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NACA 63A010 AIRFOIL (n63010a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 63A010 AIRFOIL (n63010a-il)
Reynolds number: 100,000
Max Cl/Cd: 34.85 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n63010a-il-100000-n5.txt
Download as CSV file: xf-n63010a-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.7288   0.08578   0.08081  -0.0110   1.0000   0.0257
 -10.500  -0.7457   0.07845   0.07340  -0.0165   1.0000   0.0255
 -10.250  -0.7640   0.07232   0.06717  -0.0206   1.0000   0.0253
 -10.000  -0.7821   0.06732   0.06202  -0.0227   1.0000   0.0252
  -9.750  -0.7988   0.06311   0.05764  -0.0227   1.0000   0.0251
  -9.500  -0.8113   0.05904   0.05333  -0.0218   1.0000   0.0250
  -9.250  -0.8185   0.05488   0.04887  -0.0207   1.0000   0.0250
  -9.000  -0.8210   0.05084   0.04445  -0.0194   1.0000   0.0251
  -8.750  -0.8190   0.04699   0.04018  -0.0179   1.0000   0.0253
  -8.500  -0.8125   0.04365   0.03634  -0.0162   1.0000   0.0260
  -8.250  -0.8035   0.04048   0.03270  -0.0147   1.0000   0.0270
  -8.000  -0.7904   0.03759   0.02958  -0.0137   1.0000   0.0281
  -7.750  -0.7740   0.03512   0.02677  -0.0126   1.0000   0.0288
  -7.500  -0.7556   0.03276   0.02409  -0.0115   1.0000   0.0294
  -7.250  -0.7354   0.03064   0.02168  -0.0105   1.0000   0.0302
  -7.000  -0.7138   0.02871   0.01951  -0.0096   1.0000   0.0312
  -6.750  -0.6915   0.02701   0.01760  -0.0087   1.0000   0.0326
  -6.500  -0.6688   0.02571   0.01609  -0.0078   1.0000   0.0351
  -6.250  -0.6459   0.02447   0.01464  -0.0069   1.0000   0.0370
  -6.000  -0.6257   0.02278   0.01297  -0.0058   1.0000   0.0388
  -5.750  -0.6056   0.02163   0.01181  -0.0046   1.0000   0.0411
  -5.500  -0.5858   0.02062   0.01073  -0.0033   1.0000   0.0442
  -5.250  -0.5658   0.01977   0.00975  -0.0020   1.0000   0.0483
  -5.000  -0.5473   0.01883   0.00885  -0.0006   1.0000   0.0560
  -4.750  -0.5282   0.01797   0.00796   0.0008   1.0000   0.0663
  -4.500  -0.5094   0.01711   0.00719   0.0022   1.0000   0.0882
  -4.250  -0.4928   0.01591   0.00643   0.0036   1.0000   0.1523
  -4.000  -0.4810   0.01421   0.00579   0.0055   1.0000   0.3417
  -3.750  -0.4657   0.01336   0.00564   0.0077   1.0000   0.4921
  -3.500  -0.4473   0.01303   0.00559   0.0097   1.0000   0.5786
  -3.250  -0.4282   0.01289   0.00562   0.0117   1.0000   0.6391
  -3.000  -0.4094   0.01286   0.00569   0.0139   1.0000   0.6896
  -2.750  -0.3901   0.01288   0.00578   0.0159   0.9997   0.7293
  -2.500  -0.3548   0.01293   0.00577   0.0147   0.9907   0.7590
  -2.250  -0.3183   0.01294   0.00571   0.0130   0.9819   0.7781
  -2.000  -0.2807   0.01294   0.00562   0.0110   0.9735   0.7931
  -1.750  -0.2437   0.01292   0.00551   0.0091   0.9644   0.8069
  -1.500  -0.2084   0.01290   0.00542   0.0076   0.9544   0.8203
  -1.250  -0.1727   0.01288   0.00536   0.0060   0.9449   0.8333
  -1.000  -0.1363   0.01287   0.00531   0.0044   0.9356   0.8451
  -0.750  -0.1024   0.01286   0.00528   0.0033   0.9246   0.8570
  -0.500  -0.0681   0.01285   0.00525   0.0022   0.9138   0.8688
  -0.250  -0.0337   0.01284   0.00523   0.0010   0.9033   0.8805
   0.000   0.0000   0.01284   0.00521   0.0000   0.8925   0.8924
   0.250   0.0337   0.01284   0.00522  -0.0010   0.8805   0.9033
   0.500   0.0681   0.01285   0.00525  -0.0022   0.8688   0.9138
   0.750   0.1024   0.01286   0.00528  -0.0033   0.8570   0.9246
   1.000   0.1363   0.01287   0.00531  -0.0044   0.8451   0.9356
   1.250   0.1726   0.01288   0.00536  -0.0060   0.8333   0.9449
   1.500   0.2084   0.01290   0.00542  -0.0076   0.8203   0.9545
   1.750   0.2437   0.01292   0.00551  -0.0091   0.8069   0.9644
   2.000   0.2807   0.01294   0.00562  -0.0110   0.7931   0.9735
   2.250   0.3183   0.01294   0.00571  -0.0130   0.7781   0.9819
   2.500   0.3547   0.01293   0.00577  -0.0147   0.7590   0.9907
   2.750   0.3900   0.01288   0.00578  -0.0159   0.7293   0.9997
   3.000   0.4093   0.01286   0.00569  -0.0139   0.6897   1.0000
   3.250   0.4281   0.01289   0.00562  -0.0117   0.6392   1.0000
   3.500   0.4472   0.01303   0.00559  -0.0097   0.5787   1.0000
   3.750   0.4656   0.01336   0.00564  -0.0077   0.4924   1.0000
   4.000   0.4809   0.01420   0.00579  -0.0055   0.3421   1.0000
   4.250   0.4928   0.01591   0.00643  -0.0036   0.1524   1.0000
   4.500   0.5093   0.01711   0.00719  -0.0021   0.0882   1.0000
   4.750   0.5282   0.01797   0.00796  -0.0008   0.0663   1.0000
   5.000   0.5472   0.01882   0.00885   0.0006   0.0560   1.0000
   5.250   0.5658   0.01977   0.00975   0.0020   0.0484   1.0000
   5.500   0.5858   0.02062   0.01073   0.0033   0.0442   1.0000
   5.750   0.6056   0.02163   0.01181   0.0046   0.0411   1.0000
   6.000   0.6257   0.02278   0.01297   0.0058   0.0388   1.0000
   6.250   0.6459   0.02447   0.01464   0.0069   0.0370   1.0000
   6.500   0.6688   0.02571   0.01609   0.0078   0.0351   1.0000
   6.750   0.6915   0.02701   0.01760   0.0087   0.0326   1.0000
   7.000   0.7139   0.02871   0.01951   0.0096   0.0312   1.0000
   7.250   0.7354   0.03064   0.02168   0.0105   0.0302   1.0000
   7.500   0.7557   0.03276   0.02410   0.0115   0.0294   1.0000
   7.750   0.7741   0.03512   0.02677   0.0126   0.0288   1.0000
   8.000   0.7904   0.03759   0.02959   0.0137   0.0281   1.0000
   8.250   0.8036   0.04048   0.03269   0.0147   0.0270   1.0000
   8.500   0.8125   0.04365   0.03634   0.0162   0.0260   1.0000
   8.750   0.8191   0.04699   0.04018   0.0178   0.0253   1.0000
   9.000   0.8211   0.05084   0.04446   0.0193   0.0251   1.0000
   9.250   0.8187   0.05489   0.04888   0.0207   0.0250   1.0000
   9.500   0.8115   0.05905   0.05334   0.0217   0.0250   1.0000
   9.750   0.7991   0.06313   0.05766   0.0226   0.0251   1.0000
  10.000   0.7824   0.06734   0.06205   0.0226   0.0252   1.0000
  10.250   0.7643   0.07237   0.06722   0.0205   0.0253   1.0000
  10.500   0.7461   0.07851   0.07346   0.0164   0.0255   1.0000
  10.750   0.7293   0.08586   0.08088   0.0108   0.0257   1.0000
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