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CAP 21 (TraCFoil) (cap21c-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: CAP 21 (TraCFoil) (cap21c-il)
Reynolds number: 100,000
Max Cl/Cd: 17.06 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cap21c-il-100000.txt
Download as CSV file: xf-cap21c-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CAP 21   (TraCFoil)                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5193   0.12777   0.12179   0.0309   1.0005   0.2046
 -10.250  -0.5610   0.12513   0.11916   0.0243   1.0005   0.2124
 -10.000  -0.5430   0.12042   0.11447   0.0248   1.0005   0.2138
  -9.750  -0.5144   0.11730   0.11137   0.0267   1.0005   0.2160
  -9.500  -0.4988   0.11466   0.10875   0.0271   1.0005   0.2205
  -9.250  -0.5395   0.11051   0.10462   0.0207   1.0005   0.2286
  -9.000  -0.4993   0.10777   0.10190   0.0241   1.0005   0.2313
  -8.750  -0.4826   0.10531   0.09945   0.0247   1.0005   0.2365
  -8.500  -0.5168   0.10085   0.09504   0.0192   1.0005   0.2443
  -8.250  -0.4845   0.09824   0.09243   0.0216   1.0005   0.2467
  -8.000  -0.4679   0.09582   0.09005   0.0222   1.0005   0.2517
  -7.750  -0.4940   0.09142   0.08568   0.0177   1.0005   0.2603
  -7.500  -0.4597   0.08964   0.08395   0.0205   1.0005   0.2645
  -7.250  -0.4874   0.08554   0.07990   0.0161   1.0005   0.2755
  -7.000  -0.5846   0.06395   0.05797  -0.0068   1.0005   0.2437
  -6.750  -0.5684   0.06110   0.05514  -0.0062   1.0005   0.2446
  -6.500  -0.5667   0.05560   0.04950  -0.0084   1.0005   0.2413
  -6.250  -0.5760   0.04886   0.04242  -0.0113   1.0005   0.2419
  -6.000  -0.5813   0.04305   0.03606  -0.0126   1.0005   0.2433
  -5.750  -0.5538   0.04291   0.03630  -0.0108   1.0005   0.2463
  -5.500  -0.5351   0.04157   0.03502  -0.0097   1.0005   0.2490
  -5.250  -0.5207   0.03949   0.03284  -0.0091   1.0005   0.2525
  -5.000  -0.5092   0.03666   0.02972  -0.0088   1.0005   0.2564
  -4.750  -0.4953   0.03407   0.02679  -0.0085   1.0005   0.2595
  -4.500  -0.4736   0.03303   0.02596  -0.0074   1.0005   0.2618
  -4.250  -0.4527   0.03192   0.02494  -0.0064   1.0005   0.2645
  -4.000  -0.3499   0.02977   0.02171  -0.0202   0.6655   0.2735
  -3.750  -0.3310   0.02961   0.02052  -0.0184   0.5010   0.2758
  -3.500  -0.3049   0.02915   0.01979  -0.0180   0.4648   0.2783
  -3.250  -0.2784   0.02856   0.01897  -0.0178   0.4430   0.2811
  -3.000  -0.2517   0.02798   0.01812  -0.0176   0.4274   0.2848
  -2.750  -0.2246   0.02744   0.01719  -0.0176   0.4151   0.2889
  -2.500  -0.1976   0.02687   0.01645  -0.0174   0.4048   0.2921
  -2.250  -0.1698   0.02646   0.01601  -0.0171   0.3959   0.2951
  -2.000  -0.1420   0.02617   0.01551  -0.0170   0.3884   0.2982
  -1.750  -0.1136   0.02582   0.01506  -0.0169   0.3805   0.3023
  -1.500  -0.0854   0.02559   0.01457  -0.0168   0.3737   0.3062
  -1.250  -0.0574   0.02530   0.01436  -0.0166   0.3670   0.3099
  -1.000  -0.0290   0.02514   0.01415  -0.0164   0.3614   0.3135
  -0.750  -0.0004   0.02514   0.01397  -0.0163   0.3568   0.3172
  -0.500   0.0286   0.02506   0.01385  -0.0162   0.3517   0.3210
  -0.250   0.0565   0.02490   0.01377  -0.0160   0.3462   0.3248
   0.000   0.0845   0.02504   0.01383  -0.0157   0.3415   0.3299
   0.250   0.1131   0.02510   0.01395  -0.0156   0.3364   0.3356
   0.500   0.1410   0.02512   0.01409  -0.0153   0.3321   0.3407
   0.750   0.1690   0.02530   0.01428  -0.0150   0.3283   0.3464
   1.000   0.1971   0.02563   0.01460  -0.0148   0.3245   0.3523
   1.250   0.2242   0.02576   0.01501  -0.0145   0.3196   0.3583
   1.500   0.2519   0.02603   0.01529  -0.0142   0.3151   0.3667
   1.750   0.2788   0.02634   0.01568  -0.0138   0.3115   0.3755
   2.000   0.3054   0.02685   0.01642  -0.0134   0.3082   0.3856
   2.250   0.3316   0.02732   0.01716  -0.0130   0.3039   0.3974
   2.500   0.3576   0.02766   0.01768  -0.0125   0.2996   0.4114
   2.750   0.3838   0.02801   0.01808  -0.0119   0.2960   0.4316
   3.000   0.4072   0.02865   0.01923  -0.0112   0.2920   0.4639
   3.250   0.4275   0.02888   0.02035  -0.0100   0.2880   0.5726
   3.500   0.4635   0.02870   0.02121  -0.0084   0.2831   0.9862
   3.750   0.5043   0.02971   0.02197  -0.0109   0.2786   0.9995
   4.000   0.5201   0.03119   0.02371  -0.0096   0.2741   0.9995
   4.250   0.5385   0.03251   0.02510  -0.0085   0.2704   0.9995
   4.500   0.5596   0.03351   0.02602  -0.0074   0.2672   0.9995
   4.750   0.5849   0.03428   0.02651  -0.0066   0.2644   0.9995
   5.000   0.5924   0.03707   0.02984  -0.0055   0.2593   0.9995
   5.250   0.6090   0.03876   0.03164  -0.0047   0.2545   0.9995
   5.500   0.6332   0.03939   0.03213  -0.0039   0.2511   0.9995
   6.000   0.6488   0.04626   0.03950  -0.0035   0.2443   0.9995
   6.250   0.6460   0.05133   0.04487  -0.0046   0.2406   0.9995
   6.500   0.6708   0.05166   0.04510  -0.0035   0.2365   0.9995
   6.750   0.7213   0.04852   0.04142  -0.0009   0.2335   0.9995
   7.000   0.6645   0.06179   0.05553  -0.0065   0.2312   0.9995
   7.250   0.6519   0.06931   0.06320  -0.0104   0.2343   0.9995
   7.500   0.6646   0.07264   0.06651  -0.0104   0.2335   0.9995
   8.000   0.5149   0.10125   0.09540  -0.0380   0.2576   0.9995
   8.250   0.5280   0.10379   0.09791  -0.0379   0.2526   0.9995
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