Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 16-021 (naca16021-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 16-021 (naca16021-il)
Reynolds number: 200,000
Max Cl/Cd: 26.34 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca16021-il-200000-n5.txt
Download as CSV file: xf-naca16021-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 16-021                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -0.9810   0.10059   0.09479  -0.0834   0.9963   0.0298
 -19.500  -0.9889   0.09601   0.09006  -0.0853   0.9956   0.0301
 -19.250  -0.9897   0.09256   0.08655  -0.0868   0.9949   0.0305
 -19.000  -0.9909   0.08908   0.08298  -0.0883   0.9942   0.0309
 -18.750  -0.9920   0.08562   0.07941  -0.0897   0.9936   0.0314
 -18.500  -0.9943   0.08222   0.07589  -0.0905   0.9925   0.0318
 -18.250  -0.9963   0.07893   0.07247  -0.0911   0.9912   0.0323
 -18.000  -0.9976   0.07580   0.06918  -0.0915   0.9899   0.0329
 -17.750  -0.9982   0.07286   0.06606  -0.0918   0.9888   0.0334
 -17.500  -0.9978   0.07009   0.06310  -0.0919   0.9877   0.0340
 -17.250  -0.9963   0.06746   0.06026  -0.0919   0.9866   0.0347
 -17.000  -0.9917   0.06520   0.05788  -0.0919   0.9857   0.0353
 -16.750  -0.9847   0.06324   0.05587  -0.0920   0.9849   0.0359
 -16.500  -0.9768   0.06132   0.05388  -0.0921   0.9841   0.0365
 -16.250  -0.9676   0.05947   0.05194  -0.0924   0.9833   0.0372
 -16.000  -0.9602   0.05773   0.05009  -0.0919   0.9820   0.0380
 -15.750  -0.9547   0.05614   0.04840  -0.0907   0.9798   0.0388
 -15.500  -0.9469   0.05462   0.04675  -0.0898   0.9781   0.0396
 -15.250  -0.9371   0.05320   0.04517  -0.0892   0.9767   0.0404
 -15.000  -0.9264   0.05178   0.04369  -0.0887   0.9755   0.0412
 -14.750  -0.9153   0.05039   0.04227  -0.0883   0.9744   0.0420
 -14.500  -0.9024   0.04908   0.04089  -0.0881   0.9734   0.0429
 -14.250  -0.8881   0.04781   0.03956  -0.0881   0.9725   0.0439
 -14.000  -0.8725   0.04662   0.03827  -0.0882   0.9717   0.0452
 -13.750  -0.8634   0.04560   0.03716  -0.0865   0.9694   0.0462
 -13.500  -0.8551   0.04467   0.03612  -0.0846   0.9668   0.0471
 -13.250  -0.8454   0.04354   0.03497  -0.0833   0.9650   0.0482
 -13.000  -0.8334   0.04245   0.03386  -0.0824   0.9634   0.0493
 -12.750  -0.8188   0.04143   0.03279  -0.0819   0.9621   0.0506
 -12.500  -0.8023   0.04045   0.03174  -0.0816   0.9609   0.0524
 -12.250  -0.7843   0.03953   0.03071  -0.0816   0.9599   0.0542
 -12.000  -0.7680   0.03847   0.02963  -0.0814   0.9591   0.0560
 -11.750  -0.7655   0.03777   0.02892  -0.0779   0.9555   0.0574
 -11.500  -0.7572   0.03704   0.02815  -0.0755   0.9526   0.0593
 -11.250  -0.7431   0.03627   0.02731  -0.0744   0.9506   0.0617
 -11.000  -0.7273   0.03543   0.02644  -0.0736   0.9490   0.0646
 -10.750  -0.7102   0.03459   0.02560  -0.0732   0.9477   0.0682
 -10.500  -0.6907   0.03387   0.02481  -0.0730   0.9466   0.0728
 -10.250  -0.6730   0.03305   0.02400  -0.0726   0.9457   0.0780
 -10.000  -0.6701   0.03265   0.02358  -0.0686   0.9417   0.0823
  -9.750  -0.6628   0.03211   0.02304  -0.0657   0.9381   0.0877
  -9.500  -0.6468   0.03149   0.02241  -0.0646   0.9359   0.0955
  -9.250  -0.6300   0.03079   0.02175  -0.0637   0.9343   0.1052
  -9.000  -0.6119   0.03014   0.02112  -0.0631   0.9330   0.1169
  -8.750  -0.5930   0.02948   0.02051  -0.0626   0.9319   0.1309
  -8.500  -0.5736   0.02880   0.01989  -0.0622   0.9310   0.1477
  -8.250  -0.5830   0.02865   0.01977  -0.0553   0.9241   0.1573
  -8.000  -0.5710   0.02804   0.01923  -0.0532   0.9215   0.1770
  -7.750  -0.5576   0.02737   0.01867  -0.0515   0.9195   0.2030
  -7.500  -0.5448   0.02658   0.01804  -0.0497   0.9180   0.2368
  -7.250  -0.5338   0.02566   0.01733  -0.0476   0.9167   0.2808
  -7.000  -0.5473   0.02528   0.01710  -0.0399   0.9101   0.3107
  -6.750  -0.5514   0.02445   0.01651  -0.0344   0.9062   0.3595
  -6.500  -0.5552   0.02339   0.01577  -0.0290   0.9035   0.4208
  -6.250  -0.5579   0.02228   0.01505  -0.0237   0.9015   0.4942
  -6.000  -0.5789   0.02200   0.01503  -0.0138   0.8941   0.5392
  -5.750  -0.5506   0.02215   0.01573  -0.0137   0.8925   0.6328
  -5.500  -0.4933   0.02322   0.01697  -0.0193   0.8926   0.6801
  -5.250  -0.4596   0.02376   0.01750  -0.0204   0.8911   0.7008
  -5.000  -0.4303   0.02409   0.01780  -0.0208   0.8894   0.7158
  -4.500  -0.3812   0.02415   0.01775  -0.0199   0.8865   0.7426
  -4.250  -0.3454   0.02466   0.01822  -0.0215   0.8858   0.7526
  -4.000  -0.3161   0.02534   0.01887  -0.0215   0.8843   0.7628
  -3.750  -0.3429   0.02562   0.01917  -0.0103   0.8748   0.7756
  -3.250  -0.2733   0.02684   0.02029  -0.0129   0.8723   0.7871
  -3.000  -0.2467   0.02682   0.02022  -0.0130   0.8712   0.7919
  -2.500  -0.2456   0.02697   0.02033  -0.0025   0.8603   0.8063
  -2.250  -0.2098   0.02728   0.02060  -0.0045   0.8589   0.8072
  -2.000  -0.1738   0.02753   0.02082  -0.0065   0.8577   0.8083
  -1.750  -0.1374   0.02770   0.02096  -0.0086   0.8566   0.8097
  -1.250  -0.1327   0.02764   0.02087   0.0009   0.8468   0.8230
  -1.000  -0.1011   0.02787   0.02109  -0.0003   0.8444   0.8241
  -0.750  -0.0674   0.02797   0.02117  -0.0019   0.8427   0.8253
  -0.500  -0.0335   0.02801   0.02120  -0.0036   0.8413   0.8267
  -0.250  -0.0007   0.02799   0.02117  -0.0051   0.8402   0.8286
   0.000   0.0292   0.02781   0.02099  -0.0060   0.8391   0.8314
   0.500   0.0334   0.02801   0.02120   0.0036   0.8267   0.8413
   0.750   0.0675   0.02797   0.02117   0.0019   0.8253   0.8427
   1.000   0.1011   0.02787   0.02109   0.0003   0.8241   0.8444
   1.250   0.1326   0.02764   0.02087  -0.0009   0.8230   0.8468
   1.750   0.1375   0.02770   0.02096   0.0086   0.8097   0.8566
   2.000   0.1738   0.02753   0.02082   0.0065   0.8083   0.8577
   2.250   0.2098   0.02728   0.02060   0.0045   0.8072   0.8589
   2.500   0.2456   0.02696   0.02032   0.0025   0.8063   0.8604
   3.000   0.2467   0.02682   0.02022   0.0130   0.7919   0.8712
   3.250   0.2729   0.02684   0.02030   0.0130   0.7870   0.8724
   3.750   0.3429   0.02561   0.01916   0.0103   0.7756   0.8749
   4.000   0.3108   0.02531   0.01884   0.0226   0.7628   0.8851
   4.250   0.3458   0.02465   0.01821   0.0214   0.7526   0.8858
   4.500   0.3814   0.02413   0.01774   0.0199   0.7426   0.8866
   4.750   0.4031   0.02424   0.01790   0.0208   0.7290   0.8880
   5.000   0.4305   0.02408   0.01778   0.0208   0.7158   0.8895
   5.250   0.4598   0.02374   0.01748   0.0204   0.7007   0.8911
   5.500   0.4935   0.02320   0.01694   0.0193   0.6800   0.8926
   5.750   0.5504   0.02214   0.01572   0.0138   0.6334   0.8926
   6.000   0.5790   0.02198   0.01501   0.0138   0.5398   0.8942
   6.250   0.5582   0.02227   0.01504   0.0236   0.4940   0.9016
   6.500   0.5557   0.02337   0.01575   0.0289   0.4212   0.9035
   6.750   0.5517   0.02443   0.01649   0.0344   0.3596   0.9062
   7.000   0.5472   0.02525   0.01707   0.0399   0.3111   0.9103
   7.250   0.5343   0.02564   0.01732   0.0475   0.2809   0.9167
   7.500   0.5453   0.02656   0.01802   0.0496   0.2369   0.9180
   7.750   0.5582   0.02735   0.01864   0.0514   0.2033   0.9196
   8.000   0.5714   0.02802   0.01921   0.0531   0.1769   0.9216
   8.250   0.5831   0.02863   0.01974   0.0553   0.1572   0.9243
   8.500   0.5743   0.02878   0.01986   0.0621   0.1474   0.9310
   8.750   0.5937   0.02945   0.02048   0.0625   0.1307   0.9319
   9.000   0.6126   0.03011   0.02110   0.0629   0.1168   0.9330
   9.250   0.6307   0.03076   0.02171   0.0636   0.1051   0.9344
   9.500   0.6475   0.03146   0.02238   0.0645   0.0954   0.9361
   9.750   0.6633   0.03207   0.02300   0.0656   0.0877   0.9383
  10.000   0.6686   0.03258   0.02351   0.0690   0.0825   0.9423
  10.250   0.6741   0.03302   0.02397   0.0724   0.0778   0.9457
  10.500   0.6918   0.03384   0.02478   0.0728   0.0727   0.9467
  10.750   0.7113   0.03456   0.02556   0.0730   0.0682   0.9478
  11.000   0.7284   0.03540   0.02640   0.0734   0.0645   0.9491
  11.250   0.7442   0.03623   0.02727   0.0742   0.0617   0.9508
  11.500   0.7580   0.03699   0.02810   0.0754   0.0592   0.9528
  11.750   0.7651   0.03769   0.02884   0.0780   0.0574   0.9560
  12.000   0.7695   0.03843   0.02959   0.0811   0.0559   0.9592
  12.250   0.7860   0.03948   0.03066   0.0813   0.0541   0.9600
  12.500   0.8039   0.04040   0.03169   0.0814   0.0523   0.9611
  12.750   0.8205   0.04137   0.03273   0.0816   0.0506   0.9622
  13.000   0.8350   0.04239   0.03379   0.0821   0.0492   0.9636
  13.250   0.8468   0.04347   0.03490   0.0831   0.0481   0.9652
  13.500   0.8564   0.04460   0.03604   0.0844   0.0471   0.9671
  13.750   0.8631   0.04550   0.03705   0.0868   0.0462   0.9701
  14.000   0.8748   0.04655   0.03820   0.0878   0.0451   0.9718
  14.250   0.8904   0.04775   0.03948   0.0877   0.0439   0.9727
  14.500   0.9047   0.04901   0.04082   0.0877   0.0429   0.9736
  14.750   0.9176   0.05032   0.04219   0.0879   0.0420   0.9746
  15.000   0.9287   0.05170   0.04361   0.0883   0.0412   0.9757
  15.250   0.9394   0.05311   0.04508   0.0889   0.0404   0.9770
  15.500   0.9490   0.05453   0.04666   0.0895   0.0395   0.9784
  15.750   0.9567   0.05604   0.04830   0.0905   0.0387   0.9802
  16.000   0.9614   0.05761   0.04997   0.0919   0.0380   0.9826
  16.250   0.9708   0.05938   0.05185   0.0919   0.0372   0.9835
  16.500   0.9799   0.06122   0.05379   0.0916   0.0365   0.9842
  16.750   0.9878   0.06314   0.05576   0.0915   0.0358   0.9851
  17.000   0.9948   0.06510   0.05777   0.0914   0.0352   0.9859
  17.250   0.9993   0.06736   0.06017   0.0914   0.0346   0.9869
  17.500   1.0009   0.06998   0.06300   0.0914   0.0340   0.9880
  17.750   1.0012   0.07276   0.06596   0.0913   0.0334   0.9891
  18.000   1.0007   0.07570   0.06908   0.0911   0.0328   0.9903
  18.250   0.9995   0.07883   0.07236   0.0907   0.0323   0.9916
  18.500   0.9976   0.08210   0.07577   0.0901   0.0318   0.9929
  18.750   0.9960   0.08548   0.07927   0.0891   0.0313   0.9938
  19.000   0.9951   0.08892   0.08281   0.0877   0.0309   0.9944
  19.250   0.9941   0.09237   0.08634   0.0863   0.0305   0.9951
<< Back to NACA 16-021 (naca16021-il)

Polar data table (+)

Polar graphs


<< Back to NACA 16-021 (naca16021-il)