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CAST 10-2/DOA 2 AIRFOIL (cast102-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: CAST 10-2/DOA 2 AIRFOIL (cast102-il)
Reynolds number: 50,000
Max Cl/Cd: 30.31 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cast102-il-50000-n5.txt
Download as CSV file: xf-cast102-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CAST 10-2/DOA 2 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4863   0.08813   0.08148  -0.0494   1.0000   0.0730
  -9.250  -0.5316   0.09157   0.08454  -0.0473   1.0000   0.0795
  -9.000  -0.5810   0.08797   0.08092  -0.0464   1.0000   0.0714
  -8.750  -0.5875   0.08483   0.07783  -0.0442   1.0000   0.0692
  -8.500  -0.6032   0.08174   0.07474  -0.0419   1.0000   0.0674
  -8.250  -0.6205   0.07850   0.07144  -0.0395   1.0000   0.0653
  -8.000  -0.6595   0.07579   0.06805  -0.0356   1.0000   0.0594
  -7.750  -0.6509   0.07169   0.06408  -0.0344   1.0000   0.0581
  -7.500  -0.6512   0.06833   0.06063  -0.0324   1.0000   0.0568
  -7.250  -0.6512   0.06504   0.05717  -0.0304   1.0000   0.0556
  -7.000  -0.6493   0.06173   0.05363  -0.0285   1.0000   0.0542
  -6.750  -0.6450   0.05841   0.05000  -0.0266   1.0000   0.0528
  -6.500  -0.6379   0.05510   0.04627  -0.0248   1.0000   0.0513
  -6.250  -0.6274   0.05192   0.04261  -0.0231   1.0000   0.0499
  -6.000  -0.6137   0.04917   0.03926  -0.0213   1.0000   0.0487
  -5.750  -0.5978   0.04674   0.03638  -0.0199   1.0000   0.0483
  -5.500  -0.5807   0.04423   0.03371  -0.0190   1.0000   0.0493
  -5.250  -0.5623   0.04213   0.03141  -0.0181   1.0000   0.0506
  -5.000  -0.5422   0.04019   0.02917  -0.0172   1.0000   0.0518
  -4.750  -0.5203   0.03832   0.02699  -0.0162   1.0000   0.0522
  -4.500  -0.4969   0.03660   0.02496  -0.0153   1.0000   0.0524
  -4.250  -0.4729   0.03507   0.02317  -0.0145   1.0000   0.0528
  -4.000  -0.4486   0.03374   0.02165  -0.0135   1.0000   0.0535
  -3.750  -0.4245   0.03266   0.02041  -0.0125   1.0000   0.0553
  -3.500  -0.4010   0.03184   0.01941  -0.0113   1.0000   0.0580
  -3.250  -0.3781   0.03102   0.01849  -0.0099   1.0000   0.0601
  -3.000  -0.3567   0.03009   0.01755  -0.0086   1.0000   0.0620
  -2.750  -0.3355   0.02932   0.01668  -0.0076   1.0000   0.0644
  -2.500  -0.3137   0.02864   0.01588  -0.0069   1.0000   0.0681
  -2.250  -0.2915   0.02805   0.01514  -0.0063   1.0000   0.0738
  -2.000  -0.2682   0.02736   0.01439  -0.0062   1.0000   0.0815
  -1.750  -0.2437   0.02676   0.01373  -0.0063   1.0000   0.0927
  -1.500  -0.2193   0.02392   0.01351  -0.0071   1.0000   0.5731
  -1.250  -0.2121   0.02429   0.01428  -0.0008   1.0000   0.7461
  -1.000  -0.2067   0.02461   0.01470   0.0058   1.0000   0.8106
  -0.750  -0.2022   0.02484   0.01499   0.0129   0.9986   0.8706
  -0.500  -0.1782   0.02523   0.01533   0.0162   0.9958   0.9315
  -0.250  -0.1378   0.02550   0.01538   0.0130   0.9927   0.9473
   0.000  -0.0993   0.02571   0.01539   0.0098   0.9889   0.9559
   0.250  -0.0576   0.02602   0.01555   0.0058   0.9853   0.9649
   0.500  -0.0195   0.02624   0.01565   0.0024   0.9806   0.9748
   0.750   0.0214   0.02654   0.01585  -0.0015   0.9759   0.9861
   1.000   0.0598   0.02678   0.01603  -0.0051   0.9703   1.0000
   1.250   0.0847   0.02689   0.01609  -0.0061   0.9630   1.0000
   1.500   0.1158   0.02717   0.01631  -0.0082   0.9565   1.0000
   1.750   0.1462   0.02742   0.01653  -0.0101   0.9481   1.0000
   2.000   0.1819   0.02774   0.01683  -0.0127   0.9387   1.0000
   2.250   0.2260   0.02806   0.01715  -0.0166   0.9271   1.0000
   2.500   0.2720   0.02824   0.01736  -0.0206   0.9135   1.0000
   2.750   0.3126   0.02828   0.01746  -0.0234   0.8986   1.0000
   3.000   0.3517   0.02823   0.01749  -0.0257   0.8836   1.0000
   3.250   0.3924   0.02806   0.01743  -0.0280   0.8680   1.0000
   3.500   0.4236   0.02782   0.01729  -0.0284   0.8494   1.0000
   3.750   0.4573   0.02745   0.01704  -0.0291   0.8298   1.0000
   4.000   0.4956   0.02684   0.01662  -0.0301   0.8098   1.0000
   4.250   0.5214   0.02638   0.01630  -0.0291   0.7852   1.0000
   4.500   0.5475   0.02583   0.01589  -0.0280   0.7578   1.0000
   4.750   0.5689   0.02536   0.01558  -0.0260   0.7240   1.0000
   5.000   0.5892   0.02496   0.01535  -0.0239   0.6801   1.0000
   5.250   0.6271   0.02383   0.01426  -0.0234   0.6115   1.0000
   5.500   0.6922   0.02284   0.01249  -0.0265   0.4742   1.0000
   5.750   0.7113   0.02382   0.01293  -0.0248   0.4035   1.0000
   6.000   0.7289   0.02486   0.01365  -0.0234   0.3564   1.0000
   6.250   0.7483   0.02587   0.01443  -0.0223   0.3213   1.0000
   6.500   0.7700   0.02681   0.01529  -0.0216   0.2928   1.0000
   6.750   0.7937   0.02773   0.01617  -0.0213   0.2687   1.0000
   7.000   0.8189   0.02867   0.01707  -0.0212   0.2482   1.0000
   7.250   0.8466   0.02963   0.01803  -0.0214   0.2306   1.0000
   7.500   0.8753   0.03062   0.01911  -0.0219   0.2132   1.0000
   7.750   0.9019   0.03166   0.02026  -0.0219   0.1961   1.0000
   8.000   0.9217   0.03263   0.02132  -0.0211   0.1775   1.0000
   8.500   0.9476   0.03445   0.02314  -0.0177   0.1410   1.0000
   8.750   0.9646   0.03562   0.02447  -0.0166   0.1242   1.0000
   9.000   0.9822   0.03703   0.02601  -0.0154   0.1090   1.0000
   9.250   0.9981   0.03854   0.02760  -0.0142   0.0959   1.0000
   9.500   1.0122   0.04006   0.02911  -0.0127   0.0868   1.0000
   9.750   1.0325   0.04216   0.03155  -0.0120   0.0785   1.0000
  10.000   1.0466   0.04400   0.03344  -0.0107   0.0732   1.0000
  10.250   1.0599   0.04620   0.03600  -0.0092   0.0679   1.0000
  10.500   1.0707   0.04812   0.03802  -0.0076   0.0646   1.0000
  10.750   1.0822   0.05070   0.04080  -0.0062   0.0623   1.0000
  11.000   1.0856   0.05384   0.04442  -0.0039   0.0601   1.0000
  11.250   1.0840   0.05688   0.04784  -0.0015   0.0582   1.0000
  11.500   1.0801   0.05981   0.05105   0.0008   0.0565   1.0000
  11.750   1.0755   0.06266   0.05410   0.0028   0.0550   1.0000
  12.000   1.0713   0.06548   0.05708   0.0044   0.0538   1.0000
  12.250   1.0666   0.06860   0.06031   0.0057   0.0528   1.0000
  12.500   1.0491   0.07307   0.06505   0.0069   0.0525   1.0000
  12.750   1.0267   0.07832   0.07058   0.0070   0.0524   1.0000
  13.000   1.0020   0.08432   0.07683   0.0059   0.0525   1.0000
  13.250   0.9754   0.09133   0.08404   0.0033   0.0526   1.0000
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