Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

ARA-D 20% AIRFOIL (arad20-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: ARA-D 20% AIRFOIL (arad20-il)
Reynolds number: 200,000
Max Cl/Cd: 51.96 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-arad20-il-200000.txt
Download as CSV file: xf-arad20-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ARA-D 20% 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.7903   0.09603   0.09157  -0.0240   1.0000   0.0436
 -14.750  -0.8303   0.08514   0.08047  -0.0315   1.0000   0.0434
 -14.500  -0.8680   0.07568   0.07076  -0.0378   1.0000   0.0431
 -14.250  -0.9022   0.06782   0.06262  -0.0425   1.0000   0.0430
 -14.000  -0.9319   0.06145   0.05597  -0.0454   1.0000   0.0430
 -13.750  -0.9577   0.05633   0.05055  -0.0464   1.0000   0.0431
 -13.500  -0.9807   0.05221   0.04612  -0.0457   1.0000   0.0432
 -13.250  -1.0022   0.04898   0.04260  -0.0431   1.0000   0.0434
 -13.000  -1.0182   0.04625   0.03951  -0.0399   1.0000   0.0436
 -12.750  -1.0045   0.04419   0.03746  -0.0390   1.0000   0.0442
 -12.500  -0.9906   0.04262   0.03589  -0.0380   1.0000   0.0448
 -12.250  -0.9764   0.04111   0.03434  -0.0369   1.0000   0.0455
 -12.000  -0.9645   0.03936   0.03244  -0.0357   1.0000   0.0464
 -11.750  -0.9532   0.03743   0.03026  -0.0343   1.0000   0.0474
 -11.500  -0.9420   0.03551   0.02796  -0.0327   1.0000   0.0484
 -11.250  -0.9184   0.03418   0.02677  -0.0325   1.0000   0.0495
 -11.000  -0.8967   0.03314   0.02573  -0.0319   1.0000   0.0508
 -10.750  -0.8768   0.03190   0.02432  -0.0311   1.0000   0.0526
 -10.500  -0.8547   0.03060   0.02297  -0.0306   1.0000   0.0543
 -10.250  -0.8308   0.02970   0.02213  -0.0303   1.0000   0.0560
 -10.000  -0.8076   0.02865   0.02094  -0.0298   1.0000   0.0582
  -9.750  -0.7829   0.02753   0.01990  -0.0295   1.0000   0.0601
  -9.500  -0.7577   0.02668   0.01910  -0.0293   1.0000   0.0624
  -9.250  -0.7208   0.02566   0.01801  -0.0314   0.9324   0.0656
  -9.000  -0.6983   0.02535   0.01743  -0.0296   0.8030   0.0683
  -8.750  -0.6775   0.02493   0.01656  -0.0278   0.7335   0.0714
  -8.500  -0.6532   0.02447   0.01598  -0.0271   0.6956   0.0745
  -8.250  -0.6274   0.02394   0.01521  -0.0267   0.6707   0.0784
  -8.000  -0.6012   0.02347   0.01468  -0.0264   0.6521   0.0822
  -7.750  -0.5744   0.02291   0.01401  -0.0262   0.6366   0.0866
  -7.500  -0.5470   0.02250   0.01351  -0.0261   0.6242   0.0917
  -7.250  -0.5198   0.02194   0.01295  -0.0260   0.6131   0.0967
  -7.000  -0.4921   0.02149   0.01241  -0.0259   0.6034   0.1030
  -6.750  -0.4638   0.02106   0.01197  -0.0260   0.5938   0.1101
  -6.500  -0.4361   0.02061   0.01151  -0.0260   0.5857   0.1181
  -6.250  -0.4076   0.02014   0.01108  -0.0262   0.5781   0.1279
  -6.000  -0.3789   0.01969   0.01067  -0.0263   0.5703   0.1399
  -5.750  -0.3503   0.01932   0.01029  -0.0265   0.5633   0.1546
  -5.500  -0.3211   0.01897   0.00999  -0.0267   0.5569   0.1727
  -5.250  -0.2919   0.01851   0.00969  -0.0271   0.5502   0.1944
  -5.000  -0.2625   0.01817   0.00941  -0.0274   0.5437   0.2214
  -4.750  -0.2334   0.01793   0.00925  -0.0277   0.5377   0.2532
  -4.500  -0.2034   0.01757   0.00909  -0.0282   0.5320   0.2898
  -4.250  -0.1735   0.01728   0.00897  -0.0286   0.5258   0.3297
  -4.000  -0.1437   0.01707   0.00887  -0.0290   0.5200   0.3710
  -3.750  -0.1140   0.01705   0.00890  -0.0292   0.5145   0.4124
  -3.500  -0.0837   0.01685   0.00890  -0.0296   0.5092   0.4533
  -3.250  -0.0535   0.01673   0.00891  -0.0299   0.5033   0.4923
  -3.000  -0.0235   0.01668   0.00892  -0.0300   0.4978   0.5292
  -2.750   0.0061   0.01677   0.00903  -0.0301   0.4928   0.5621
  -2.500   0.0363   0.01677   0.00914  -0.0303   0.4876   0.5937
  -2.250   0.0665   0.01676   0.00920  -0.0304   0.4818   0.6232
  -2.000   0.0960   0.01677   0.00926  -0.0303   0.4765   0.6500
  -1.750   0.1252   0.01688   0.00935  -0.0302   0.4719   0.6758
  -1.500   0.1544   0.01701   0.00954  -0.0300   0.4668   0.7006
  -1.250   0.1835   0.01704   0.00965  -0.0299   0.4612   0.7242
  -1.000   0.2123   0.01709   0.00972  -0.0296   0.4559   0.7462
  -0.750   0.2407   0.01719   0.00977  -0.0292   0.4515   0.7674
  -0.500   0.2689   0.01740   0.00996  -0.0288   0.4467   0.7879
  -0.250   0.2971   0.01744   0.01007  -0.0285   0.4412   0.8079
   0.000   0.3239   0.01748   0.01013  -0.0277   0.4360   0.8264
   0.250   0.3499   0.01753   0.01014  -0.0267   0.4317   0.8442
   0.500   0.3753   0.01774   0.01026  -0.0257   0.4274   0.8620
   0.750   0.4003   0.01772   0.01035  -0.0246   0.4221   0.8800
   1.000   0.4246   0.01770   0.01034  -0.0233   0.4170   0.8985
   1.250   0.4483   0.01765   0.01024  -0.0219   0.4127   0.9175
   1.500   0.4726   0.01765   0.01014  -0.0206   0.4087   0.9372
   1.750   0.5016   0.01765   0.01018  -0.0205   0.4035   0.9567
   2.000   0.5385   0.01764   0.01017  -0.0222   0.3977   0.9731
   2.250   0.5812   0.01769   0.01012  -0.0252   0.3925   0.9854
   2.500   0.6254   0.01795   0.01022  -0.0286   0.3877   0.9954
   2.750   0.6565   0.01801   0.01035  -0.0299   0.3822   1.0000
   3.000   0.6810   0.01808   0.01037  -0.0298   0.3773   1.0000
   3.250   0.7106   0.01820   0.01037  -0.0305   0.3730   1.0000
   3.500   0.7411   0.01853   0.01056  -0.0314   0.3688   1.0000
   3.750   0.7714   0.01874   0.01085  -0.0322   0.3634   1.0000
   4.000   0.8020   0.01892   0.01097  -0.0330   0.3584   1.0000
   4.250   0.8328   0.01910   0.01104  -0.0338   0.3542   1.0000
   4.500   0.8631   0.01947   0.01133  -0.0345   0.3500   1.0000
   4.750   0.8926   0.01974   0.01167  -0.0351   0.3449   1.0000
   5.000   0.9226   0.01995   0.01185  -0.0357   0.3402   1.0000
   5.250   0.9526   0.02018   0.01196  -0.0363   0.3362   1.0000
   5.500   0.9819   0.02061   0.01234  -0.0369   0.3320   1.0000
   5.750   1.0105   0.02094   0.01275  -0.0373   0.3272   1.0000
   6.000   1.0396   0.02120   0.01298  -0.0378   0.3228   1.0000
   6.250   1.0689   0.02147   0.01315  -0.0383   0.3190   1.0000
   6.500   1.0973   0.02196   0.01362  -0.0387   0.3149   1.0000
   6.750   1.1245   0.02236   0.01411  -0.0390   0.3105   1.0000
   7.000   1.1526   0.02269   0.01443  -0.0393   0.3064   1.0000
   7.250   1.1811   0.02300   0.01466  -0.0397   0.3027   1.0000
   7.500   1.2089   0.02355   0.01514  -0.0401   0.2990   1.0000
   7.750   1.2343   0.02403   0.01576  -0.0402   0.2949   1.0000
   8.000   1.2607   0.02444   0.01621  -0.0403   0.2910   1.0000
   8.250   1.2881   0.02479   0.01650  -0.0406   0.2874   1.0000
   8.500   1.3164   0.02535   0.01691  -0.0410   0.2840   1.0000
   8.750   1.3391   0.02595   0.01769  -0.0407   0.2804   1.0000
   9.000   1.3630   0.02649   0.01832  -0.0406   0.2766   1.0000
   9.250   1.3882   0.02693   0.01876  -0.0406   0.2732   1.0000
   9.500   1.4147   0.02736   0.01911  -0.0407   0.2701   1.0000
   9.750   1.4392   0.02810   0.01984  -0.0408   0.2668   1.0000
  10.000   1.4582   0.02883   0.02075  -0.0400   0.2634   1.0000
  10.250   1.4793   0.02945   0.02144  -0.0396   0.2600   1.0000
  10.500   1.5025   0.02994   0.02192  -0.0393   0.2569   1.0000
  10.750   1.5281   0.03047   0.02235  -0.0394   0.2541   1.0000
  11.000   1.5472   0.03140   0.02335  -0.0388   0.2511   1.0000
  11.250   1.5595   0.03235   0.02448  -0.0373   0.2481   1.0000
  11.500   1.5745   0.03315   0.02537  -0.0361   0.2450   1.0000
  11.750   1.5929   0.03378   0.02600  -0.0354   0.2422   1.0000
  12.000   1.6162   0.03433   0.02649  -0.0352   0.2396   1.0000
  12.250   1.6335   0.03538   0.02755  -0.0345   0.2370   1.0000
  12.500   1.6291   0.03682   0.02922  -0.0311   0.2345   1.0000
  12.750   1.6239   0.03834   0.03089  -0.0277   0.2320   1.0000
  13.000   1.6273   0.03969   0.03233  -0.0258   0.2295   1.0000
  13.250   1.6405   0.04065   0.03328  -0.0249   0.2270   1.0000
  13.500   1.6664   0.04113   0.03366  -0.0251   0.2246   1.0000
  13.750   1.6643   0.04325   0.03590  -0.0234   0.2223   1.0000
  14.000   1.6400   0.04694   0.03988  -0.0215   0.2201   1.0000
  14.250   1.6232   0.05067   0.04380  -0.0209   0.2175   1.0000
  14.500   1.6203   0.05343   0.04665  -0.0209   0.2150   1.0000
  14.750   1.6356   0.05449   0.04769  -0.0208   0.2127   1.0000
  15.000   1.6712   0.05379   0.04683  -0.0205   0.2105   1.0000
  15.250   1.6377   0.05976   0.05307  -0.0210   0.2082   1.0000
  15.500   1.3077   0.10685   0.10125  -0.0367   0.1977   1.0000
  15.750   1.3950   0.09691   0.09118  -0.0328   0.1987   1.0000
  16.000   1.4902   0.08654   0.08060  -0.0287   0.1988   1.0000
  16.250   1.5593   0.08040   0.07427  -0.0261   0.1978   1.0000
  16.500   0.9209   0.20433   0.19931  -0.0841   0.1578   1.0000
  16.750   0.9311   0.20769   0.20270  -0.0856   0.1588   1.0000
<< Back to ARA-D 20% AIRFOIL (arad20-il)

Polar data table (+)

Polar graphs


<< Back to ARA-D 20% AIRFOIL (arad20-il)