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Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il)
Reynolds number: 200,000
Max Cl/Cd: 76.81 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-apex16-il-200000-n5.txt
Download as CSV file: xf-apex16-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Apex 16 (normalized using XFOIL date021206)     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3835   0.09055   0.08695  -0.0682   0.9878   0.0279
  -9.250  -0.3831   0.08551   0.08185  -0.0739   0.9836   0.0279
  -8.750  -0.3903   0.07724   0.07341  -0.0818   0.9711   0.0279
  -7.250  -0.3628   0.05100   0.04618  -0.0896   0.9379   0.0293
  -7.000  -0.3464   0.04784   0.04298  -0.0908   0.9346   0.0305
  -6.750  -0.3253   0.04503   0.04003  -0.0923   0.9323   0.0319
  -6.500  -0.3084   0.04274   0.03738  -0.0899   0.9256   0.0267
  -6.250  -0.2924   0.03902   0.03342  -0.0902   0.9216   0.0250
  -6.000  -0.2681   0.03578   0.02988  -0.0909   0.9192   0.0238
  -5.750  -0.2518   0.03334   0.02716  -0.0893   0.9132   0.0229
  -5.500  -0.2291   0.03075   0.02428  -0.0888   0.9086   0.0224
  -5.250  -0.2001   0.02821   0.02142  -0.0892   0.9060   0.0222
  -5.000  -0.1690   0.02598   0.01890  -0.0900   0.9040   0.0223
  -4.750  -0.1522   0.02466   0.01740  -0.0879   0.8970   0.0227
  -4.500  -0.1240   0.02342   0.01595  -0.0881   0.8936   0.0243
  -4.250  -0.0929   0.02189   0.01423  -0.0887   0.8913   0.0247
  -4.000  -0.0603   0.02042   0.01258  -0.0896   0.8895   0.0247
  -3.750  -0.0413   0.01948   0.01155  -0.0878   0.8831   0.0248
  -3.500  -0.0140   0.01846   0.01044  -0.0877   0.8793   0.0252
  -3.250   0.0160   0.01751   0.00940  -0.0882   0.8766   0.0256
  -3.000   0.0470   0.01664   0.00848  -0.0890   0.8744   0.0263
  -2.750   0.0630   0.01617   0.00797  -0.0867   0.8671   0.0270
  -2.500   0.0910   0.01568   0.00743  -0.0869   0.8633   0.0279
  -2.250   0.1189   0.01477   0.00647  -0.0873   0.8604   0.0308
  -2.000   0.1377   0.01439   0.00605  -0.0857   0.8539   0.0319
  -1.750   0.1647   0.01399   0.00557  -0.0857   0.8495   0.0336
  -1.500   0.1963   0.01363   0.00508  -0.0866   0.8464   0.0360
  -1.250   0.2193   0.01346   0.00482  -0.0857   0.8403   0.0395
  -1.000   0.2469   0.01320   0.00454  -0.0858   0.8354   0.0503
  -0.750   0.2693   0.01171   0.00420  -0.0857   0.8316   0.4322
  -0.500   0.2873   0.01139   0.00430  -0.0838   0.8246   0.5419
  -0.250   0.3136   0.01118   0.00433  -0.0834   0.8196   0.6103
   0.000   0.3416   0.01108   0.00433  -0.0833   0.8149   0.6505
   0.250   0.3655   0.01106   0.00434  -0.0825   0.8079   0.6686
   0.500   0.3974   0.01098   0.00422  -0.0833   0.8031   0.6810
   0.750   0.4212   0.01098   0.00424  -0.0825   0.7955   0.6930
   1.000   0.4509   0.01092   0.00418  -0.0829   0.7895   0.7057
   1.250   0.4759   0.01091   0.00420  -0.0823   0.7818   0.7185
   1.500   0.5047   0.01086   0.00416  -0.0825   0.7748   0.7315
   1.750   0.5290   0.01087   0.00421  -0.0817   0.7664   0.7447
   2.000   0.5579   0.01083   0.00420  -0.0819   0.7592   0.7585
   2.250   0.5808   0.01085   0.00429  -0.0809   0.7498   0.7729
   2.500   0.6081   0.01084   0.00431  -0.0807   0.7415   0.7879
   2.750   0.6325   0.01086   0.00440  -0.0799   0.7320   0.8039
   3.000   0.6568   0.01088   0.00449  -0.0792   0.7221   0.8209
   3.250   0.6831   0.01089   0.00453  -0.0788   0.7124   0.8383
   3.500   0.7079   0.01091   0.00460  -0.0782   0.7013   0.8563
   3.750   0.7324   0.01094   0.00470  -0.0775   0.6889   0.8754
   4.000   0.7598   0.01095   0.00478  -0.0773   0.6743   0.8958
   4.250   0.7916   0.01100   0.00483  -0.0781   0.6511   0.9202
   4.500   0.8319   0.01112   0.00494  -0.0809   0.6235   0.9534
   4.750   0.8640   0.01131   0.00510  -0.0821   0.6025   1.0000
   5.250   0.9033   0.01176   0.00546  -0.0791   0.5621   1.0000
   5.500   0.9194   0.01206   0.00566  -0.0768   0.5316   1.0000
   5.750   0.9312   0.01247   0.00591  -0.0737   0.4897   1.0000
   6.000   0.9377   0.01303   0.00620  -0.0697   0.4387   1.0000
   6.250   0.9424   0.01364   0.00655  -0.0654   0.3923   1.0000
   6.500   0.9464   0.01436   0.00701  -0.0611   0.3426   1.0000
   6.750   0.9517   0.01514   0.00753  -0.0573   0.2935   1.0000
   7.000   0.9572   0.01603   0.00814  -0.0537   0.2424   1.0000
   7.250   0.9646   0.01693   0.00882  -0.0505   0.1962   1.0000
   7.500   0.9750   0.01775   0.00947  -0.0480   0.1630   1.0000
   8.000   0.9958   0.01951   0.01093  -0.0432   0.1020   1.0000
   8.250   1.0041   0.02058   0.01179  -0.0406   0.0667   1.0000
   8.500   1.0126   0.02167   0.01273  -0.0381   0.0451   1.0000
   8.750   1.0243   0.02259   0.01365  -0.0360   0.0378   1.0000
   9.000   1.0349   0.02360   0.01471  -0.0338   0.0338   1.0000
   9.250   1.0477   0.02447   0.01568  -0.0320   0.0318   1.0000
   9.500   1.0596   0.02541   0.01672  -0.0302   0.0296   1.0000
   9.750   1.0698   0.02648   0.01786  -0.0282   0.0274   1.0000
  10.000   1.0767   0.02781   0.01925  -0.0260   0.0257   1.0000
  10.250   1.0846   0.02910   0.02065  -0.0240   0.0247   1.0000
  10.500   1.0939   0.03033   0.02200  -0.0222   0.0238   1.0000
  10.750   1.1030   0.03161   0.02338  -0.0205   0.0227   1.0000
  11.000   1.1118   0.03294   0.02484  -0.0188   0.0214   1.0000
  11.250   1.1200   0.03434   0.02631  -0.0173   0.0201   1.0000
  11.500   1.1253   0.03606   0.02809  -0.0156   0.0192   1.0000
  11.750   1.1280   0.03821   0.03031  -0.0137   0.0184   1.0000
  12.000   1.1374   0.03974   0.03197  -0.0124   0.0179   1.0000
  12.250   1.1466   0.04134   0.03372  -0.0112   0.0173   1.0000
  12.500   1.1547   0.04302   0.03554  -0.0101   0.0163   1.0000
  12.750   1.1617   0.04477   0.03742  -0.0090   0.0153   1.0000
  13.000   1.1677   0.04666   0.03942  -0.0080   0.0146   1.0000
  13.250   1.1728   0.04873   0.04160  -0.0070   0.0141   1.0000
  13.500   1.1768   0.05096   0.04393  -0.0061   0.0137   1.0000
  13.750   1.1801   0.05345   0.04653  -0.0052   0.0133   1.0000
  14.000   1.1814   0.05649   0.04972  -0.0043   0.0128   1.0000
  14.250   1.1822   0.05928   0.05277  -0.0037   0.0127   1.0000
  14.500   1.1803   0.06242   0.05615  -0.0032   0.0124   1.0000
  14.750   1.1758   0.06595   0.05994  -0.0030   0.0121   1.0000
  15.000   1.1699   0.06980   0.06402  -0.0031   0.0120   1.0000
  15.250   1.1618   0.07404   0.06849  -0.0035   0.0119   1.0000
  15.500   1.1513   0.07875   0.07344  -0.0045   0.0116   1.0000
  15.750   1.1385   0.08403   0.07896  -0.0060   0.0114   1.0000
  16.000   1.1255   0.08958   0.08473  -0.0080   0.0111   1.0000
  16.250   1.1091   0.09604   0.09142  -0.0107   0.0112   1.0000
  16.500   1.0926   0.10291   0.09850  -0.0140   0.0112   1.0000
  16.750   1.0762   0.11016   0.10594  -0.0180   0.0110   1.0000
  17.000   1.0558   0.11871   0.11471  -0.0229   0.0112   1.0000
  17.250   1.0343   0.12814   0.12433  -0.0287   0.0112   1.0000
  17.500   1.0087   0.13934   0.13570  -0.0356   0.0116   1.0000
  17.750   0.9819   0.15189   0.14835  -0.0434   0.0119   1.0000
  18.000   0.9410   0.17061   0.16716  -0.0540   0.0123   1.0000
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