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

NACA 642-015A AIRFOIL (n64015a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 642-015A AIRFOIL (n64015a-il)
Reynolds number: 200,000
Max Cl/Cd: 44.49 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64015a-il-200000-n5.txt
Download as CSV file: xf-n64015a-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 642-015A AIRFOIL                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -0.8974   0.10088   0.09652  -0.0205   1.0000   0.0203
 -15.750  -0.9345   0.08982   0.08519  -0.0271   1.0000   0.0201
 -15.500  -0.9604   0.08190   0.07703  -0.0313   1.0000   0.0201
 -15.250  -0.9806   0.07547   0.07037  -0.0342   1.0000   0.0201
 -15.000  -0.9968   0.07007   0.06475  -0.0362   1.0000   0.0202
 -14.750  -1.0099   0.06537   0.05983  -0.0376   1.0000   0.0203
 -14.500  -1.0200   0.06123   0.05548  -0.0384   1.0000   0.0204
 -14.250  -1.0274   0.05754   0.05158  -0.0389   1.0000   0.0206
 -14.000  -1.0324   0.05421   0.04803  -0.0390   1.0000   0.0208
 -13.750  -1.0348   0.05122   0.04483  -0.0389   1.0000   0.0210
 -13.500  -1.0349   0.04852   0.04193  -0.0385   1.0000   0.0213
 -13.250  -1.0330   0.04607   0.03928  -0.0380   1.0000   0.0216
 -13.000  -1.0292   0.04384   0.03683  -0.0373   1.0000   0.0220
 -12.750  -1.0235   0.04182   0.03459  -0.0366   1.0000   0.0224
 -12.500  -1.0149   0.03995   0.03260  -0.0358   1.0000   0.0228
 -12.250  -1.0046   0.03832   0.03092  -0.0350   1.0000   0.0232
 -12.000  -0.9938   0.03683   0.02935  -0.0342   1.0000   0.0236
 -11.750  -0.9822   0.03540   0.02785  -0.0334   1.0000   0.0240
 -11.500  -0.9700   0.03404   0.02641  -0.0325   1.0000   0.0244
 -11.250  -0.9572   0.03273   0.02502  -0.0315   1.0000   0.0250
 -11.000  -0.9440   0.03147   0.02367  -0.0305   1.0000   0.0255
 -10.750  -0.9305   0.03027   0.02237  -0.0294   1.0000   0.0262
 -10.500  -0.9168   0.02912   0.02111  -0.0283   1.0000   0.0268
 -10.250  -0.9030   0.02804   0.01993  -0.0271   1.0000   0.0275
 -10.000  -0.8920   0.02684   0.01872  -0.0257   1.0000   0.0282
  -9.750  -0.8799   0.02585   0.01772  -0.0243   1.0000   0.0292
  -9.500  -0.8671   0.02498   0.01682  -0.0228   1.0000   0.0303
  -9.250  -0.8546   0.02415   0.01593  -0.0211   1.0000   0.0316
  -9.000  -0.8428   0.02337   0.01509  -0.0191   1.0000   0.0329
  -8.750  -0.8343   0.02256   0.01426  -0.0165   1.0000   0.0341
  -8.500  -0.8264   0.02184   0.01355  -0.0137   1.0000   0.0355
  -8.250  -0.8167   0.02123   0.01292  -0.0110   1.0000   0.0371
  -8.000  -0.8086   0.02070   0.01234  -0.0080   1.0000   0.0390
  -7.750  -0.7870   0.01997   0.01160  -0.0078   0.9941   0.0420
  -7.500  -0.7568   0.01924   0.01085  -0.0092   0.9834   0.0468
  -7.250  -0.7275   0.01850   0.01010  -0.0105   0.9719   0.0524
  -7.000  -0.6983   0.01784   0.00942  -0.0115   0.9602   0.0601
  -6.750  -0.6707   0.01719   0.00879  -0.0122   0.9471   0.0707
  -6.500  -0.6450   0.01653   0.00818  -0.0124   0.9335   0.0859
  -6.250  -0.6206   0.01587   0.00760  -0.0124   0.9199   0.1091
  -6.000  -0.5992   0.01511   0.00702  -0.0118   0.9061   0.1477
  -5.750  -0.5803   0.01426   0.00643  -0.0108   0.8927   0.2044
  -5.500  -0.5642   0.01332   0.00583  -0.0092   0.8797   0.2829
  -5.250  -0.5506   0.01239   0.00537  -0.0071   0.8666   0.3804
  -5.000  -0.5316   0.01195   0.00520  -0.0055   0.8551   0.4583
  -4.750  -0.5082   0.01177   0.00507  -0.0046   0.8452   0.4981
  -4.500  -0.4837   0.01166   0.00494  -0.0038   0.8349   0.5254
  -4.250  -0.4585   0.01157   0.00483  -0.0033   0.8256   0.5450
  -4.000  -0.4329   0.01151   0.00472  -0.0027   0.8166   0.5624
  -3.750  -0.4077   0.01149   0.00467  -0.0021   0.8077   0.5832
  -3.500  -0.3825   0.01149   0.00463  -0.0014   0.7994   0.6033
  -3.250  -0.3565   0.01148   0.00460  -0.0010   0.7907   0.6172
  -3.000  -0.3297   0.01146   0.00454  -0.0006   0.7831   0.6273
  -2.750  -0.3029   0.01143   0.00444  -0.0004   0.7753   0.6364
  -2.500  -0.2755   0.01139   0.00436  -0.0003   0.7678   0.6426
  -2.250  -0.2483   0.01135   0.00423  -0.0002   0.7604   0.6491
  -2.000  -0.2208   0.01130   0.00415  -0.0002   0.7527   0.6542
  -1.750  -0.1932   0.01127   0.00407  -0.0001   0.7461   0.6595
  -1.500  -0.1658   0.01124   0.00399  -0.0001   0.7389   0.6658
  -1.250  -0.1380   0.01121   0.00393  -0.0001   0.7328   0.6709
  -1.000  -0.1105   0.01118   0.00390  -0.0001   0.7255   0.6764
  -0.750  -0.0830   0.01117   0.00382   0.0000   0.7188   0.6827
  -0.500  -0.0552   0.01115   0.00381   0.0000   0.7126   0.6879
  -0.250  -0.0277   0.01115   0.00381   0.0000   0.7060   0.6942
   0.000   0.0000   0.01115   0.00378   0.0000   0.7005   0.7005
   0.250   0.0277   0.01115   0.00381   0.0000   0.6942   0.7060
   0.500   0.0552   0.01115   0.00381   0.0000   0.6879   0.7126
   0.750   0.0830   0.01117   0.00382   0.0000   0.6827   0.7188
   1.000   0.1105   0.01118   0.00390   0.0001   0.6764   0.7256
   1.250   0.1380   0.01121   0.00393   0.0001   0.6709   0.7328
   1.500   0.1658   0.01124   0.00399   0.0001   0.6658   0.7389
   1.750   0.1932   0.01127   0.00407   0.0001   0.6595   0.7462
   2.000   0.2208   0.01130   0.00415   0.0002   0.6542   0.7527
   2.250   0.2483   0.01135   0.00423   0.0002   0.6491   0.7604
   2.500   0.2756   0.01139   0.00436   0.0003   0.6426   0.7678
   2.750   0.3029   0.01143   0.00444   0.0004   0.6364   0.7753
   3.000   0.3298   0.01146   0.00454   0.0006   0.6273   0.7831
   3.250   0.3565   0.01148   0.00460   0.0010   0.6172   0.7908
   3.500   0.3825   0.01149   0.00463   0.0014   0.6033   0.7994
   3.750   0.4078   0.01149   0.00467   0.0021   0.5832   0.8077
   4.000   0.4329   0.01151   0.00472   0.0027   0.5624   0.8166
   4.250   0.4585   0.01157   0.00483   0.0033   0.5450   0.8256
   4.500   0.4838   0.01166   0.00494   0.0038   0.5253   0.8349
   4.750   0.5083   0.01177   0.00507   0.0045   0.4981   0.8452
   5.000   0.5316   0.01195   0.00520   0.0055   0.4582   0.8551
   5.250   0.5506   0.01239   0.00537   0.0070   0.3801   0.8666
   5.500   0.5643   0.01332   0.00583   0.0092   0.2828   0.8797
   5.750   0.5804   0.01426   0.00643   0.0107   0.2042   0.8926
   6.000   0.5993   0.01511   0.00702   0.0118   0.1477   0.9061
   6.250   0.6207   0.01587   0.00760   0.0124   0.1090   0.9199
   6.500   0.6451   0.01653   0.00818   0.0124   0.0859   0.9335
   6.750   0.6708   0.01719   0.00879   0.0121   0.0706   0.9471
   7.000   0.6984   0.01784   0.00942   0.0115   0.0601   0.9602
   7.250   0.7276   0.01850   0.01010   0.0104   0.0524   0.9720
   7.500   0.7569   0.01924   0.01085   0.0092   0.0468   0.9835
   7.750   0.7871   0.01997   0.01160   0.0077   0.0420   0.9941
   8.000   0.8086   0.02069   0.01234   0.0080   0.0390   1.0000
   8.250   0.8168   0.02123   0.01291   0.0110   0.0371   1.0000
   8.500   0.8266   0.02184   0.01354   0.0136   0.0355   1.0000
   8.750   0.8346   0.02256   0.01426   0.0165   0.0341   1.0000
   9.000   0.8432   0.02337   0.01509   0.0190   0.0329   1.0000
   9.250   0.8550   0.02415   0.01593   0.0210   0.0316   1.0000
   9.500   0.8676   0.02498   0.01682   0.0227   0.0303   1.0000
   9.750   0.8804   0.02585   0.01772   0.0242   0.0292   1.0000
  10.000   0.8927   0.02684   0.01872   0.0256   0.0282   1.0000
  10.250   0.9037   0.02804   0.01993   0.0270   0.0275   1.0000
  10.500   0.9176   0.02912   0.02111   0.0282   0.0268   1.0000
  10.750   0.9313   0.03027   0.02237   0.0293   0.0262   1.0000
  11.000   0.9448   0.03147   0.02367   0.0304   0.0255   1.0000
  11.250   0.9581   0.03273   0.02502   0.0314   0.0249   1.0000
  11.500   0.9709   0.03404   0.02641   0.0323   0.0244   1.0000
  11.750   0.9832   0.03540   0.02785   0.0332   0.0240   1.0000
  12.000   0.9948   0.03683   0.02935   0.0340   0.0236   1.0000
  12.250   1.0057   0.03832   0.03092   0.0348   0.0232   1.0000
  12.500   1.0160   0.03995   0.03260   0.0356   0.0228   1.0000
  12.750   1.0247   0.04182   0.03459   0.0364   0.0224   1.0000
  13.000   1.0304   0.04385   0.03684   0.0371   0.0220   1.0000
  13.250   1.0342   0.04608   0.03929   0.0378   0.0216   1.0000
  13.500   1.0361   0.04852   0.04194   0.0383   0.0213   1.0000
  13.750   1.0361   0.05123   0.04485   0.0387   0.0210   1.0000
  14.000   1.0337   0.05423   0.04805   0.0388   0.0208   1.0000
  14.250   1.0288   0.05755   0.05160   0.0387   0.0206   1.0000
  14.500   1.0214   0.06125   0.05551   0.0382   0.0204   1.0000
  14.750   1.0113   0.06540   0.05986   0.0373   0.0203   1.0000
  15.000   0.9984   0.07009   0.06477   0.0359   0.0202   1.0000
  15.250   0.9821   0.07551   0.07041   0.0339   0.0201   1.0000
  15.500   0.9619   0.08194   0.07707   0.0309   0.0201   1.0000
  15.750   0.9358   0.08994   0.08532   0.0267   0.0201   1.0000
  16.000   0.8982   0.10112   0.09677   0.0200   0.0203   1.0000
<< Back to NACA 642-015A AIRFOIL (n64015a-il)

Polar data table (+)

Polar graphs


<< Back to NACA 642-015A AIRFOIL (n64015a-il)