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ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: ARA-D 10% AIRFOIL (arad10-il)
Reynolds number: 500,000
Max Cl/Cd: 82.15 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-arad10-il-500000.txt
Download as CSV file: xf-arad10-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ARA-D 10% AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3006   0.08271   0.08055  -0.0326   1.0000   0.0312
  -8.500  -0.2959   0.08018   0.07804  -0.0321   1.0000   0.0314
  -8.250  -0.2942   0.07774   0.07564  -0.0313   1.0000   0.0317
  -8.000  -0.5244   0.02866   0.02497  -0.0658   1.0000   0.0209
  -7.750  -0.5066   0.02469   0.02043  -0.0664   0.9996   0.0214
  -7.500  -0.4734   0.02180   0.01704  -0.0689   0.9979   0.0219
  -7.250  -0.4388   0.01983   0.01468  -0.0710   0.9961   0.0223
  -7.000  -0.4033   0.01837   0.01290  -0.0730   0.9945   0.0227
  -6.750  -0.3688   0.01693   0.01135  -0.0748   0.9926   0.0234
  -6.500  -0.3336   0.01616   0.01052  -0.0765   0.9900   0.0241
  -6.250  -0.2975   0.01541   0.00967  -0.0782   0.9877   0.0250
  -6.000  -0.2605   0.01468   0.00880  -0.0801   0.9858   0.0261
  -5.750  -0.2233   0.01381   0.00785  -0.0822   0.9842   0.0274
  -5.500  -0.1873   0.01337   0.00742  -0.0838   0.9812   0.0291
  -5.250  -0.1530   0.01288   0.00684  -0.0850   0.9762   0.0312
  -5.000  -0.1183   0.01240   0.00639  -0.0863   0.9718   0.0337
  -4.750  -0.0871   0.01195   0.00590  -0.0868   0.9644   0.0369
  -4.500  -0.0565   0.01171   0.00564  -0.0871   0.9570   0.0407
  -4.250  -0.0289   0.01139   0.00533  -0.0867   0.9468   0.0449
  -4.000  -0.0015   0.01115   0.00507  -0.0862   0.9374   0.0497
  -3.750   0.0253   0.01102   0.00492  -0.0856   0.9264   0.0543
  -3.500   0.0525   0.01076   0.00467  -0.0851   0.9153   0.0592
  -3.250   0.0796   0.01067   0.00452  -0.0845   0.9043   0.0637
  -3.000   0.1070   0.01045   0.00432  -0.0841   0.8925   0.0699
  -2.750   0.1348   0.01028   0.00413  -0.0838   0.8796   0.0764
  -2.500   0.1624   0.01017   0.00399  -0.0834   0.8643   0.0829
  -2.250   0.1898   0.01000   0.00379  -0.0829   0.8454   0.0907
  -2.000   0.2175   0.00991   0.00362  -0.0824   0.8260   0.0992
  -1.750   0.2458   0.00984   0.00351  -0.0822   0.8083   0.1090
  -1.500   0.2742   0.00975   0.00339  -0.0821   0.7908   0.1201
  -1.250   0.3028   0.00969   0.00329  -0.0819   0.7733   0.1311
  -0.750   0.3603   0.00963   0.00315  -0.0819   0.7396   0.1555
  -0.250   0.4179   0.00957   0.00305  -0.0819   0.7047   0.1851
   0.000   0.4468   0.00955   0.00302  -0.0819   0.6876   0.2049
   0.250   0.4757   0.00950   0.00300  -0.0820   0.6701   0.2342
   0.500   0.5045   0.00935   0.00300  -0.0822   0.6513   0.3011
   0.750   0.5242   0.00744   0.00288  -0.0803   0.6338   1.0000
   1.000   0.5530   0.00758   0.00288  -0.0803   0.6146   1.0000
   1.250   0.5816   0.00774   0.00290  -0.0803   0.5938   1.0000
   1.500   0.6101   0.00793   0.00294  -0.0803   0.5712   1.0000
   1.750   0.6386   0.00811   0.00299  -0.0803   0.5474   1.0000
   2.000   0.6668   0.00832   0.00305  -0.0803   0.5221   1.0000
   2.250   0.6950   0.00855   0.00314  -0.0803   0.4931   1.0000
   2.500   0.7228   0.00883   0.00324  -0.0802   0.4606   1.0000
   2.750   0.7505   0.00915   0.00337  -0.0802   0.4261   1.0000
   3.000   0.7778   0.00952   0.00353  -0.0801   0.3879   1.0000
   3.250   0.8049   0.00992   0.00372  -0.0801   0.3485   1.0000
   3.500   0.8320   0.01033   0.00393  -0.0800   0.3152   1.0000
   4.000   0.8865   0.01106   0.00437  -0.0799   0.2688   1.0000
   4.250   0.9138   0.01139   0.00459  -0.0799   0.2527   1.0000
   4.500   0.9410   0.01172   0.00483  -0.0798   0.2392   1.0000
   4.750   0.9684   0.01201   0.00506  -0.0798   0.2276   1.0000
   5.000   0.9957   0.01229   0.00529  -0.0797   0.2179   1.0000
   5.250   1.0225   0.01264   0.00556  -0.0796   0.2089   1.0000
   5.500   1.0499   0.01287   0.00580  -0.0795   0.2017   1.0000
   5.750   1.0763   0.01323   0.00609  -0.0794   0.1940   1.0000
   6.000   1.1035   0.01348   0.00634  -0.0793   0.1878   1.0000
   6.250   1.1300   0.01380   0.00663  -0.0791   0.1817   1.0000
   6.500   1.1561   0.01415   0.00696  -0.0789   0.1759   1.0000
   6.750   1.1829   0.01440   0.00722  -0.0787   0.1705   1.0000
   7.000   1.2085   0.01479   0.00757  -0.0785   0.1648   1.0000
   7.250   1.2343   0.01512   0.00791  -0.0782   0.1602   1.0000
   7.500   1.2605   0.01540   0.00821  -0.0780   0.1553   1.0000
   7.750   1.2852   0.01582   0.00859  -0.0776   0.1501   1.0000
   8.000   1.3104   0.01618   0.00898  -0.0772   0.1460   1.0000
   8.250   1.3360   0.01647   0.00930  -0.0769   0.1417   1.0000
   8.500   1.3602   0.01689   0.00970  -0.0765   0.1370   1.0000
   8.750   1.3838   0.01736   0.01018  -0.0759   0.1329   1.0000
   9.000   1.4087   0.01765   0.01053  -0.0755   0.1293   1.0000
   9.250   1.4324   0.01806   0.01094  -0.0749   0.1251   1.0000
   9.500   1.4535   0.01869   0.01153  -0.0740   0.1207   1.0000
   9.750   1.4777   0.01899   0.01192  -0.0735   0.1178   1.0000
  10.000   1.5006   0.01938   0.01235  -0.0729   0.1142   1.0000
  10.250   1.5212   0.01994   0.01289  -0.0719   0.1104   1.0000
  10.500   1.5413   0.02052   0.01351  -0.0708   0.1072   1.0000
  10.750   1.5631   0.02091   0.01398  -0.0699   0.1042   1.0000
  11.000   1.5830   0.02141   0.01451  -0.0688   0.1011   1.0000
  11.250   1.5992   0.02216   0.01524  -0.0672   0.0978   1.0000
  11.500   1.6169   0.02276   0.01591  -0.0658   0.0952   1.0000
  11.750   1.6351   0.02327   0.01651  -0.0644   0.0927   1.0000
  12.000   1.6507   0.02390   0.01719  -0.0627   0.0902   1.0000
  12.250   1.6601   0.02474   0.01805  -0.0600   0.0878   1.0000
  12.500   1.6666   0.02585   0.01919  -0.0570   0.0853   1.0000
  12.750   1.6811   0.02652   0.01999  -0.0553   0.0835   1.0000
  13.000   1.6938   0.02734   0.02089  -0.0535   0.0813   1.0000
  13.250   1.7044   0.02835   0.02195  -0.0516   0.0791   1.0000
  13.500   1.7109   0.02970   0.02333  -0.0495   0.0770   1.0000
  13.750   1.7161   0.03123   0.02493  -0.0473   0.0751   1.0000
  14.000   1.7282   0.03229   0.02611  -0.0460   0.0734   1.0000
  14.250   1.7385   0.03352   0.02744  -0.0447   0.0714   1.0000
  14.500   1.7461   0.03502   0.02900  -0.0434   0.0695   1.0000
  14.750   1.7486   0.03703   0.03105  -0.0419   0.0676   1.0000
  15.000   1.7505   0.03921   0.03331  -0.0406   0.0658   1.0000
  15.250   1.7588   0.04087   0.03510  -0.0398   0.0643   1.0000
  15.500   1.7648   0.04279   0.03713  -0.0391   0.0627   1.0000
  15.750   1.7681   0.04506   0.03949  -0.0385   0.0612   1.0000
  16.000   1.7675   0.04784   0.04233  -0.0380   0.0597   1.0000
  16.250   1.7608   0.05138   0.04594  -0.0376   0.0583   1.0000
  16.500   1.7600   0.05436   0.04904  -0.0374   0.0572   1.0000
  16.750   1.7606   0.05729   0.05212  -0.0376   0.0561   1.0000
  17.000   1.7588   0.06061   0.05557  -0.0379   0.0549   1.0000
  17.250   1.7550   0.06430   0.05938  -0.0384   0.0539   1.0000
  17.500   1.7481   0.06849   0.06366  -0.0392   0.0529   1.0000
  17.750   1.7379   0.07325   0.06851  -0.0404   0.0519   1.0000
  18.000   1.7238   0.07865   0.07400  -0.0418   0.0510   1.0000
  18.250   1.7106   0.08404   0.07950  -0.0433   0.0501   1.0000
  18.500   1.7016   0.08900   0.08462  -0.0450   0.0494   1.0000
  18.750   1.6903   0.09441   0.09018  -0.0469   0.0487   1.0000
  19.000   1.6778   0.10008   0.09599  -0.0491   0.0479   1.0000
  19.250   1.6641   0.10602   0.10205  -0.0515   0.0472   1.0000
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