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Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il)
Reynolds number: 50,000
Max Cl/Cd: 34.02 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-apex16-il-50000.txt
Download as CSV file: xf-apex16-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4059   0.13410   0.12693  -0.0396   1.0000   0.1807
 -11.000  -0.3967   0.13031   0.12318  -0.0383   1.0000   0.1891
 -10.750  -0.4162   0.12924   0.12223  -0.0390   1.0000   0.1963
 -10.500  -0.4049   0.12555   0.11857  -0.0372   1.0000   0.2094
 -10.250  -0.4015   0.12268   0.11574  -0.0357   1.0000   0.2230
 -10.000  -0.4045   0.12044   0.11356  -0.0343   1.0000   0.2383
  -9.750  -0.3944   0.11776   0.11091  -0.0316   1.0000   0.2621
  -9.500  -0.3890   0.11581   0.10901  -0.0289   1.0000   0.2900
  -9.250  -0.3850   0.11418   0.10744  -0.0260   1.0000   0.3209
  -9.000  -0.3819   0.11257   0.10588  -0.0230   1.0000   0.3512
  -8.750  -0.3748   0.11056   0.10392  -0.0201   1.0000   0.3805
  -8.500  -0.3648   0.10818   0.10157  -0.0174   1.0000   0.4092
  -8.250  -0.3554   0.10582   0.09923  -0.0148   1.0000   0.4380
  -8.000  -0.3464   0.10342   0.09687  -0.0123   1.0000   0.4666
  -7.750  -0.3384   0.10108   0.09457  -0.0097   1.0000   0.4969
  -7.500  -0.3297   0.09872   0.09226  -0.0072   1.0000   0.5269
  -7.250  -0.3213   0.09637   0.08995  -0.0048   1.0000   0.5582
  -7.000  -0.3142   0.09378   0.08741  -0.0027   1.0000   0.5838
  -6.750  -0.3099   0.09144   0.08512  -0.0006   1.0000   0.6034
  -6.500  -0.3114   0.08924   0.08296   0.0015   1.0000   0.6138
  -6.250  -0.3150   0.08705   0.08084   0.0033   1.0000   0.6165
  -6.000  -0.3227   0.08516   0.07902   0.0057   1.0000   0.6185
  -4.750  -0.4816   0.07652   0.07112   0.0220   1.0000   0.5203
  -4.250  -0.5501   0.04753   0.04094  -0.0218   1.0000   0.3080
  -4.000  -0.5120   0.04194   0.03399  -0.0278   1.0000   0.2488
  -3.750  -0.4784   0.04093   0.03185  -0.0283   1.0000   0.2099
  -3.500  -0.4509   0.03984   0.03025  -0.0274   1.0000   0.1865
  -3.250  -0.4252   0.03898   0.02893  -0.0264   1.0000   0.1718
  -3.000  -0.4009   0.03799   0.02760  -0.0252   1.0000   0.1621
  -2.750  -0.3766   0.03758   0.02673  -0.0240   1.0000   0.1512
  -2.500  -0.3533   0.03638   0.02530  -0.0229   1.0000   0.1431
  -2.250  -0.3302   0.03596   0.02454  -0.0215   1.0000   0.1369
  -2.000  -0.3081   0.03486   0.02340  -0.0204   1.0000   0.1335
  -1.750  -0.2861   0.03411   0.02257  -0.0192   1.0000   0.1308
  -1.500  -0.2651   0.03348   0.02190  -0.0179   1.0000   0.1323
  -1.250  -0.2446   0.03301   0.02137  -0.0165   1.0000   0.1349
  -1.000  -0.2241   0.03266   0.02097  -0.0152   1.0000   0.1367
  -0.750  -0.2048   0.03239   0.02062  -0.0138   1.0000   0.1383
  -0.500  -0.1849   0.03194   0.02015  -0.0129   1.0000   0.1420
  -0.250  -0.1643   0.03167   0.01978  -0.0124   1.0000   0.1503
   0.000  -0.1422   0.03138   0.01936  -0.0123   1.0000   0.1646
   0.250  -0.1174   0.03097   0.01894  -0.0127   1.0000   0.1913
   0.500  -0.1009   0.02969   0.02010  -0.0100   1.0000   0.6775
   0.750  -0.0904   0.02888   0.02024  -0.0038   1.0000   1.0000
   1.000  -0.0693   0.02941   0.02028  -0.0044   1.0000   1.0000
   1.250  -0.0485   0.03002   0.02053  -0.0050   1.0000   1.0000
   1.500  -0.0284   0.03069   0.02092  -0.0055   1.0000   1.0000
   1.750  -0.0088   0.03142   0.02141  -0.0059   1.0000   1.0000
   2.000   0.0103   0.03220   0.02197  -0.0063   1.0000   1.0000
   2.250   0.0290   0.03303   0.02262  -0.0065   1.0000   1.0000
   2.500   0.0473   0.03390   0.02335  -0.0068   1.0000   1.0000
   2.750   0.0651   0.03482   0.02415  -0.0070   1.0000   1.0000
   3.000   0.0826   0.03579   0.02501  -0.0072   1.0000   1.0000
   3.250   0.1785   0.03976   0.02880  -0.0218   0.9564   1.0000
   3.500   0.2141   0.04101   0.03000  -0.0250   0.9373   1.0000
   3.750   0.2521   0.04240   0.03136  -0.0284   0.9192   1.0000
   4.000   0.2907   0.04379   0.03273  -0.0318   0.9022   1.0000
   4.250   0.3307   0.04519   0.03415  -0.0351   0.8855   1.0000
   4.500   0.3568   0.04615   0.03514  -0.0363   0.8686   1.0000
   4.750   0.3853   0.04721   0.03623  -0.0377   0.8518   1.0000
   5.000   0.4155   0.04829   0.03739  -0.0393   0.8349   1.0000
   5.250   0.4483   0.04935   0.03853  -0.0411   0.8179   1.0000
   5.500   0.4847   0.05036   0.03964  -0.0432   0.8007   1.0000
   5.750   0.5237   0.05125   0.04068  -0.0454   0.7837   1.0000
   6.000   0.5420   0.05217   0.04171  -0.0450   0.7647   1.0000
   6.250   0.5714   0.05295   0.04263  -0.0457   0.7459   1.0000
   6.500   0.6128   0.05331   0.04318  -0.0474   0.7270   1.0000
   6.750   0.6409   0.05379   0.04386  -0.0475   0.7064   1.0000
   7.000   0.6776   0.05371   0.04400  -0.0480   0.6850   1.0000
   7.250   0.7183   0.05309   0.04365  -0.0482   0.6627   1.0000
   7.500   0.7684   0.05142   0.04234  -0.0485   0.6398   1.0000
   7.750   0.8085   0.04991   0.04116  -0.0476   0.6156   1.0000
   8.000   0.9184   0.04184   0.03386  -0.0491   0.5942   1.0000
   8.250   1.0359   0.03201   0.02466  -0.0505   0.5323   1.0000
   8.500   1.0406   0.03059   0.02304  -0.0436   0.4711   1.0000
   8.750   1.0397   0.03076   0.02283  -0.0375   0.4049   1.0000
   9.000   1.0321   0.03209   0.02360  -0.0316   0.3361   1.0000
   9.250   1.0199   0.03433   0.02511  -0.0260   0.2687   1.0000
   9.500   1.0121   0.03728   0.02736  -0.0216   0.2043   1.0000
   9.750   1.0446   0.04048   0.02993  -0.0214   0.1514   1.0000
  10.000   1.1104   0.04426   0.03361  -0.0260   0.1236   1.0000
  10.250   1.1560   0.04815   0.03766  -0.0288   0.1109   1.0000
  10.500   1.1723   0.05126   0.04128  -0.0272   0.1056   1.0000
  10.750   1.1973   0.05518   0.04551  -0.0272   0.1017   1.0000
  11.000   1.2136   0.05961   0.05015  -0.0265   0.0985   1.0000
  11.250   1.2045   0.06258   0.05361  -0.0222   0.0974   1.0000
  11.500   1.1924   0.06565   0.05706  -0.0179   0.0967   1.0000
  11.750   1.1770   0.06889   0.06063  -0.0138   0.0962   1.0000
  12.000   1.1604   0.07245   0.06448  -0.0103   0.0963   1.0000
  12.250   1.1420   0.07626   0.06855  -0.0074   0.0966   1.0000
  12.500   1.1220   0.08043   0.07295  -0.0051   0.0971   1.0000
  12.750   1.1025   0.08500   0.07772  -0.0037   0.0977   1.0000
  13.000   1.0832   0.09000   0.08288  -0.0030   0.0983   1.0000
  13.250   1.0700   0.09556   0.08856  -0.0030   0.0990   1.0000
  13.500   0.9555   0.10860   0.10192  -0.0106   0.1099   1.0000
  13.750   0.9385   0.11638   0.10972  -0.0139   0.1115   1.0000
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