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ARA-D 10% AIRFOIL (arad10-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: ARA-D 10% AIRFOIL (arad10-il)
Reynolds number: 200,000
Max Cl/Cd: 61.68 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-arad10-il-200000-n5.txt
Download as CSV file: xf-arad10-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4082   0.09435   0.09059  -0.0243   1.0000   0.0225
  -7.500  -0.4739   0.02911   0.02358  -0.0659   1.0000   0.0222
  -7.250  -0.4495   0.02608   0.02003  -0.0670   0.9986   0.0229
  -7.000  -0.4153   0.02515   0.01902  -0.0690   0.9954   0.0237
  -6.750  -0.3811   0.02365   0.01726  -0.0711   0.9922   0.0248
  -6.500  -0.3471   0.02175   0.01494  -0.0729   0.9884   0.0261
  -6.250  -0.3119   0.02050   0.01349  -0.0749   0.9852   0.0270
  -6.000  -0.2762   0.01966   0.01256  -0.0768   0.9821   0.0282
  -5.750  -0.2424   0.01871   0.01142  -0.0781   0.9770   0.0298
  -5.500  -0.2071   0.01789   0.01048  -0.0797   0.9727   0.0317
  -5.250  -0.1728   0.01734   0.00987  -0.0811   0.9675   0.0343
  -5.000  -0.1394   0.01674   0.00918  -0.0823   0.9610   0.0372
  -4.750  -0.1041   0.01618   0.00853  -0.0837   0.9560   0.0406
  -4.500  -0.0731   0.01574   0.00807  -0.0843   0.9470   0.0441
  -4.250  -0.0394   0.01531   0.00757  -0.0853   0.9405   0.0488
  -4.000  -0.0096   0.01501   0.00726  -0.0855   0.9301   0.0537
  -3.750   0.0213   0.01469   0.00693  -0.0859   0.9212   0.0588
  -3.500   0.0508   0.01440   0.00657  -0.0859   0.9105   0.0645
  -3.250   0.0796   0.01415   0.00633  -0.0859   0.8994   0.0702
  -3.000   0.1085   0.01387   0.00604  -0.0857   0.8886   0.0762
  -2.750   0.1367   0.01367   0.00579  -0.0855   0.8765   0.0829
  -2.500   0.1648   0.01345   0.00559  -0.0852   0.8639   0.0900
  -2.250   0.1930   0.01326   0.00536  -0.0849   0.8514   0.0979
  -2.000   0.2210   0.01310   0.00519  -0.0846   0.8385   0.1069
  -1.750   0.2490   0.01295   0.00502  -0.0843   0.8246   0.1161
  -1.500   0.2765   0.01285   0.00484  -0.0838   0.8065   0.1265
  -1.250   0.3038   0.01274   0.00469  -0.0833   0.7829   0.1378
  -1.000   0.3311   0.01266   0.00454  -0.0827   0.7591   0.1496
  -0.750   0.3589   0.01261   0.00442  -0.0824   0.7390   0.1630
  -0.500   0.3869   0.01256   0.00433  -0.0822   0.7192   0.1781
  -0.250   0.4150   0.01251   0.00425  -0.0820   0.6994   0.1957
   0.000   0.4431   0.01247   0.00420  -0.0818   0.6795   0.2176
   0.250   0.4712   0.01241   0.00416  -0.0817   0.6601   0.2480
   0.500   0.4991   0.01226   0.00414  -0.0817   0.6407   0.3111
   1.000   0.5464   0.01061   0.00396  -0.0790   0.6014   1.0000
   1.250   0.5744   0.01079   0.00397  -0.0789   0.5791   1.0000
   1.500   0.6022   0.01100   0.00401  -0.0787   0.5562   1.0000
   1.750   0.6299   0.01122   0.00406  -0.0785   0.5309   1.0000
   2.250   0.6845   0.01175   0.00422  -0.0781   0.4746   1.0000
   2.500   0.7115   0.01206   0.00435  -0.0779   0.4436   1.0000
   2.750   0.7382   0.01241   0.00449  -0.0776   0.4101   1.0000
   3.000   0.7647   0.01280   0.00467  -0.0774   0.3768   1.0000
   3.250   0.7911   0.01320   0.00488  -0.0772   0.3459   1.0000
   3.500   0.8174   0.01362   0.00512  -0.0770   0.3187   1.0000
   3.750   0.8438   0.01402   0.00537  -0.0768   0.2958   1.0000
   4.000   0.8701   0.01442   0.00565  -0.0766   0.2777   1.0000
   4.250   0.8965   0.01480   0.00593  -0.0764   0.2625   1.0000
   4.500   0.9228   0.01518   0.00623  -0.0762   0.2492   1.0000
   4.750   0.9489   0.01558   0.00655  -0.0759   0.2378   1.0000
   5.000   0.9751   0.01595   0.00686  -0.0757   0.2274   1.0000
   5.250   1.0012   0.01632   0.00719  -0.0755   0.2184   1.0000
   5.500   1.0268   0.01673   0.00755  -0.0752   0.2099   1.0000
   5.750   1.0527   0.01709   0.00791  -0.0749   0.2026   1.0000
   6.000   1.0781   0.01750   0.00828  -0.0746   0.1953   1.0000
   6.250   1.1034   0.01790   0.00868  -0.0742   0.1890   1.0000
   6.500   1.1287   0.01830   0.00908  -0.0739   0.1828   1.0000
   7.000   1.1781   0.01916   0.00995  -0.0730   0.1719   1.0000
   7.250   1.2024   0.01960   0.01040  -0.0725   0.1665   1.0000
   7.500   1.2258   0.02013   0.01089  -0.0719   0.1618   1.0000
   7.750   1.2502   0.02054   0.01138  -0.0714   0.1571   1.0000
   8.000   1.2736   0.02101   0.01188  -0.0709   0.1522   1.0000
   8.250   1.2955   0.02160   0.01243  -0.0701   0.1479   1.0000
   8.500   1.3191   0.02204   0.01297  -0.0695   0.1437   1.0000
   8.750   1.3415   0.02255   0.01354  -0.0688   0.1393   1.0000
   9.000   1.3624   0.02315   0.01413  -0.0678   0.1353   1.0000
   9.250   1.3838   0.02371   0.01476  -0.0670   0.1316   1.0000
   9.500   1.4050   0.02425   0.01539  -0.0661   0.1277   1.0000
   9.750   1.4246   0.02486   0.01604  -0.0650   0.1240   1.0000
  10.000   1.4423   0.02559   0.01676  -0.0636   0.1206   1.0000
  10.250   1.4619   0.02618   0.01749  -0.0625   0.1173   1.0000
  10.500   1.4797   0.02683   0.01823  -0.0612   0.1139   1.0000
  10.750   1.4954   0.02756   0.01900  -0.0595   0.1108   1.0000
  11.000   1.5089   0.02842   0.01988  -0.0577   0.1080   1.0000
  11.250   1.5232   0.02916   0.02076  -0.0558   0.1052   1.0000
  11.500   1.5353   0.02999   0.02170  -0.0537   0.1024   1.0000
  11.750   1.5459   0.03093   0.02271  -0.0515   0.0997   1.0000
  12.000   1.5546   0.03205   0.02386  -0.0494   0.0974   1.0000
  12.250   1.5652   0.03315   0.02508  -0.0475   0.0950   1.0000
  12.500   1.5761   0.03427   0.02634  -0.0458   0.0925   1.0000
  12.750   1.5854   0.03551   0.02769  -0.0442   0.0901   1.0000
  13.000   1.5928   0.03693   0.02918  -0.0425   0.0879   1.0000
  13.250   1.5979   0.03860   0.03089  -0.0409   0.0860   1.0000
  13.500   1.6056   0.04016   0.03262  -0.0396   0.0841   1.0000
  13.750   1.6126   0.04184   0.03446  -0.0383   0.0820   1.0000
  14.000   1.6181   0.04370   0.03644  -0.0372   0.0800   1.0000
  14.250   1.6216   0.04579   0.03863  -0.0363   0.0782   1.0000
  14.500   1.6230   0.04815   0.04107  -0.0355   0.0766   1.0000
  14.750   1.6236   0.05072   0.04372  -0.0348   0.0752   1.0000
  15.000   1.6258   0.05322   0.04642  -0.0343   0.0737   1.0000
  15.250   1.6263   0.05598   0.04935  -0.0340   0.0721   1.0000
  15.500   1.6252   0.05900   0.05252  -0.0339   0.0706   1.0000
  15.750   1.6226   0.06228   0.05593  -0.0341   0.0693   1.0000
  16.000   1.6181   0.06589   0.05964  -0.0345   0.0680   1.0000
  16.250   1.6121   0.06979   0.06362  -0.0351   0.0669   1.0000
  16.500   1.6057   0.07389   0.06784  -0.0359   0.0658   1.0000
  16.750   1.5989   0.07826   0.07242  -0.0370   0.0647   1.0000
  17.000   1.5904   0.08297   0.07732  -0.0384   0.0636   1.0000
  17.250   1.5809   0.08798   0.08250  -0.0401   0.0626   1.0000
  17.500   1.5701   0.09332   0.08800  -0.0421   0.0616   1.0000
  17.750   1.5583   0.09894   0.09376  -0.0444   0.0607   1.0000
  18.000   1.5459   0.10478   0.09973  -0.0470   0.0598   1.0000
  18.250   1.5344   0.11053   0.10557  -0.0496   0.0590   1.0000
  18.500   1.5254   0.11578   0.11087  -0.0520   0.0581   1.0000
  18.750   1.5094   0.12270   0.11797  -0.0556   0.0573   1.0000
  19.000   1.4885   0.13082   0.12630  -0.0601   0.0565   1.0000
  19.250   1.4649   0.13975   0.13544  -0.0654   0.0556   1.0000
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