219   0.00562  -0.2776   0.6982   0.0431
  -1.750   1.0341   0.01207   0.00544  -0.2779   0.6952   0.0469
  -1.500   1.0639   0.01187   0.00519  -0.2786   0.6923   0.0521
  -1.250   1.0921   0.01187   0.00515  -0.2789   0.6893   0.0574
  -1.000   1.1194   0.01168   0.00499  -0.2791   0.6860   0.0638
  -0.750   1.1466   0.01168   0.00497  -0.2792   0.6828   0.0702
  -0.500   1.1751   0.01155   0.00483  -0.2796   0.6797   0.0793
  -0.250   1.2045   0.01152   0.00474  -0.2801   0.6768   0.0891
   0.000   1.2323   0.01152   0.00474  -0.2804   0.6737   0.1028
   0.250   1.2590   0.01144   0.00477  -0.2805   0.6704   0.1318
   0.500   1.2869   0.01129   0.00487  -0.2809   0.6670   0.2420
   0.750   1.3147   0.01123   0.00498  -0.2813   0.6639   0.3434
   1.000   1.3435   0.01125   0.00509  -0.2818   0.6609   0.4221
   1.250   1.3696   0.01129   0.00526  -0.2818   0.6578   0.4921
   1.500   1.3948   0.01130   0.00542  -0.2815   0.6543   0.5603
   1.750   1.4207   0.01129   0.00556  -0.2814   0.6508   0.6415
   2.000   1.4439   0.01093   0.00564  -0.2806   0.6478   1.0000
   2.250   1.4728   0.01111   0.00572  -0.2811   0.6446   1.0000
   2.500   1.4963   0.01124   0.00587  -0.2805   0.6412   1.0000
   2.750   1.5211   0.01138   0.00599  -0.2801   0.6376   1.0000
   3.000   1.5466   0.01152   0.00609  -0.2799   0.6342   1.0000
   3.250   1.5736   0.01168   0.00618  -0.2801   0.6309   1.0000
   3.500   1.5988   0.01186   0.00636  -0.2799   0.6276   1.0000
   3.750   1.6215   0.01202   0.00654  -0.2791   0.6237   1.0000
   4.000   1.6453   0.01218   0.00668  -0.2786   0.6200   1.0000
   4.250   1.6705   0.01234   0.00681  -0.2784   0.6165   1.0000
   4.500   1.6960   0.01255   0.00699  -0.2783   0.6129   1.0000
   4.750   1.7162   0.01273   0.00722  -0.2771   0.6088   1.0000
   5.000   1.7380   0.01291   0.00741  -0.2762   0.6048   1.0000
   5.250   1.7618   0.01310   0.00758  -0.2758   0.6010   1.0000
   5.500   1.7847   0.01332   0.00781  -0.2751   0.5971   1.0000
   5.750   1.8013   0.01354   0.00808  -0.2732   0.5926   1.0000
   6.000   1.8202   0.01376   0.00831  -0.2718   0.5884   1.0000
   6.250   1.8437   0.01399   0.00851  -0.2713   0.5844   1.0000
   6.500   1.8594   0.01428   0.00886  -0.2693   0.5799   1.0000
   6.750   1.8747   0.01457   0.00921  -0.2673   0.5751   1.0000
   7.000   1.8935   0.01486   0.00949  -0.2659   0.5707   1.0000
   7.250   1.9113   0.01519   0.00985  -0.2644   0.5661   1.0000
   7.500   1.9241   0.01559   0.01033  -0.2620   0.5610   1.0000
   7.750   1.9403   0.01597   0.01072  -0.2603   0.5562   1.0000
   8.000   1.9584   0.01636   0.01111  -0.2589   0.5516   1.0000
   8.250   1.9696   0.01688   0.01174  -0.2564   0.5462   1.0000
   8.500   1.9841   0.01737   0.01225  -0.2544   0.5411   1.0000
   8.750   2.0000   0.01786   0.01276  -0.2528   0.5361   1.0000
   9.000   2.0100   0.01853   0.01353  -0.2502   0.5303   1.0000
   9.250   2.0235   0.01912   0.01414  -0.2482   0.5247   1.0000
   9.500   2.0337   0.01988   0.01496  -0.2458   0.5184   1.0000
   9.750   2.0391   0.02084   0.01594  -0.2427   0.5095   1.0000
  10.000   2.0420   0.02201   0.01716  -0.2393   0.4991   1.0000
  10.250   2.0449   0.02326   0.01842  -0.2360   0.4885   1.0000
  10.500   2.0470   0.02462   0.01979  -0.2327   0.4779   1.0000
  10.750   2.0493   0.02608   0.02130  -0.2296   0.4667   1.0000
  11.000   2.0503   0.02771   0.02295  -0.2264   0.4552   1.0000
  11.250   2.0491   0.02956   0.02480  -0.2230   0.4426   1.0000
  11.500   2.0466   0.03159   0.02682  -0.2197   0.4296   1.0000
  11.750   2.0436   0.03377   0.02899  -0.2164   0.4160   1.0000
  12.000   2.0399   0.03610   0.03132  -0.2132   0.4015   1.0000
  12.250   2.0331   0.03875   0.03395  -0.2098   0.3859   1.0000
  12.500   2.0246   0.04165   0.03682  -0.2064   0.3696   1.0000
  12.750   2.0156   0.04470   0.03983  -0.2031   0.3519   1.0000
  13.000   2.0043   0.04804   0.04313  -0.1997   0.3332   1.0000
  13.250   1.9924   0.05152   0.04656  -0.1965   0.3154   1.0000
  13.500   1.9800   0.05515   0.05014  -0.1934   0.2979   1.0000
  13.750   1.9666   0.05896   0.05391  -0.1903   0.2806   1.0000
  14.000   1.9538   0.06279   0.05769  -0.1875   0.2629   1.0000
  14.250   1.9402   0.06678   0.06162  -0.1848   0.2440   1.0000
  14.500   1.9247   0.07106   0.06584  -0.1822   0.2245   1.0000
  14.750   1.9077   0.07561   0.07031  -0.1796   0.2043   1.0000
  15.000   1.8896   0.08033   0.07494  -0.1772   0.1816   1.0000
  15.250   1.8688   0.08547   0.07995  -0.1748   0.1567   1.0000
  15.500   1.8461   0.09096   0.08530  -0.1726   0.1296   1.0000
  15.750   1.8218   0.09673   0.09090  -0.1706   0.1020   1.0000
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