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NACA 64-110 AIRFOIL (n64110-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-110 AIRFOIL (n64110-il)
Reynolds number: 500,000
Max Cl/Cd: 63.46 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64110-il-500000.txt
Download as CSV file: xf-n64110-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-110 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.7101   0.05867   0.05586  -0.0310   1.0000   0.0232
  -8.750  -0.7148   0.05490   0.05187  -0.0303   1.0000   0.0232
  -8.500  -0.7159   0.05101   0.04772  -0.0294   1.0000   0.0232
  -8.250  -0.7353   0.04110   0.03742  -0.0285   1.0000   0.0241
  -8.000  -0.7432   0.02971   0.02507  -0.0251   1.0000   0.0174
  -7.750  -0.7271   0.02671   0.02174  -0.0239   1.0000   0.0174
  -7.500  -0.7101   0.02380   0.01853  -0.0230   1.0000   0.0178
  -7.250  -0.6884   0.02303   0.01776  -0.0227   1.0000   0.0188
  -7.000  -0.6667   0.02200   0.01665  -0.0220   1.0000   0.0198
  -6.750  -0.6466   0.02010   0.01452  -0.0208   1.0000   0.0201
  -6.500  -0.6274   0.01865   0.01290  -0.0194   1.0000   0.0206
  -6.250  -0.6100   0.01751   0.01164  -0.0176   0.9998   0.0212
  -6.000  -0.5747   0.01624   0.01022  -0.0194   0.9949   0.0220
  -5.750  -0.5386   0.01583   0.00971  -0.0213   0.9893   0.0231
  -5.500  -0.5062   0.01364   0.00743  -0.0228   0.9841   0.0248
  -5.250  -0.4729   0.01278   0.00654  -0.0244   0.9763   0.0263
  -5.000  -0.4383   0.01210   0.00582  -0.0261   0.9692   0.0280
  -4.750  -0.4074   0.01158   0.00525  -0.0269   0.9586   0.0303
  -4.500  -0.3800   0.01104   0.00463  -0.0269   0.9464   0.0328
  -4.250  -0.3554   0.01045   0.00399  -0.0264   0.9338   0.0372
  -4.000  -0.3304   0.01015   0.00361  -0.0257   0.9220   0.0415
  -3.750  -0.3060   0.00973   0.00317  -0.0250   0.9107   0.0509
  -3.500  -0.2818   0.00922   0.00279  -0.0244   0.8996   0.0868
  -3.250  -0.2621   0.00770   0.00222  -0.0239   0.8878   0.3271
  -3.000  -0.2398   0.00684   0.00203  -0.0233   0.8771   0.5136
  -2.750  -0.2140   0.00667   0.00196  -0.0228   0.8676   0.5672
  -2.500  -0.1875   0.00657   0.00190  -0.0224   0.8576   0.6002
  -2.250  -0.1604   0.00651   0.00184  -0.0222   0.8477   0.6237
  -2.000  -0.1334   0.00647   0.00179  -0.0219   0.8384   0.6432
  -1.750  -0.1068   0.00644   0.00180  -0.0215   0.8286   0.6743
  -1.500  -0.0802   0.00643   0.00186  -0.0210   0.8190   0.7034
  -1.250  -0.0529   0.00644   0.00183  -0.0208   0.8103   0.7169
  -1.000  -0.0250   0.00643   0.00179  -0.0207   0.8007   0.7279
  -0.750   0.0027   0.00642   0.00177  -0.0206   0.7915   0.7373
  -0.500   0.0303   0.00642   0.00174  -0.0205   0.7827   0.7458
   0.000   0.0861   0.00642   0.00173  -0.0204   0.7646   0.7643
   0.250   0.1140   0.00642   0.00173  -0.0203   0.7557   0.7735
   0.500   0.1419   0.00644   0.00176  -0.0203   0.7467   0.7831
   0.750   0.1694   0.00646   0.00178  -0.0202   0.7385   0.7922
   1.000   0.1973   0.00647   0.00182  -0.0201   0.7293   0.8020
   1.250   0.2250   0.00650   0.00187  -0.0200   0.7198   0.8121
   1.500   0.2521   0.00653   0.00191  -0.0198   0.7099   0.8213
   1.750   0.2794   0.00655   0.00194  -0.0196   0.6970   0.8311
   2.000   0.3059   0.00656   0.00193  -0.0191   0.6725   0.8416
   2.250   0.3316   0.00659   0.00194  -0.0185   0.6444   0.8515
   2.500   0.3580   0.00665   0.00200  -0.0181   0.6248   0.8619
   2.750   0.3845   0.00672   0.00207  -0.0177   0.6043   0.8728
   3.000   0.4101   0.00681   0.00214  -0.0171   0.5791   0.8834
   3.250   0.4351   0.00693   0.00225  -0.0164   0.5458   0.8944
   3.500   0.4582   0.00722   0.00235  -0.0154   0.4791   0.9064
   3.750   0.4742   0.00845   0.00273  -0.0137   0.2709   0.9204
   4.000   0.4898   0.00980   0.00329  -0.0121   0.0905   0.9363
   4.250   0.5119   0.01035   0.00370  -0.0111   0.0516   0.9532
   4.500   0.5405   0.01078   0.00414  -0.0114   0.0412   0.9697
   4.750   0.5744   0.01151   0.00489  -0.0130   0.0332   0.9854
   5.000   0.6069   0.01194   0.00536  -0.0143   0.0304   1.0000
   5.250   0.6318   0.01247   0.00592  -0.0141   0.0279   1.0000
   5.500   0.6555   0.01324   0.00670  -0.0137   0.0260   1.0000
   5.750   0.6763   0.01456   0.00809  -0.0128   0.0242   1.0000
   6.000   0.7022   0.01501   0.00858  -0.0126   0.0231   1.0000
   6.250   0.7265   0.01580   0.00945  -0.0122   0.0222   1.0000
   6.500   0.7507   0.01672   0.01042  -0.0117   0.0213   1.0000
   6.750   0.7750   0.01770   0.01147  -0.0113   0.0206   1.0000
   7.000   0.7993   0.01874   0.01258  -0.0109   0.0198   1.0000
   7.250   0.8232   0.01993   0.01383  -0.0105   0.0192   1.0000
   7.500   0.8457   0.02188   0.01589  -0.0100   0.0183   1.0000
   7.750   0.8655   0.02507   0.01940  -0.0092   0.0176   1.0000
   8.000   0.8868   0.02672   0.02131  -0.0084   0.0174   1.0000
   8.250   0.9051   0.02927   0.02417  -0.0073   0.0172   1.0000
   8.500   0.9196   0.03247   0.02773  -0.0059   0.0172   1.0000
   8.750   0.9306   0.03727   0.03278  -0.0047   0.0181   1.0000
  11.500   0.7453   0.11065   0.10848  -0.0210   0.0228   1.0000
  11.750   0.7405   0.11759   0.11541  -0.0250   0.0221   1.0000
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