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NACA 63A010 AIRFOIL (n63010a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 63A010 AIRFOIL (n63010a-il)
Reynolds number: 1,000,000
Max Cl/Cd: 59.73 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n63010a-il-1000000.txt
Download as CSV file: xf-n63010a-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63A010 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.8763   0.06182   0.06001  -0.0175   1.0000   0.0082
 -11.250  -0.9108   0.05361   0.05159  -0.0222   1.0000   0.0081
 -11.000  -0.9484   0.04667   0.04437  -0.0227   1.0000   0.0080
 -10.750  -0.9842   0.04040   0.03771  -0.0194   1.0000   0.0080
 -10.500  -1.0000   0.03490   0.03176  -0.0166   1.0000   0.0081
 -10.250  -0.9999   0.03110   0.02760  -0.0144   1.0000   0.0083
 -10.000  -0.9912   0.02835   0.02453  -0.0127   1.0000   0.0085
  -9.750  -0.9768   0.02643   0.02237  -0.0114   1.0000   0.0087
  -9.500  -0.9582   0.02523   0.02099  -0.0105   1.0000   0.0090
  -9.250  -0.9446   0.02271   0.01813  -0.0090   1.0000   0.0093
  -9.000  -0.9293   0.02043   0.01567  -0.0078   1.0000   0.0099
  -8.750  -0.9073   0.01975   0.01493  -0.0072   1.0000   0.0102
  -8.500  -0.8854   0.01891   0.01400  -0.0065   1.0000   0.0106
  -8.250  -0.8634   0.01800   0.01299  -0.0058   1.0000   0.0109
  -8.000  -0.8414   0.01709   0.01199  -0.0050   1.0000   0.0112
  -7.750  -0.8194   0.01620   0.01101  -0.0042   1.0000   0.0116
  -7.500  -0.7973   0.01541   0.01013  -0.0033   1.0000   0.0120
  -7.250  -0.7750   0.01474   0.00939  -0.0025   1.0000   0.0124
  -7.000  -0.7520   0.01430   0.00890  -0.0017   1.0000   0.0127
  -6.750  -0.7339   0.01315   0.00764   0.0000   1.0000   0.0133
  -6.500  -0.7153   0.01227   0.00669   0.0015   1.0000   0.0140
  -6.250  -0.6945   0.01175   0.00614   0.0028   1.0000   0.0146
  -6.000  -0.6736   0.01131   0.00568   0.0040   1.0000   0.0151
  -5.750  -0.6518   0.01091   0.00524   0.0050   0.9998   0.0157
  -5.500  -0.6173   0.01046   0.00475   0.0033   0.9972   0.0166
  -5.250  -0.5821   0.01009   0.00435   0.0015   0.9946   0.0175
  -5.000  -0.5492   0.00956   0.00375   0.0002   0.9905   0.0194
  -4.750  -0.5148   0.00919   0.00337  -0.0015   0.9864   0.0220
  -4.500  -0.4804   0.00893   0.00310  -0.0030   0.9815   0.0245
  -4.250  -0.4491   0.00849   0.00271  -0.0039   0.9728   0.0373
  -4.000  -0.4185   0.00813   0.00244  -0.0047   0.9625   0.0599
  -3.750  -0.3908   0.00766   0.00217  -0.0049   0.9491   0.1098
  -3.500  -0.3665   0.00704   0.00188  -0.0045   0.9327   0.1983
  -3.250  -0.3439   0.00636   0.00160  -0.0037   0.9152   0.3112
  -3.000  -0.3208   0.00582   0.00138  -0.0030   0.8983   0.4143
  -2.750  -0.2964   0.00548   0.00125  -0.0024   0.8822   0.4882
  -2.500  -0.2711   0.00526   0.00117  -0.0019   0.8670   0.5456
  -2.250  -0.2446   0.00517   0.00110  -0.0016   0.8527   0.5729
  -2.000  -0.2180   0.00509   0.00104  -0.0013   0.8391   0.5982
  -1.750  -0.1915   0.00500   0.00100  -0.0010   0.8261   0.6326
  -1.500  -0.1647   0.00493   0.00098  -0.0007   0.8138   0.6595
  -1.000  -0.1102   0.00488   0.00093  -0.0004   0.7907   0.6961
  -0.750  -0.0829   0.00487   0.00092  -0.0002   0.7797   0.7111
  -0.500  -0.0554   0.00486   0.00091  -0.0001   0.7687   0.7251
  -0.250  -0.0276   0.00486   0.00090  -0.0001   0.7580   0.7370
   0.000   0.0000   0.00485   0.00090   0.0000   0.7476   0.7476
   0.250   0.0276   0.00486   0.00090   0.0001   0.7370   0.7581
   0.500   0.0553   0.00486   0.00091   0.0001   0.7251   0.7687
   0.750   0.0829   0.00487   0.00092   0.0002   0.7111   0.7797
   1.000   0.1102   0.00488   0.00093   0.0004   0.6962   0.7907
   1.250   0.1374   0.00491   0.00095   0.0006   0.6794   0.8020
   1.500   0.1647   0.00493   0.00098   0.0007   0.6595   0.8138
   1.750   0.1915   0.00500   0.00100   0.0010   0.6324   0.8261
   2.000   0.2180   0.00509   0.00104   0.0013   0.5982   0.8391
   2.250   0.2446   0.00517   0.00110   0.0016   0.5728   0.8527
   2.500   0.2711   0.00526   0.00117   0.0019   0.5445   0.8670
   2.750   0.2964   0.00548   0.00125   0.0024   0.4888   0.8822
   3.000   0.3209   0.00582   0.00138   0.0030   0.4144   0.8983
   3.250   0.3440   0.00635   0.00159   0.0037   0.3123   0.9151
   3.500   0.3665   0.00704   0.00188   0.0045   0.1975   0.9326
   3.750   0.3908   0.00766   0.00217   0.0049   0.1094   0.9491
   4.000   0.4186   0.00813   0.00244   0.0047   0.0600   0.9625
   4.250   0.4491   0.00849   0.00270   0.0039   0.0374   0.9728
   4.500   0.4803   0.00893   0.00310   0.0031   0.0245   0.9815
   4.750   0.5147   0.00919   0.00337   0.0015   0.0220   0.9864
   5.000   0.5491   0.00956   0.00375  -0.0001   0.0194   0.9905
   5.250   0.5821   0.01009   0.00434  -0.0015   0.0175   0.9946
   5.500   0.6172   0.01046   0.00475  -0.0033   0.0166   0.9973
   5.750   0.6517   0.01091   0.00523  -0.0050   0.0157   0.9999
   6.000   0.6733   0.01131   0.00568  -0.0039   0.0151   1.0000
   6.250   0.6943   0.01175   0.00614  -0.0027   0.0145   1.0000
   6.500   0.7152   0.01227   0.00670  -0.0015   0.0140   1.0000
   6.750   0.7338   0.01316   0.00764   0.0001   0.0133   1.0000
   7.000   0.7518   0.01431   0.00890   0.0017   0.0127   1.0000
   7.250   0.7750   0.01473   0.00939   0.0025   0.0124   1.0000
   7.500   0.7973   0.01541   0.01013   0.0033   0.0120   1.0000
   7.750   0.8194   0.01621   0.01102   0.0042   0.0116   1.0000
   8.000   0.8415   0.01710   0.01199   0.0050   0.0112   1.0000
   8.250   0.8635   0.01801   0.01301   0.0058   0.0109   1.0000
   8.500   0.8854   0.01893   0.01402   0.0065   0.0106   1.0000
   8.750   0.9074   0.01976   0.01495   0.0072   0.0102   1.0000
   9.000   0.9294   0.02045   0.01569   0.0077   0.0099   1.0000
   9.250   0.9448   0.02272   0.01815   0.0090   0.0093   1.0000
   9.500   0.9584   0.02524   0.02101   0.0105   0.0090   1.0000
   9.750   0.9769   0.02645   0.02239   0.0114   0.0087   1.0000
  10.000   0.9915   0.02836   0.02454   0.0127   0.0085   1.0000
  10.250   1.0001   0.03112   0.02761   0.0143   0.0083   1.0000
  10.500   1.0001   0.03495   0.03182   0.0165   0.0081   1.0000
  10.750   0.9844   0.04043   0.03775   0.0193   0.0080   1.0000
  11.000   0.9490   0.04671   0.04441   0.0226   0.0080   1.0000
  11.250   0.9109   0.05372   0.05171   0.0220   0.0081   1.0000
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