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Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il)
Reynolds number: 100,000
Max Cl/Cd: 54.44 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-apex16-il-100000-n5.txt
Download as CSV file: xf-apex16-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4362   0.10044   0.09570  -0.0433   1.0000   0.0526
  -9.000  -0.4495   0.09724   0.09257  -0.0435   1.0000   0.0529
  -8.750  -0.4718   0.09368   0.08910  -0.0447   1.0000   0.0533
  -8.500  -0.4814   0.08823   0.08358  -0.0525   0.9938   0.0536
  -8.250  -0.4943   0.08400   0.07913  -0.0590   0.9843   0.0541
  -8.000  -0.4972   0.08059   0.07537  -0.0630   0.9763   0.0545
  -7.500  -0.4718   0.07012   0.06508  -0.0648   0.9693   0.0570
  -7.250  -0.4616   0.06645   0.06130  -0.0662   0.9643   0.0587
  -7.000  -0.4521   0.06298   0.05764  -0.0675   0.9584   0.0605
  -6.750  -0.4479   0.06235   0.05622  -0.0677   0.9493   0.0659
  -6.500  -0.4305   0.05753   0.05131  -0.0691   0.9457   0.0667
  -6.250  -0.4151   0.05362   0.04737  -0.0694   0.9413   0.0678
  -6.000  -0.3895   0.04904   0.04227  -0.0680   0.9362   0.0392
  -5.750  -0.3672   0.04562   0.03861  -0.0690   0.9327   0.0374
  -5.500  -0.3509   0.04302   0.03571  -0.0681   0.9267   0.0361
  -5.250  -0.3286   0.04040   0.03276  -0.0679   0.9220   0.0350
  -5.000  -0.2999   0.03814   0.03014  -0.0687   0.9189   0.0362
  -4.750  -0.2807   0.03641   0.02812  -0.0674   0.9131   0.0370
  -4.500  -0.2557   0.03449   0.02590  -0.0671   0.9086   0.0370
  -4.250  -0.2256   0.03247   0.02358  -0.0677   0.9057   0.0363
  -4.000  -0.1925   0.03062   0.02142  -0.0686   0.9036   0.0359
  -3.750  -0.1760   0.02944   0.02006  -0.0664   0.8965   0.0357
  -3.500  -0.1463   0.02803   0.01844  -0.0667   0.8931   0.0358
  -3.250  -0.1135   0.02671   0.01697  -0.0674   0.8907   0.0361
  -3.000  -0.0857   0.02564   0.01580  -0.0673   0.8870   0.0367
  -2.750  -0.0649   0.02499   0.01505  -0.0660   0.8808   0.0388
  -2.500  -0.0344   0.02431   0.01428  -0.0664   0.8775   0.0408
  -2.250  -0.0041   0.02322   0.01326  -0.0669   0.8752   0.0420
  -2.000   0.0103   0.02270   0.01272  -0.0646   0.8676   0.0431
  -1.750   0.0374   0.02206   0.01199  -0.0647   0.8635   0.0450
  -1.500   0.0699   0.02147   0.01124  -0.0658   0.8609   0.0478
  -1.250   0.0884   0.02125   0.01089  -0.0643   0.8536   0.0511
  -1.000   0.1178   0.02085   0.01040  -0.0647   0.8493   0.0592
  -0.750   0.1514   0.02029   0.00986  -0.0659   0.8467   0.0872
  -0.500   0.1636   0.01877   0.00986  -0.0639   0.8396   0.5152
  -0.250   0.1843   0.01845   0.01013  -0.0618   0.8349   0.6546
   0.000   0.2113   0.01828   0.01020  -0.0607   0.8320   0.7278
   0.250   0.2299   0.01839   0.01026  -0.0589   0.8238   0.7422
   0.500   0.2621   0.01826   0.01007  -0.0597   0.8199   0.7569
   0.750   0.2986   0.01805   0.00983  -0.0612   0.8173   0.7722
   1.000   0.3153   0.01817   0.00997  -0.0591   0.8084   0.7885
   1.250   0.3495   0.01798   0.00978  -0.0601   0.8047   0.8057
   1.750   0.4028   0.01786   0.00970  -0.0594   0.7920   0.8460
   2.000   0.4419   0.01759   0.00946  -0.0614   0.7887   0.8661
   2.250   0.4653   0.01763   0.00958  -0.0606   0.7798   0.8910
   2.500   0.5117   0.01740   0.00942  -0.0642   0.7755   0.9147
   2.750   0.5587   0.01731   0.00941  -0.0682   0.7691   0.9439
   3.000   0.6068   0.01721   0.00939  -0.0726   0.7623   1.0000
   3.250   0.6334   0.01717   0.00934  -0.0725   0.7541   1.0000
   3.500   0.6627   0.01710   0.00927  -0.0729   0.7460   1.0000
   3.750   0.6845   0.01718   0.00937  -0.0719   0.7359   1.0000
   4.000   0.7205   0.01699   0.00923  -0.0733   0.7285   1.0000
   4.250   0.7414   0.01708   0.00937  -0.0720   0.7168   1.0000
   4.500   0.7642   0.01714   0.00947  -0.0711   0.7049   1.0000
   4.750   0.7895   0.01713   0.00951  -0.0705   0.6921   1.0000
   5.000   0.8150   0.01706   0.00952  -0.0698   0.6765   1.0000
   5.250   0.8433   0.01689   0.00936  -0.0695   0.6571   1.0000
   5.500   0.8644   0.01694   0.00943  -0.0681   0.6356   1.0000
   5.750   0.8901   0.01696   0.00947  -0.0674   0.6149   1.0000
   6.000   0.9131   0.01709   0.00966  -0.0664   0.5936   1.0000
   6.250   0.9355   0.01727   0.00986  -0.0652   0.5706   1.0000
   6.500   0.9543   0.01753   0.01014  -0.0635   0.5447   1.0000
   6.750   0.9704   0.01783   0.01039  -0.0612   0.5113   1.0000
   7.000   0.9813   0.01827   0.01063  -0.0579   0.4647   1.0000
   7.250   0.9862   0.01898   0.01104  -0.0538   0.4055   1.0000
   7.500   0.9874   0.01998   0.01162  -0.0494   0.3411   1.0000
   7.750   0.9882   0.02115   0.01239  -0.0453   0.2780   1.0000
   8.000   0.9919   0.02234   0.01326  -0.0419   0.2248   1.0000
   8.250   0.9985   0.02349   0.01420  -0.0391   0.1835   1.0000
   8.500   1.0061   0.02467   0.01520  -0.0365   0.1481   1.0000
   8.750   1.0133   0.02594   0.01631  -0.0341   0.1137   1.0000
   9.000   1.0197   0.02734   0.01754  -0.0315   0.0821   1.0000
   9.250   1.0256   0.02882   0.01892  -0.0291   0.0628   1.0000
   9.500   1.0320   0.03028   0.02032  -0.0267   0.0530   1.0000
   9.750   1.0397   0.03165   0.02177  -0.0246   0.0472   1.0000
  10.000   1.0444   0.03326   0.02342  -0.0223   0.0440   1.0000
  10.250   1.0512   0.03478   0.02507  -0.0202   0.0415   1.0000
  10.500   1.0582   0.03633   0.02677  -0.0183   0.0396   1.0000
  10.750   1.0652   0.03793   0.02847  -0.0166   0.0374   1.0000
  11.000   1.0707   0.03971   0.03031  -0.0149   0.0351   1.0000
  11.250   1.0766   0.04166   0.03231  -0.0132   0.0332   1.0000
  11.500   1.0872   0.04335   0.03423  -0.0119   0.0318   1.0000
  11.750   1.0987   0.04515   0.03619  -0.0107   0.0305   1.0000
  12.000   1.1097   0.04700   0.03820  -0.0095   0.0291   1.0000
  12.250   1.1188   0.04895   0.04026  -0.0085   0.0276   1.0000
  12.500   1.1262   0.05113   0.04248  -0.0075   0.0261   1.0000
  12.750   1.1360   0.05371   0.04521  -0.0066   0.0249   1.0000
  13.000   1.1431   0.05627   0.04807  -0.0055   0.0242   1.0000
  13.250   1.1470   0.05914   0.05124  -0.0044   0.0236   1.0000
  13.500   1.1469   0.06234   0.05473  -0.0034   0.0231   1.0000
  13.750   1.1430   0.06578   0.05845  -0.0026   0.0226   1.0000
  14.000   1.1358   0.06946   0.06241  -0.0021   0.0221   1.0000
  14.250   1.1265   0.07348   0.06669  -0.0019   0.0218   1.0000
  14.500   1.1153   0.07770   0.07115  -0.0022   0.0213   1.0000
  14.750   1.1035   0.08213   0.07578  -0.0029   0.0208   1.0000
  15.000   1.0886   0.08739   0.08128  -0.0043   0.0207   1.0000
  15.250   1.0694   0.09366   0.08782  -0.0065   0.0209   1.0000
  15.500   1.0529   0.09978   0.09413  -0.0093   0.0206   1.0000
  15.750   1.0331   0.10699   0.10155  -0.0131   0.0205   1.0000
  16.000   1.0008   0.11775   0.11259  -0.0195   0.0211   1.0000
  16.250   0.9639   0.13124   0.12630  -0.0281   0.0221   1.0000
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