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ARA-D 20% AIRFOIL (arad20-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: ARA-D 20% AIRFOIL (arad20-il)
Reynolds number: 100,000
Max Cl/Cd: 38.59 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-arad20-il-100000-n5.txt
Download as CSV file: xf-arad20-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.7445   0.09157   0.08544  -0.0245   1.0000   0.0431
 -14.000  -0.8050   0.07723   0.07066  -0.0347   1.0000   0.0429
 -13.750  -0.8391   0.06871   0.06181  -0.0400   1.0000   0.0430
 -13.500  -0.8638   0.06234   0.05511  -0.0432   1.0000   0.0433
 -13.250  -0.8836   0.05716   0.04960  -0.0448   1.0000   0.0437
 -13.000  -0.8825   0.05457   0.04698  -0.0449   1.0000   0.0441
 -12.750  -0.8823   0.05207   0.04441  -0.0446   1.0000   0.0446
 -12.500  -0.8829   0.04969   0.04193  -0.0439   1.0000   0.0452
 -12.250  -0.8848   0.04744   0.03957  -0.0426   1.0000   0.0460
 -12.000  -0.8876   0.04533   0.03729  -0.0405   1.0000   0.0469
 -11.750  -0.8865   0.04309   0.03475  -0.0387   1.0000   0.0482
 -11.500  -0.8746   0.04171   0.03339  -0.0375   1.0000   0.0492
 -11.250  -0.8614   0.04039   0.03205  -0.0365   1.0000   0.0504
 -11.000  -0.8478   0.03887   0.03040  -0.0354   1.0000   0.0520
 -10.750  -0.8326   0.03728   0.02864  -0.0344   1.0000   0.0537
 -10.500  -0.8142   0.03620   0.02761  -0.0336   1.0000   0.0551
 -10.250  -0.7954   0.03501   0.02636  -0.0329   1.0000   0.0571
 -10.000  -0.7758   0.03377   0.02503  -0.0322   1.0000   0.0593
  -9.750  -0.7548   0.03280   0.02413  -0.0317   1.0000   0.0613
  -9.500  -0.7271   0.03169   0.02286  -0.0324   0.9461   0.0644
  -9.250  -0.6966   0.03086   0.02196  -0.0332   0.8509   0.0672
  -9.000  -0.6760   0.03020   0.02095  -0.0316   0.7791   0.0703
  -8.750  -0.6557   0.02961   0.02016  -0.0302   0.7299   0.0730
  -8.500  -0.6331   0.02900   0.01928  -0.0292   0.6957   0.0768
  -8.250  -0.6097   0.02837   0.01854  -0.0286   0.6705   0.0802
  -8.000  -0.5849   0.02777   0.01772  -0.0281   0.6508   0.0848
  -7.750  -0.5601   0.02717   0.01708  -0.0277   0.6343   0.0891
  -7.500  -0.5343   0.02658   0.01638  -0.0274   0.6205   0.0943
  -7.250  -0.5084   0.02606   0.01574  -0.0271   0.6089   0.1004
  -7.000  -0.4820   0.02549   0.01517  -0.0270   0.5983   0.1067
  -6.750  -0.4555   0.02498   0.01460  -0.0269   0.5886   0.1142
  -6.500  -0.4285   0.02452   0.01407  -0.0267   0.5801   0.1230
  -6.250  -0.4009   0.02405   0.01359  -0.0268   0.5713   0.1334
  -6.000  -0.3734   0.02364   0.01314  -0.0267   0.5639   0.1452
  -5.750  -0.3456   0.02323   0.01273  -0.0268   0.5568   0.1591
  -5.500  -0.3173   0.02281   0.01237  -0.0270   0.5493   0.1753
  -5.250  -0.2891   0.02244   0.01203  -0.0271   0.5426   0.1948
  -5.000  -0.2608   0.02216   0.01173  -0.0272   0.5368   0.2181
  -4.750  -0.2319   0.02179   0.01151  -0.0275   0.5301   0.2448
  -4.250  -0.1744   0.02123   0.01111  -0.0279   0.5179   0.3101
  -4.000  -0.1456   0.02102   0.01098  -0.0281   0.5127   0.3462
  -3.750  -0.1162   0.02081   0.01092  -0.0284   0.5065   0.3836
  -3.250  -0.0582   0.02054   0.01082  -0.0285   0.4953   0.4580
  -3.000  -0.0293   0.02050   0.01082  -0.0285   0.4905   0.4933
  -2.750   0.0001   0.02044   0.01089  -0.0285   0.4845   0.5279
  -2.500   0.0291   0.02042   0.01094  -0.0284   0.4788   0.5602
  -2.250   0.0577   0.02043   0.01097  -0.0282   0.4738   0.5915
  -2.000   0.0865   0.02051   0.01100  -0.0280   0.4694   0.6212
  -1.750   0.1152   0.02055   0.01116  -0.0278   0.4636   0.6482
  -1.500   0.1434   0.02061   0.01126  -0.0274   0.4580   0.6737
  -1.250   0.1713   0.02068   0.01131  -0.0270   0.4531   0.6981
  -1.000   0.1990   0.02078   0.01135  -0.0264   0.4490   0.7212
  -0.750   0.2269   0.02089   0.01152  -0.0261   0.4435   0.7433
  -0.500   0.2545   0.02100   0.01164  -0.0256   0.4379   0.7647
  -0.250   0.2819   0.02109   0.01169  -0.0251   0.4330   0.7856
   0.000   0.3088   0.02117   0.01170  -0.0244   0.4290   0.8055
   0.250   0.3351   0.02129   0.01185  -0.0237   0.4240   0.8242
   0.500   0.3614   0.02140   0.01199  -0.0230   0.4184   0.8430
   0.750   0.3877   0.02146   0.01202  -0.0222   0.4136   0.8618
   1.000   0.4142   0.02150   0.01198  -0.0215   0.4095   0.8808
   1.250   0.4413   0.02160   0.01206  -0.0211   0.4049   0.9000
   1.500   0.4698   0.02172   0.01221  -0.0210   0.3992   0.9193
   1.750   0.5010   0.02179   0.01223  -0.0215   0.3941   0.9384
   2.000   0.5358   0.02185   0.01218  -0.0228   0.3899   0.9566
   2.250   0.5735   0.02205   0.01237  -0.0249   0.3845   0.9741
   2.750   0.6424   0.02237   0.01260  -0.0283   0.3739   1.0000
   3.000   0.6698   0.02252   0.01261  -0.0286   0.3703   1.0000
   3.250   0.6975   0.02288   0.01298  -0.0291   0.3650   1.0000
   3.500   0.7258   0.02320   0.01328  -0.0296   0.3598   1.0000
   3.750   0.7546   0.02344   0.01344  -0.0301   0.3555   1.0000
   4.000   0.7837   0.02366   0.01352  -0.0305   0.3519   1.0000
   4.250   0.8115   0.02413   0.01404  -0.0310   0.3466   1.0000
   4.500   0.8396   0.02451   0.01442  -0.0315   0.3416   1.0000
   4.750   0.8680   0.02479   0.01463  -0.0319   0.3375   1.0000
   5.000   0.8967   0.02505   0.01476  -0.0322   0.3341   1.0000
   5.250   0.9233   0.02562   0.01543  -0.0326   0.3290   1.0000
   5.500   0.9503   0.02607   0.01589  -0.0328   0.3243   1.0000
   5.750   0.9778   0.02641   0.01618  -0.0331   0.3203   1.0000
   6.000   1.0057   0.02672   0.01637  -0.0334   0.3171   1.0000
   6.250   1.0306   0.02739   0.01715  -0.0335   0.3124   1.0000
   6.500   1.0559   0.02795   0.01775  -0.0336   0.3078   1.0000
   6.750   1.0820   0.02837   0.01815  -0.0337   0.3040   1.0000
   7.000   1.1088   0.02873   0.01841  -0.0338   0.3009   1.0000
   7.250   1.1320   0.02946   0.01923  -0.0337   0.2968   1.0000
   7.500   1.1545   0.03020   0.02006  -0.0336   0.2925   1.0000
   7.750   1.1782   0.03076   0.02062  -0.0334   0.2888   1.0000
   8.000   1.2030   0.03120   0.02100  -0.0333   0.2856   1.0000
   8.250   1.2259   0.03184   0.02165  -0.0331   0.2824   1.0000
   8.500   1.2432   0.03288   0.02284  -0.0325   0.2783   1.0000
   8.750   1.2623   0.03370   0.02373  -0.0319   0.2746   1.0000
   9.000   1.2832   0.03432   0.02435  -0.0314   0.2715   1.0000
   9.250   1.3064   0.03482   0.02477  -0.0312   0.2688   1.0000
   9.500   1.3191   0.03601   0.02609  -0.0300   0.2654   1.0000
   9.750   1.3272   0.03738   0.02763  -0.0284   0.2619   1.0000
  10.000   1.3374   0.03853   0.02886  -0.0270   0.2587   1.0000
  10.250   1.3511   0.03942   0.02975  -0.0258   0.2559   1.0000
  10.500   1.3686   0.04005   0.03033  -0.0249   0.2535   1.0000
  10.750   1.3636   0.04203   0.03246  -0.0223   0.2508   1.0000
  11.000   1.3445   0.04541   0.03609  -0.0201   0.2476   1.0000
  11.250   1.3323   0.04882   0.03966  -0.0193   0.2443   1.0000
  11.500   1.3342   0.05118   0.04207  -0.0191   0.2415   1.0000
  11.750   1.3525   0.05196   0.04280  -0.0189   0.2392   1.0000
  12.000   1.3324   0.05692   0.04794  -0.0195   0.2361   1.0000
  12.250   1.1083   0.09051   0.08225  -0.0302   0.2220   1.0000
  12.500   1.1602   0.08615   0.07782  -0.0284   0.2226   1.0000
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