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Apex 16 (normalized using XFOIL date021206) (apex16-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Apex 16 (normalized using XFOIL date021206) (apex16-il)
Reynolds number: 500,000
Max Cl/Cd: 112.59 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-apex16-il-500000.txt
Download as CSV file: xf-apex16-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2641   0.08859   0.08641  -0.0648   0.9870   0.0186
 -10.000  -0.2598   0.08387   0.08170  -0.0676   0.9859   0.0189
  -9.750  -0.3899   0.08744   0.08521  -0.0645   0.9909   0.0178
  -9.500  -0.3831   0.08222   0.07999  -0.0697   0.9885   0.0180
  -9.250  -0.3773   0.07657   0.07431  -0.0765   0.9861   0.0181
  -9.000  -0.3773   0.07037   0.06804  -0.0852   0.9830   0.0182
  -8.750  -0.3829   0.06621   0.06381  -0.0895   0.9758   0.0183
  -8.500  -0.3743   0.06168   0.05916  -0.0944   0.9723   0.0186
  -8.250  -0.3708   0.05829   0.05567  -0.0958   0.9659   0.0188
  -8.000  -0.3595   0.05470   0.05195  -0.0983   0.9618   0.0193
  -7.750  -0.3424   0.05092   0.04799  -0.1012   0.9594   0.0200
  -7.500  -0.3201   0.04724   0.04410  -0.1040   0.9579   0.0212
  -7.250  -0.3038   0.04610   0.04259  -0.1015   0.9501   0.0227
  -7.000  -0.2815   0.04304   0.03923  -0.1027   0.9475   0.0228
  -6.750  -0.2666   0.03655   0.03257  -0.1052   0.9455   0.0237
  -6.500  -0.2389   0.03416   0.03007  -0.1074   0.9440   0.0244
  -6.250  -0.2237   0.03262   0.02844  -0.1062   0.9373   0.0253
  -6.000  -0.1983   0.03069   0.02633  -0.1066   0.9337   0.0270
  -5.750  -0.1629   0.03075   0.02605  -0.1067   0.9315   0.0298
  -5.500  -0.1423   0.02568   0.02064  -0.1074   0.9291   0.0312
  -5.250  -0.1276   0.02434   0.01927  -0.1055   0.9220   0.0320
  -5.000  -0.1012   0.02299   0.01782  -0.1059   0.9186   0.0337
  -4.750  -0.0703   0.02205   0.01670  -0.1065   0.9161   0.0373
  -4.500  -0.0426   0.02316   0.01758  -0.1056   0.9117   0.0393
  -4.250  -0.0251   0.01903   0.01340  -0.1050   0.9063   0.0429
  -4.000   0.0039   0.01813   0.01242  -0.1055   0.9030   0.0462
  -3.750   0.0396   0.01514   0.00900  -0.1050   0.9008   0.0307
  -3.500   0.0623   0.01405   0.00791  -0.1039   0.8953   0.0288
  -3.250   0.0874   0.01302   0.00684  -0.1033   0.8907   0.0285
  -3.000   0.1149   0.01227   0.00603  -0.1033   0.8871   0.0288
  -2.750   0.1368   0.01172   0.00543  -0.1022   0.8818   0.0290
  -2.500   0.1619   0.01141   0.00508  -0.1017   0.8765   0.0299
  -2.250   0.1861   0.01062   0.00421  -0.1012   0.8723   0.0312
  -2.000   0.2080   0.01021   0.00376  -0.1001   0.8666   0.0325
  -1.750   0.2336   0.00990   0.00340  -0.0998   0.8613   0.0346
  -1.500   0.2628   0.00964   0.00308  -0.1001   0.8572   0.0375
  -1.250   0.2860   0.00945   0.00286  -0.0992   0.8509   0.0419
  -1.000   0.3102   0.00886   0.00256  -0.0987   0.8454   0.1649
  -0.750   0.3258   0.00768   0.00238  -0.0970   0.8394   0.5088
  -0.500   0.3501   0.00753   0.00237  -0.0963   0.8330   0.5577
  -0.250   0.3783   0.00741   0.00235  -0.0964   0.8279   0.6066
   0.000   0.4005   0.00735   0.00240  -0.0952   0.8204   0.6417
   0.250   0.4282   0.00731   0.00239  -0.0952   0.8144   0.6663
   0.500   0.4528   0.00730   0.00241  -0.0945   0.8071   0.6825
   0.750   0.4803   0.00728   0.00238  -0.0945   0.8005   0.6947
   1.000   0.5056   0.00727   0.00240  -0.0940   0.7930   0.7068
   1.250   0.5324   0.00727   0.00239  -0.0938   0.7859   0.7195
   1.500   0.5575   0.00727   0.00243  -0.0932   0.7781   0.7325
   2.000   0.6081   0.00727   0.00249  -0.0922   0.7621   0.7592
   2.250   0.6348   0.00728   0.00251  -0.0920   0.7544   0.7727
   2.500   0.6575   0.00728   0.00259  -0.0909   0.7445   0.7870
   2.750   0.6818   0.00730   0.00265  -0.0901   0.7352   0.8022
   3.000   0.7058   0.00733   0.00269  -0.0893   0.7242   0.8181
   3.250   0.7267   0.00735   0.00274  -0.0877   0.7081   0.8344
   3.500   0.7478   0.00738   0.00279  -0.0862   0.6920   0.8507
   3.750   0.7696   0.00742   0.00286  -0.0850   0.6785   0.8672
   4.000   0.7911   0.00745   0.00293  -0.0836   0.6643   0.8849
   4.250   0.8134   0.00749   0.00302  -0.0824   0.6490   0.9066
   4.500   0.8437   0.00759   0.00316  -0.0831   0.6271   0.9351
   4.750   0.8883   0.00789   0.00336  -0.0871   0.5947   0.9698
   5.000   0.9185   0.00816   0.00358  -0.0880   0.5687   1.0000
   5.250   0.9328   0.00843   0.00374  -0.0854   0.5398   1.0000
   5.500   0.9434   0.00880   0.00394  -0.0820   0.4993   1.0000
   5.750   0.9521   0.00925   0.00418  -0.0782   0.4550   1.0000
   6.000   0.9572   0.00980   0.00449  -0.0738   0.4064   1.0000
   6.250   0.9646   0.01038   0.00484  -0.0700   0.3605   1.0000
   6.500   0.9739   0.01099   0.00525  -0.0667   0.3157   1.0000
   6.750   0.9823   0.01170   0.00571  -0.0633   0.2654   1.0000
   7.000   0.9909   0.01248   0.00621  -0.0601   0.2138   1.0000
   7.250   0.9995   0.01331   0.00678  -0.0570   0.1665   1.0000
   7.500   1.0087   0.01416   0.00739  -0.0540   0.1235   1.0000
   7.750   1.0141   0.01524   0.00815  -0.0506   0.0701   1.0000
   8.000   1.0207   0.01631   0.00900  -0.0473   0.0395   1.0000
   8.250   1.0343   0.01700   0.00968  -0.0452   0.0340   1.0000
   8.500   1.0474   0.01774   0.01046  -0.0430   0.0306   1.0000
   8.750   1.0621   0.01838   0.01117  -0.0411   0.0288   1.0000
   9.000   1.0755   0.01911   0.01195  -0.0392   0.0269   1.0000
   9.250   1.0848   0.02009   0.01298  -0.0367   0.0250   1.0000
   9.500   1.0922   0.02123   0.01420  -0.0340   0.0237   1.0000
   9.750   1.1056   0.02200   0.01504  -0.0322   0.0227   1.0000
  10.000   1.1179   0.02286   0.01596  -0.0304   0.0215   1.0000
  10.250   1.1291   0.02381   0.01696  -0.0285   0.0202   1.0000
  10.500   1.1372   0.02500   0.01820  -0.0264   0.0192   1.0000
  10.750   1.1343   0.02719   0.02048  -0.0230   0.0181   1.0000
  11.000   1.1473   0.02813   0.02151  -0.0215   0.0176   1.0000
  11.250   1.1588   0.02922   0.02268  -0.0200   0.0169   1.0000
  11.500   1.1689   0.03049   0.02403  -0.0184   0.0162   1.0000
  11.750   1.1791   0.03171   0.02532  -0.0169   0.0154   1.0000
  12.000   1.1884   0.03305   0.02672  -0.0154   0.0148   1.0000
  12.250   1.1965   0.03459   0.02831  -0.0140   0.0143   1.0000
  12.500   1.2041   0.03720   0.03101  -0.0122   0.0135   1.0000
  12.750   1.2117   0.03832   0.03227  -0.0109   0.0131   1.0000
  13.000   1.2197   0.03990   0.03399  -0.0096   0.0126   1.0000
  13.250   1.2272   0.04175   0.03597  -0.0083   0.0123   1.0000
  13.500   1.2334   0.04375   0.03812  -0.0070   0.0120   1.0000
  13.750   1.2380   0.04562   0.04010  -0.0059   0.0115   1.0000
  14.000   1.2420   0.04786   0.04248  -0.0047   0.0113   1.0000
  14.250   1.2436   0.05010   0.04485  -0.0038   0.0110   1.0000
  14.500   1.2439   0.05286   0.04778  -0.0028   0.0109   1.0000
  14.750   1.2428   0.05558   0.05062  -0.0021   0.0108   1.0000
  15.000   1.2416   0.05832   0.05347  -0.0016   0.0106   1.0000
  15.250   1.2370   0.06175   0.05704  -0.0012   0.0104   1.0000
  15.500   1.2295   0.06569   0.06115  -0.0010   0.0103   1.0000
  15.750   1.2128   0.07123   0.06691  -0.0011   0.0101   1.0000
  16.000   1.2022   0.07568   0.07154  -0.0019   0.0101   1.0000
  16.250   1.1835   0.08169   0.07777  -0.0032   0.0101   1.0000
  16.500   1.1670   0.08758   0.08384  -0.0051   0.0101   1.0000
  16.750   1.1549   0.09295   0.08938  -0.0074   0.0101   1.0000
  17.000   1.1331   0.10041   0.09703  -0.0107   0.0101   1.0000
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