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NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-209 (naca64209-il)
Reynolds number: 200,000
Max Cl/Cd: 53.84 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64209-il-200000-n5.txt
Download as CSV file: xf-naca64209-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-209                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5732   0.08411   0.08057  -0.0207   1.0000   0.0141
  -9.250  -0.5803   0.07775   0.07427  -0.0252   1.0000   0.0139
  -9.000  -0.5952   0.06946   0.06601  -0.0329   1.0000   0.0135
  -8.750  -0.6154   0.06342   0.05994  -0.0368   1.0000   0.0133
  -8.500  -0.6301   0.05698   0.05331  -0.0391   1.0000   0.0131
  -8.250  -0.6395   0.05042   0.04647  -0.0400   1.0000   0.0129
  -8.000  -0.6392   0.04532   0.04106  -0.0400   1.0000   0.0129
  -7.750  -0.6340   0.04074   0.03616  -0.0395   1.0000   0.0130
  -7.500  -0.6245   0.03686   0.03192  -0.0387   1.0000   0.0133
  -7.250  -0.6122   0.03333   0.02802  -0.0377   1.0000   0.0137
  -7.000  -0.5980   0.03005   0.02431  -0.0365   1.0000   0.0141
  -6.750  -0.5826   0.02653   0.02022  -0.0350   1.0000   0.0156
  -6.500  -0.5634   0.02543   0.01896  -0.0340   1.0000   0.0165
  -6.250  -0.5443   0.02413   0.01746  -0.0329   1.0000   0.0173
  -6.000  -0.5254   0.02241   0.01545  -0.0315   1.0000   0.0184
  -5.750  -0.5010   0.02040   0.01302  -0.0309   0.9980   0.0201
  -5.500  -0.4675   0.01948   0.01199  -0.0326   0.9921   0.0219
  -5.250  -0.4329   0.01871   0.01100  -0.0343   0.9865   0.0254
  -5.000  -0.4003   0.01741   0.00952  -0.0356   0.9804   0.0282
  -4.750  -0.3668   0.01640   0.00850  -0.0373   0.9749   0.0312
  -4.500  -0.3350   0.01573   0.00774  -0.0384   0.9671   0.0334
  -4.250  -0.3020   0.01515   0.00705  -0.0397   0.9600   0.0348
  -4.000  -0.2694   0.01460   0.00644  -0.0410   0.9523   0.0353
  -3.750  -0.2374   0.01428   0.00605  -0.0420   0.9439   0.0366
  -3.500  -0.2059   0.01360   0.00534  -0.0431   0.9360   0.0379
  -3.250  -0.1767   0.01309   0.00478  -0.0437   0.9259   0.0393
  -3.000  -0.1474   0.01269   0.00434  -0.0442   0.9164   0.0412
  -2.750  -0.1179   0.01239   0.00398  -0.0446   0.9072   0.0419
  -2.500  -0.0901   0.01216   0.00369  -0.0446   0.8965   0.0419
  -2.250  -0.0624   0.01196   0.00341  -0.0446   0.8863   0.0419
  -2.000  -0.0347   0.01179   0.00317  -0.0445   0.8766   0.0420
  -1.750  -0.0075   0.01164   0.00296  -0.0443   0.8663   0.0423
  -1.500   0.0196   0.01151   0.00279  -0.0442   0.8561   0.0427
  -1.250   0.0468   0.01140   0.00262  -0.0440   0.8465   0.0433
  -1.000   0.0739   0.01131   0.00249  -0.0438   0.8367   0.0443
  -0.750   0.1011   0.01122   0.00238  -0.0436   0.8265   0.0457
  -0.500   0.1283   0.01115   0.00230  -0.0434   0.8172   0.0482
  -0.250   0.1510   0.00946   0.00214  -0.0437   0.8079   0.4935
   0.000   0.1773   0.00928   0.00218  -0.0433   0.7982   0.5599
   0.250   0.2027   0.00910   0.00228  -0.0427   0.7891   0.6353
   0.500   0.2281   0.00901   0.00239  -0.0420   0.7796   0.6905
   0.750   0.2540   0.00898   0.00249  -0.0414   0.7705   0.7239
   1.000   0.2795   0.00898   0.00259  -0.0406   0.7620   0.7562
   1.250   0.3037   0.00897   0.00274  -0.0395   0.7523   0.7958
   1.500   0.3297   0.00900   0.00285  -0.0390   0.7437   0.8128
   1.750   0.3554   0.00905   0.00295  -0.0383   0.7350   0.8304
   2.000   0.3792   0.00907   0.00307  -0.0371   0.7244   0.8558
   2.250   0.3998   0.00906   0.00320  -0.0350   0.7130   0.8953
   2.500   0.4229   0.00905   0.00326  -0.0335   0.6972   0.9245
   2.750   0.4484   0.00907   0.00317  -0.0326   0.6573   0.9403
   3.000   0.4752   0.00923   0.00306  -0.0320   0.5888   0.9574
   3.250   0.5070   0.00944   0.00315  -0.0329   0.5354   0.9766
   3.500   0.5341   0.00992   0.00327  -0.0331   0.4371   1.0000
   3.750   0.5484   0.01154   0.00380  -0.0316   0.2147   1.0000
   4.000   0.5681   0.01278   0.00441  -0.0310   0.0904   1.0000
   4.250   0.5915   0.01355   0.00496  -0.0306   0.0529   1.0000
   4.500   0.6164   0.01411   0.00555  -0.0304   0.0427   1.0000
   4.750   0.6406   0.01478   0.00623  -0.0300   0.0357   1.0000
   5.000   0.6654   0.01533   0.00685  -0.0296   0.0314   1.0000
   5.250   0.6892   0.01604   0.00761  -0.0292   0.0285   1.0000
   5.500   0.7104   0.01717   0.00879  -0.0284   0.0260   1.0000
   5.750   0.7328   0.01818   0.00988  -0.0277   0.0249   1.0000
   6.000   0.7561   0.01918   0.01096  -0.0270   0.0240   1.0000
   6.250   0.7795   0.02033   0.01221  -0.0264   0.0231   1.0000
   6.500   0.8036   0.02136   0.01337  -0.0259   0.0216   1.0000
   6.750   0.8276   0.02235   0.01446  -0.0255   0.0201   1.0000
   7.000   0.8512   0.02363   0.01586  -0.0250   0.0192   1.0000
   7.250   0.8742   0.02507   0.01744  -0.0245   0.0184   1.0000
   7.500   0.8963   0.02697   0.01953  -0.0239   0.0177   1.0000
   7.750   0.9153   0.03022   0.02309  -0.0231   0.0168   1.0000
   8.000   0.9362   0.03159   0.02482  -0.0222   0.0160   1.0000
   8.250   0.9542   0.03388   0.02751  -0.0211   0.0150   1.0000
   8.500   0.9679   0.03709   0.03117  -0.0196   0.0144   1.0000
   8.750   0.9776   0.04070   0.03523  -0.0180   0.0139   1.0000
   9.000   0.9824   0.04473   0.03969  -0.0161   0.0136   1.0000
   9.250   0.9821   0.04904   0.04439  -0.0142   0.0134   1.0000
   9.500   0.9770   0.05336   0.04905  -0.0123   0.0132   1.0000
   9.750   0.9700   0.05695   0.05291  -0.0107   0.0129   1.0000
  10.000   0.9525   0.06091   0.05708  -0.0085   0.0129   1.0000
  10.250   0.9350   0.06484   0.06116  -0.0078   0.0127   1.0000
  10.500   0.9065   0.07136   0.06788  -0.0095   0.0131   1.0000
  10.750   0.8797   0.07895   0.07562  -0.0138   0.0133   1.0000
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