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CAP 21 (TraCFoil) (cap21c-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: CAP 21 (TraCFoil) (cap21c-il)
Reynolds number: 100,000
Max Cl/Cd: 26 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cap21c-il-100000-n5.txt
Download as CSV file: xf-cap21c-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6551   0.10093   0.09449   0.0106   1.0005   0.1183
 -10.750  -0.6537   0.09723   0.09080   0.0090   1.0005   0.1212
 -10.500  -0.9111   0.04967   0.04266  -0.0287   1.0005   0.1394
 -10.250  -0.8885   0.04974   0.04281  -0.0276   1.0005   0.1414
 -10.000  -0.8607   0.05056   0.04372  -0.0262   1.0005   0.1431
  -9.750  -0.8370   0.05090   0.04411  -0.0251   1.0005   0.1449
  -9.500  -0.8191   0.05037   0.04359  -0.0244   1.0005   0.1469
  -9.250  -0.8070   0.04886   0.04203  -0.0243   1.0005   0.1495
  -9.000  -0.7988   0.04660   0.03967  -0.0244   1.0005   0.1525
  -8.750  -0.7909   0.04412   0.03705  -0.0245   1.0005   0.1559
  -8.500  -0.7818   0.04165   0.03439  -0.0244   1.0005   0.1596
  -8.250  -0.7700   0.03950   0.03205  -0.0241   1.0005   0.1635
  -8.000  -0.7547   0.03793   0.03032  -0.0235   1.0005   0.1672
  -7.750  -0.7369   0.03680   0.02899  -0.0228   1.0005   0.1702
  -7.500  -0.7175   0.03595   0.02801  -0.0220   1.0005   0.1722
  -7.250  -0.6994   0.03475   0.02671  -0.0212   1.0005   0.1740
  -7.000  -0.6855   0.03237   0.02424  -0.0202   1.0005   0.1775
  -6.750  -0.6655   0.03140   0.02329  -0.0192   1.0005   0.1799
  -6.500  -0.6444   0.03073   0.02265  -0.0181   1.0005   0.1820
  -6.250  -0.6232   0.03014   0.02208  -0.0170   1.0005   0.1842
  -6.000  -0.6020   0.02955   0.02151  -0.0159   1.0005   0.1864
  -5.750  -0.5806   0.02906   0.02105  -0.0147   1.0005   0.1891
  -5.500  -0.5591   0.02859   0.02057  -0.0136   1.0005   0.1921
  -5.250  -0.5104   0.02798   0.01993  -0.0177   0.9757   0.1966
  -5.000  -0.4647   0.02716   0.01898  -0.0210   0.8924   0.2005
  -4.750  -0.4279   0.02697   0.01775  -0.0213   0.5921   0.2035
  -4.500  -0.4072   0.02699   0.01698  -0.0200   0.4374   0.2058
  -4.250  -0.3823   0.02664   0.01626  -0.0195   0.3896   0.2081
  -4.000  -0.3561   0.02626   0.01562  -0.0192   0.3653   0.2104
  -3.750  -0.3295   0.02586   0.01502  -0.0189   0.3501   0.2125
  -3.500  -0.3029   0.02560   0.01456  -0.0185   0.3384   0.2144
  -3.250  -0.2759   0.02548   0.01429  -0.0181   0.3302   0.2163
  -3.000  -0.2485   0.02538   0.01412  -0.0177   0.3237   0.2179
  -2.750  -0.2222   0.02463   0.01325  -0.0174   0.3177   0.2210
  -2.500  -0.1960   0.02374   0.01224  -0.0172   0.3122   0.2249
  -2.250  -0.1692   0.02325   0.01165  -0.0168   0.3069   0.2279
  -2.000  -0.1421   0.02293   0.01123  -0.0164   0.3019   0.2306
  -1.750  -0.1149   0.02276   0.01097  -0.0160   0.2970   0.2332
  -1.500  -0.0876   0.02274   0.01085  -0.0157   0.2917   0.2358
  -1.250  -0.0598   0.02255   0.01064  -0.0153   0.2889   0.2384
  -1.000  -0.0319   0.02236   0.01047  -0.0150   0.2856   0.2410
  -0.750  -0.0039   0.02222   0.01033  -0.0147   0.2816   0.2438
  -0.500   0.0240   0.02212   0.01023  -0.0143   0.2775   0.2467
  -0.250   0.0519   0.02208   0.01019  -0.0140   0.2739   0.2497
   0.000   0.0799   0.02207   0.01019  -0.0136   0.2705   0.2529
   0.250   0.1078   0.02210   0.01022  -0.0133   0.2671   0.2563
   0.500   0.1357   0.02218   0.01030  -0.0130   0.2638   0.2605
   0.750   0.1635   0.02230   0.01042  -0.0126   0.2607   0.2649
   1.000   0.1913   0.02246   0.01057  -0.0122   0.2577   0.2688
   1.250   0.2190   0.02264   0.01075  -0.0119   0.2547   0.2719
   1.500   0.2466   0.02285   0.01097  -0.0115   0.2519   0.2742
   1.750   0.2735   0.02292   0.01114  -0.0110   0.2491   0.2795
   2.000   0.3003   0.02314   0.01143  -0.0106   0.2462   0.2851
   2.250   0.3269   0.02354   0.01190  -0.0102   0.2426   0.2909
   2.500   0.3528   0.02438   0.01284  -0.0098   0.2374   0.2970
   2.750   0.3789   0.02495   0.01352  -0.0094   0.2341   0.3038
   3.000   0.4060   0.02503   0.01368  -0.0089   0.2325   0.3115
   3.500   0.4593   0.02546   0.01444  -0.0081   0.2286   0.3351
   3.750   0.4853   0.02574   0.01494  -0.0076   0.2262   0.3567
   4.000   0.5108   0.02600   0.01551  -0.0072   0.2236   0.4002
   4.250   0.5340   0.02602   0.01616  -0.0064   0.2209   0.5256
   4.500   0.5505   0.02573   0.01683  -0.0033   0.2180   0.7716
   4.750   0.5959   0.02607   0.01748  -0.0058   0.2134   0.9758
   5.000   0.6272   0.02651   0.01791  -0.0065   0.2093   0.9995
   5.250   0.6510   0.02691   0.01831  -0.0056   0.2058   0.9995
   5.500   0.6748   0.02732   0.01868  -0.0048   0.2026   0.9995
   5.750   0.6986   0.02780   0.01913  -0.0040   0.1999   0.9995
   6.000   0.7223   0.02829   0.01958  -0.0032   0.1974   0.9995
   6.250   0.7458   0.02882   0.02008  -0.0024   0.1950   0.9995
   6.500   0.7686   0.02956   0.02078  -0.0017   0.1923   0.9995
   6.750   0.7884   0.03106   0.02230  -0.0009   0.1888   0.9995
   7.000   0.8070   0.03260   0.02394  -0.0001   0.1863   0.9995
   7.250   0.8282   0.03344   0.02489   0.0007   0.1848   0.9995
   7.500   0.8482   0.03443   0.02606   0.0015   0.1827   0.9995
   7.750   0.8670   0.03554   0.02732   0.0022   0.1798   0.9995
   8.000   0.8848   0.03674   0.02866   0.0030   0.1763   0.9995
   8.250   0.9021   0.03794   0.02998   0.0037   0.1725   0.9995
   8.500   0.9193   0.03908   0.03122   0.0045   0.1688   0.9995
   8.750   0.9360   0.04022   0.03244   0.0052   0.1657   0.9995
   9.000   0.9523   0.04138   0.03367   0.0060   0.1630   0.9995
   9.250   0.9693   0.04234   0.03468   0.0068   0.1606   0.9995
   9.500   0.9871   0.04311   0.03547   0.0076   0.1585   0.9995
   9.750   1.0056   0.04375   0.03610   0.0085   0.1565   0.9995
  10.000   1.0234   0.04441   0.03681   0.0094   0.1547   0.9995
  10.250   1.0386   0.04535   0.03775   0.0103   0.1528   0.9995
  10.500   1.0480   0.04709   0.03950   0.0112   0.1505   0.9995
  10.750   1.0143   0.05276   0.04542   0.0115   0.1484   0.9995
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