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Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il)
Reynolds number: 100,000
Max Cl/Cd: 56.07 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-apex16-il-100000.txt
Download as CSV file: xf-apex16-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4835   0.10083   0.09630  -0.0457   1.0000   0.0785
  -8.750  -0.5077   0.09853   0.09406  -0.0447   1.0000   0.0786
  -8.500  -0.5330   0.09666   0.09223  -0.0425   1.0000   0.0786
  -8.250  -0.5544   0.09450   0.09006  -0.0408   1.0000   0.0786
  -8.000  -0.5798   0.09277   0.08825  -0.0390   1.0000   0.0788
  -7.750  -0.5994   0.09104   0.08638  -0.0372   1.0000   0.0791
  -7.500  -0.5655   0.08316   0.07888  -0.0357   1.0000   0.0833
  -7.250  -0.5732   0.08037   0.07609  -0.0341   1.0000   0.0853
  -7.000  -0.5834   0.07743   0.07310  -0.0329   1.0000   0.0873
  -6.750  -0.5928   0.07451   0.07007  -0.0320   1.0000   0.0899
  -6.500  -0.6096   0.07444   0.06942  -0.0312   1.0000   0.0937
  -6.250  -0.6081   0.06886   0.06384  -0.0308   1.0000   0.0957
  -6.000  -0.5993   0.06458   0.05971  -0.0297   1.0000   0.0986
  -5.750  -0.5931   0.06177   0.05679  -0.0289   1.0000   0.1036
  -5.500  -0.5891   0.05962   0.05413  -0.0285   1.0000   0.1109
  -5.250  -0.5782   0.05563   0.05025  -0.0278   1.0000   0.1156
  -5.000  -0.5684   0.05337   0.04758  -0.0275   1.0000   0.1264
  -4.750  -0.5566   0.05146   0.04533  -0.0270   1.0000   0.1399
  -4.500  -0.5431   0.04760   0.04159  -0.0265   1.0000   0.1497
  -4.250  -0.5204   0.04378   0.03762  -0.0288   0.9965   0.1753
  -4.000  -0.4928   0.04082   0.03422  -0.0317   0.9911   0.2125
  -3.750  -0.4632   0.03766   0.03090  -0.0339   0.9860   0.2408
  -3.500  -0.4325   0.03457   0.02785  -0.0355   0.9809   0.2593
  -3.250  -0.3974   0.03284   0.02574  -0.0370   0.9753   0.2655
  -3.000  -0.3522   0.03157   0.02391  -0.0393   0.9706   0.2481
  -2.750  -0.3014   0.03444   0.02577  -0.0385   0.9623   0.1554
  -2.500  -0.2483   0.03476   0.02547  -0.0389   0.9575   0.0933
  -2.250  -0.2233   0.03287   0.02353  -0.0385   0.9509   0.0894
  -2.000  -0.1869   0.03180   0.02231  -0.0399   0.9457   0.0867
  -1.750  -0.1539   0.03108   0.02135  -0.0402   0.9397   0.0813
  -1.500  -0.1231   0.03058   0.02076  -0.0405   0.9333   0.0798
  -1.250  -0.0841   0.02975   0.02001  -0.0425   0.9292   0.0802
  -1.000  -0.0653   0.02900   0.01940  -0.0412   0.9212   0.0826
  -0.750  -0.0304   0.02868   0.01910  -0.0428   0.9159   0.0901
  -0.500  -0.0076   0.02846   0.01876  -0.0422   0.9080   0.0944
  -0.250   0.0271   0.02808   0.01825  -0.0438   0.9022   0.1072
   0.000   0.0525   0.02761   0.01785  -0.0437   0.8949   0.1518
   0.250   0.0627   0.02607   0.01865  -0.0391   0.8889   0.7359
   0.500   0.0752   0.02627   0.01911  -0.0348   0.8812   0.8166
   0.750   0.0959   0.02617   0.01934  -0.0311   0.8746   0.9225
   1.000   0.1798   0.02654   0.01957  -0.0426   0.8718   0.9656
   1.250   0.2161   0.02674   0.01963  -0.0464   0.8623   1.0000
   1.500   0.2599   0.02684   0.01955  -0.0504   0.8572   1.0000
   1.750   0.2782   0.02711   0.01970  -0.0499   0.8465   1.0000
   2.000   0.3131   0.02732   0.01980  -0.0519   0.8394   1.0000
   2.250   0.3437   0.02753   0.01993  -0.0530   0.8310   1.0000
   2.500   0.3703   0.02783   0.02016  -0.0534   0.8220   1.0000
   2.750   0.4098   0.02786   0.02015  -0.0557   0.8155   1.0000
   3.000   0.4326   0.02819   0.02046  -0.0553   0.8052   1.0000
   3.250   0.4773   0.02801   0.02028  -0.0581   0.8001   1.0000
   3.500   0.4977   0.02837   0.02063  -0.0573   0.7888   1.0000
   3.750   0.5473   0.02790   0.02022  -0.0606   0.7846   1.0000
   4.000   0.5673   0.02820   0.02054  -0.0595   0.7727   1.0000
   4.250   0.6175   0.02751   0.01993  -0.0627   0.7687   1.0000
   4.500   0.6409   0.02759   0.02009  -0.0619   0.7570   1.0000
   4.750   0.7008   0.02622   0.01885  -0.0660   0.7545   1.0000
   5.000   0.7250   0.02607   0.01879  -0.0650   0.7420   1.0000
   5.250   0.7583   0.02544   0.01830  -0.0651   0.7304   1.0000
   5.500   0.8460   0.02252   0.01560  -0.0728   0.7253   1.0000
   5.750   0.8839   0.02160   0.01485  -0.0734   0.7113   1.0000
   6.000   0.9221   0.02080   0.01419  -0.0742   0.6967   1.0000
   6.250   0.9555   0.02020   0.01373  -0.0742   0.6798   1.0000
   6.500   0.9793   0.01988   0.01356  -0.0727   0.6593   1.0000
   6.750   1.0102   0.01918   0.01293  -0.0719   0.6326   1.0000
   7.000   1.0335   0.01858   0.01225  -0.0696   0.5922   1.0000
   7.250   1.0417   0.01858   0.01213  -0.0651   0.5445   1.0000
   7.500   1.0472   0.01886   0.01228  -0.0604   0.4956   1.0000
   7.750   1.0522   0.01937   0.01255  -0.0559   0.4451   1.0000
   8.000   1.0535   0.02016   0.01309  -0.0512   0.3905   1.0000
   8.250   1.0511   0.02125   0.01384  -0.0461   0.3306   1.0000
   8.500   1.0445   0.02271   0.01487  -0.0409   0.2628   1.0000
   8.750   1.0330   0.02474   0.01632  -0.0355   0.1868   1.0000
   9.000   1.0199   0.02735   0.01828  -0.0303   0.1272   1.0000
   9.250   1.0176   0.02951   0.02018  -0.0265   0.1011   1.0000
   9.500   1.0231   0.03128   0.02185  -0.0238   0.0879   1.0000
   9.750   1.0344   0.03286   0.02344  -0.0219   0.0786   1.0000
  10.000   1.0528   0.03467   0.02514  -0.0208   0.0722   1.0000
  10.250   1.0774   0.03625   0.02683  -0.0202   0.0665   1.0000
  10.500   1.1138   0.03859   0.02908  -0.0215   0.0606   1.0000
  10.750   1.1495   0.04103   0.03186  -0.0224   0.0572   1.0000
  11.000   1.1742   0.04337   0.03439  -0.0223   0.0540   1.0000
  11.250   1.2198   0.04872   0.03986  -0.0260   0.0505   1.0000
  11.500   1.2262   0.05160   0.04315  -0.0234   0.0501   1.0000
  11.750   1.2284   0.05486   0.04681  -0.0206   0.0500   1.0000
  12.000   1.2243   0.05801   0.05031  -0.0172   0.0499   1.0000
  12.250   1.2165   0.06123   0.05386  -0.0138   0.0499   1.0000
  12.500   1.2038   0.06436   0.05730  -0.0103   0.0498   1.0000
  12.750   1.1876   0.06755   0.06079  -0.0071   0.0496   1.0000
  13.000   1.1698   0.07109   0.06461  -0.0044   0.0496   1.0000
  13.250   1.1530   0.07524   0.06899  -0.0025   0.0498   1.0000
  13.500   1.1330   0.07940   0.07338  -0.0011   0.0499   1.0000
  13.750   1.1122   0.08416   0.07835  -0.0005   0.0500   1.0000
  14.000   1.1010   0.09011   0.08446  -0.0007   0.0506   1.0000
  14.250   1.0769   0.09423   0.08880  -0.0011   0.0509   1.0000
  14.500   0.9676   0.11017   0.10534  -0.0111   0.0574   1.0000
  14.750   0.9365   0.12067   0.11591  -0.0174   0.0590   1.0000
  15.000   0.9219   0.12909   0.12434  -0.0217   0.0606   1.0000
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