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NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-208 (naca64208-il)
Reynolds number: 100,000
Max Cl/Cd: 42.79 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64208-il-100000-n5.txt
Download as CSV file: xf-naca64208-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-208                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4604   0.09091   0.08620  -0.0152   1.0000   0.0308
  -9.250  -0.4618   0.08622   0.08154  -0.0166   1.0000   0.0296
  -9.000  -0.5515   0.09173   0.08678  -0.0153   1.0000   0.0307
  -8.750  -0.5518   0.08720   0.08230  -0.0174   1.0000   0.0292
  -8.500  -0.5544   0.08218   0.07733  -0.0207   1.0000   0.0280
  -8.250  -0.5598   0.07672   0.07194  -0.0253   1.0000   0.0271
  -8.000  -0.5672   0.07100   0.06621  -0.0301   1.0000   0.0261
  -7.750  -0.5718   0.06506   0.06016  -0.0338   1.0000   0.0248
  -7.500  -0.5756   0.05769   0.05242  -0.0370   1.0000   0.0228
  -7.250  -0.5677   0.05339   0.04782  -0.0375   1.0000   0.0222
  -7.000  -0.5580   0.04949   0.04361  -0.0376   1.0000   0.0220
  -6.750  -0.5470   0.04555   0.03934  -0.0375   1.0000   0.0220
  -6.500  -0.5367   0.04105   0.03449  -0.0373   1.0000   0.0224
  -6.250  -0.5230   0.03842   0.03177  -0.0373   1.0000   0.0244
  -6.000  -0.5059   0.03607   0.02917  -0.0368   1.0000   0.0265
  -5.750  -0.4878   0.03289   0.02555  -0.0359   1.0000   0.0270
  -5.500  -0.4681   0.02993   0.02213  -0.0349   1.0000   0.0274
  -5.250  -0.4472   0.02739   0.01914  -0.0339   1.0000   0.0281
  -5.000  -0.4253   0.02526   0.01658  -0.0328   1.0000   0.0294
  -4.750  -0.4028   0.02396   0.01490  -0.0316   1.0000   0.0326
  -4.500  -0.3806   0.02243   0.01310  -0.0305   1.0000   0.0337
  -4.250  -0.3595   0.02046   0.01103  -0.0293   1.0000   0.0351
  -4.000  -0.3387   0.01915   0.00969  -0.0282   1.0000   0.0370
  -3.750  -0.3181   0.01814   0.00865  -0.0270   1.0000   0.0395
  -3.500  -0.2974   0.01744   0.00785  -0.0259   1.0000   0.0449
  -3.250  -0.2771   0.01658   0.00693  -0.0250   1.0000   0.0500
  -3.000  -0.2493   0.01588   0.00613  -0.0254   0.9968   0.0570
  -2.750  -0.2137   0.01511   0.00538  -0.0275   0.9897   0.0774
  -2.500  -0.1815   0.01317   0.00461  -0.0298   0.9835   0.3203
  -2.250  -0.1557   0.01209   0.00486  -0.0292   0.9763   0.6621
  -2.000  -0.1327   0.01208   0.00520  -0.0267   0.9670   0.7764
  -1.750  -0.1106   0.01220   0.00539  -0.0240   0.9574   0.8418
  -1.500  -0.0763   0.01217   0.00523  -0.0250   0.9504   0.8598
  -1.250  -0.0433   0.01212   0.00503  -0.0260   0.9416   0.8740
  -1.000  -0.0096   0.01206   0.00487  -0.0271   0.9332   0.8881
  -0.750   0.0258   0.01201   0.00473  -0.0286   0.9257   0.9022
  -0.500   0.0594   0.01196   0.00462  -0.0297   0.9163   0.9171
  -0.250   0.0967   0.01190   0.00450  -0.0316   0.9088   0.9313
   0.000   0.1346   0.01185   0.00441  -0.0337   0.9001   0.9454
   0.250   0.1745   0.01180   0.00434  -0.0363   0.8916   0.9592
   0.500   0.2163   0.01175   0.00429  -0.0393   0.8839   0.9722
   0.750   0.2565   0.01171   0.00427  -0.0421   0.8740   0.9878
   1.000   0.2907   0.01171   0.00429  -0.0437   0.8637   1.0000
   1.250   0.3161   0.01178   0.00438  -0.0434   0.8527   1.0000
   1.500   0.3422   0.01185   0.00447  -0.0432   0.8420   1.0000
   1.750   0.3676   0.01196   0.00463  -0.0429   0.8303   1.0000
   2.000   0.3936   0.01209   0.00481  -0.0426   0.8192   1.0000
   2.250   0.4201   0.01221   0.00504  -0.0424   0.8079   1.0000
   2.500   0.4463   0.01231   0.00523  -0.0419   0.7949   1.0000
   2.750   0.4721   0.01241   0.00543  -0.0413   0.7798   1.0000
   3.000   0.4937   0.01225   0.00523  -0.0388   0.7371   1.0000
   3.250   0.5117   0.01218   0.00480  -0.0352   0.6471   1.0000
   3.500   0.5332   0.01246   0.00487  -0.0334   0.5635   1.0000
   3.750   0.5488   0.01354   0.00500  -0.0309   0.3526   1.0000
   4.000   0.5602   0.01605   0.00600  -0.0293   0.0944   1.0000
   4.250   0.5820   0.01716   0.00695  -0.0285   0.0652   1.0000
   4.500   0.6046   0.01809   0.00786  -0.0279   0.0514   1.0000
   4.750   0.6276   0.01898   0.00896  -0.0271   0.0456   1.0000
   5.000   0.6495   0.02008   0.01012  -0.0262   0.0416   1.0000
   5.250   0.6704   0.02171   0.01173  -0.0252   0.0389   1.0000
   5.500   0.6950   0.02282   0.01301  -0.0246   0.0357   1.0000
   5.750   0.7196   0.02414   0.01447  -0.0240   0.0323   1.0000
   6.000   0.7445   0.02586   0.01633  -0.0235   0.0306   1.0000
   6.250   0.7693   0.02787   0.01852  -0.0229   0.0292   1.0000
   6.500   0.7932   0.03036   0.02132  -0.0224   0.0282   1.0000
   7.000   0.8353   0.03583   0.02769  -0.0205   0.0251   1.0000
   7.250   0.8535   0.03893   0.03132  -0.0193   0.0240   1.0000
   7.500   0.8681   0.04264   0.03556  -0.0179   0.0235   1.0000
   7.750   0.8791   0.04670   0.04012  -0.0165   0.0233   1.0000
   8.000   0.8864   0.05105   0.04492  -0.0151   0.0232   1.0000
   8.250   0.8899   0.05551   0.04979  -0.0139   0.0231   1.0000
   8.500   0.8896   0.05997   0.05458  -0.0129   0.0228   1.0000
   8.750   0.8853   0.06439   0.05928  -0.0122   0.0223   1.0000
   9.000   0.8763   0.06877   0.06389  -0.0118   0.0219   1.0000
   9.250   0.8611   0.07303   0.06829  -0.0114   0.0221   1.0000
   9.500   0.8435   0.07796   0.07333  -0.0129   0.0224   1.0000
   9.750   0.8269   0.08386   0.07930  -0.0164   0.0230   1.0000
  10.000   0.8128   0.09096   0.08644  -0.0216   0.0235   1.0000
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