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NACA 64-108 AIRFOIL (n64108-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-108 AIRFOIL (n64108-il)
Reynolds number: 100,000
Max Cl/Cd: 38.97 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n64108-il-100000.txt
Download as CSV file: xf-n64108-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-108 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6104   0.08831   0.08364  -0.0073   1.0000   0.1066
  -8.250  -0.6263   0.08328   0.07869  -0.0137   1.0000   0.1089
  -8.000  -0.6541   0.07892   0.07416  -0.0218   1.0000   0.1108
  -7.500  -0.6513   0.07102   0.06603  -0.0244   1.0000   0.1246
  -7.250  -0.6271   0.06603   0.06135  -0.0212   1.0000   0.1318
  -7.000  -0.6263   0.06177   0.05697  -0.0232   1.0000   0.1420
  -6.750  -0.6194   0.05813   0.05322  -0.0238   1.0000   0.1554
  -6.250  -0.6002   0.05175   0.04668  -0.0234   1.0000   0.1961
  -6.000  -0.5865   0.04944   0.04453  -0.0209   1.0000   0.2273
  -5.500  -0.5312   0.03583   0.02864  -0.0261   1.0000   0.1089
  -5.250  -0.4998   0.03139   0.02288  -0.0236   1.0000   0.0708
  -5.000  -0.4766   0.02757   0.01890  -0.0230   1.0000   0.0677
  -4.750  -0.4521   0.02501   0.01600  -0.0219   1.0000   0.0660
  -4.500  -0.4274   0.02323   0.01390  -0.0208   1.0000   0.0682
  -4.250  -0.4030   0.02169   0.01208  -0.0196   1.0000   0.0712
  -4.000  -0.3797   0.01966   0.01009  -0.0185   1.0000   0.0736
  -3.750  -0.3575   0.01830   0.00874  -0.0172   1.0000   0.0780
  -3.500  -0.3368   0.01711   0.00758  -0.0157   1.0000   0.0859
  -3.250  -0.3176   0.01602   0.00660  -0.0143   1.0000   0.1003
  -3.000  -0.2982   0.01487   0.00557  -0.0128   1.0000   0.1271
  -2.750  -0.2983   0.01178   0.00539  -0.0072   1.0000   0.6932
  -2.500  -0.2915   0.01192   0.00569  -0.0012   1.0000   0.7827
  -2.250  -0.2869   0.01212   0.00595   0.0052   1.0000   0.8400
  -2.000  -0.2842   0.01236   0.00619   0.0125   1.0000   0.8966
  -1.750  -0.1848   0.01323   0.00670   0.0036   1.0000   0.9632
  -1.500  -0.1257   0.01303   0.00626  -0.0033   1.0000   0.9748
  -1.250  -0.0720   0.01277   0.00581  -0.0094   1.0000   0.9864
  -1.000  -0.0183   0.01249   0.00541  -0.0156   1.0000   0.9984
  -0.750  -0.0318   0.01239   0.00532  -0.0108   1.0000   1.0000
  -0.500  -0.0609   0.01223   0.00517  -0.0035   1.0000   1.0000
  -0.250  -0.0668   0.01218   0.00505   0.0003   1.0000   1.0000
   0.000  -0.0526   0.01232   0.00510   0.0011   0.9996   1.0000
   0.250  -0.0052   0.01268   0.00539  -0.0040   0.9900   1.0000
   0.500   0.0422   0.01306   0.00573  -0.0089   0.9810   1.0000
   0.750   0.0875   0.01337   0.00604  -0.0133   0.9712   1.0000
   1.000   0.1304   0.01367   0.00637  -0.0172   0.9609   1.0000
   1.250   0.1749   0.01395   0.00671  -0.0212   0.9516   1.0000
   1.500   0.2220   0.01420   0.00705  -0.0256   0.9426   1.0000
   1.750   0.2627   0.01443   0.00742  -0.0287   0.9317   1.0000
   2.000   0.3070   0.01461   0.00774  -0.0323   0.9209   1.0000
   2.250   0.3508   0.01472   0.00804  -0.0354   0.9091   1.0000
   2.500   0.3909   0.01478   0.00834  -0.0375   0.8954   1.0000
   2.750   0.4306   0.01346   0.00715  -0.0345   0.8472   1.0000
   3.000   0.4435   0.01268   0.00632  -0.0278   0.7930   1.0000
   3.250   0.4612   0.01239   0.00604  -0.0238   0.7473   1.0000
   3.500   0.4746   0.01218   0.00559  -0.0184   0.6361   1.0000
   3.750   0.4709   0.01574   0.00623  -0.0126   0.1267   1.0000
   4.000   0.4910   0.01717   0.00753  -0.0113   0.0960   1.0000
   4.250   0.5122   0.01853   0.00880  -0.0101   0.0827   1.0000
   4.500   0.5362   0.01994   0.01016  -0.0091   0.0757   1.0000
   4.750   0.5617   0.02203   0.01214  -0.0084   0.0713   1.0000
   5.000   0.5885   0.02332   0.01366  -0.0077   0.0651   1.0000
   5.250   0.6159   0.02539   0.01596  -0.0070   0.0637   1.0000
   5.500   0.6430   0.02788   0.01884  -0.0061   0.0644   1.0000
   5.750   0.6689   0.03098   0.02241  -0.0051   0.0676   1.0000
   6.000   0.6925   0.03465   0.02641  -0.0042   0.0704   1.0000
   6.250   0.7139   0.03868   0.03075  -0.0035   0.0715   1.0000
   7.750   0.7760   0.06989   0.06534  -0.0034   0.1467   1.0000
   8.000   0.7926   0.07446   0.06980  -0.0021   0.1384   1.0000
   8.250   0.7668   0.07849   0.07406  -0.0058   0.1322   1.0000
   8.500   0.7843   0.08295   0.07844  -0.0039   0.1247   1.0000
   8.750   0.7542   0.08748   0.08304  -0.0084   0.1234   1.0000
   9.000   0.7321   0.09367   0.08915  -0.0156   0.1210   1.0000
   9.250   0.7667   0.09623   0.09174  -0.0078   0.1116   1.0000
   9.500   0.7424   0.10235   0.09780  -0.0158   0.1112   1.0000
   9.750   0.7214   0.10796   0.10330  -0.0235   0.1080   1.0000
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