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NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-209 (naca64209-il)
Reynolds number: 100,000
Max Cl/Cd: 43.43 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64209-il-100000-n5.txt
Download as CSV file: xf-naca64209-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4515   0.11341   0.10860  -0.0102   1.0000   0.0421
 -10.750  -0.4517   0.10921   0.10441  -0.0118   1.0000   0.0424
 -10.500  -0.5618   0.10771   0.10257  -0.0126   1.0000   0.0266
 -10.250  -0.5584   0.10377   0.09864  -0.0132   1.0000   0.0260
 -10.000  -0.5563   0.09969   0.09459  -0.0147   1.0000   0.0254
  -9.750  -0.5571   0.09487   0.08981  -0.0171   1.0000   0.0252
  -9.500  -0.5601   0.08930   0.08429  -0.0207   1.0000   0.0255
  -9.250  -0.5627   0.08395   0.07899  -0.0242   1.0000   0.0253
  -9.000  -0.5668   0.07834   0.07342  -0.0283   1.0000   0.0245
  -8.750  -0.5776   0.07227   0.06737  -0.0334   1.0000   0.0246
  -8.500  -0.5895   0.06756   0.06262  -0.0359   1.0000   0.0243
  -8.250  -0.5965   0.06284   0.05777  -0.0378   1.0000   0.0242
  -8.000  -0.6001   0.05823   0.05296  -0.0389   1.0000   0.0248
  -7.750  -0.6001   0.05370   0.04816  -0.0394   1.0000   0.0252
  -7.500  -0.5965   0.04933   0.04343  -0.0393   1.0000   0.0256
  -7.250  -0.5893   0.04522   0.03894  -0.0388   1.0000   0.0257
  -7.000  -0.5788   0.04148   0.03478  -0.0380   1.0000   0.0259
  -6.750  -0.5659   0.03806   0.03085  -0.0369   1.0000   0.0263
  -6.500  -0.5505   0.03536   0.02756  -0.0356   1.0000   0.0269
  -6.250  -0.5357   0.03198   0.02397  -0.0348   1.0000   0.0281
  -6.000  -0.5181   0.03029   0.02222  -0.0341   1.0000   0.0306
  -5.750  -0.4992   0.02836   0.01995  -0.0329   1.0000   0.0328
  -5.500  -0.4792   0.02627   0.01742  -0.0316   1.0000   0.0344
  -5.250  -0.4585   0.02462   0.01538  -0.0301   1.0000   0.0362
  -5.000  -0.4390   0.02243   0.01307  -0.0289   1.0000   0.0386
  -4.750  -0.4197   0.02120   0.01179  -0.0277   1.0000   0.0424
  -4.500  -0.4001   0.02034   0.01079  -0.0264   1.0000   0.0464
  -4.250  -0.3814   0.01942   0.00986  -0.0253   1.0000   0.0505
  -4.000  -0.3506   0.01860   0.00897  -0.0264   0.9950   0.0529
  -3.750  -0.3156   0.01797   0.00826  -0.0283   0.9879   0.0565
  -3.500  -0.2807   0.01739   0.00758  -0.0301   0.9807   0.0583
  -3.250  -0.2446   0.01686   0.00694  -0.0322   0.9740   0.0587
  -3.000  -0.2097   0.01640   0.00636  -0.0340   0.9663   0.0593
  -2.750  -0.1739   0.01599   0.00586  -0.0359   0.9592   0.0605
  -2.500  -0.1380   0.01567   0.00546  -0.0377   0.9520   0.0622
  -2.250  -0.1043   0.01540   0.00513  -0.0391   0.9436   0.0649
  -2.000  -0.0687   0.01515   0.00482  -0.0408   0.9364   0.0707
  -1.750  -0.0376   0.01470   0.00456  -0.0418   0.9270   0.1093
  -1.500  -0.0152   0.01268   0.00462  -0.0417   0.9187   0.6019
  -1.250   0.0132   0.01257   0.00467  -0.0414   0.9095   0.6657
  -1.000   0.0410   0.01254   0.00470  -0.0410   0.8998   0.7067
  -0.750   0.0696   0.01252   0.00475  -0.0406   0.8915   0.7447
  -0.500   0.0975   0.01253   0.00474  -0.0404   0.8814   0.7615
  -0.250   0.1250   0.01255   0.00474  -0.0401   0.8718   0.7796
   0.000   0.1531   0.01255   0.00475  -0.0397   0.8635   0.7986
   0.250   0.1777   0.01258   0.00483  -0.0387   0.8531   0.8220
   0.500   0.1997   0.01260   0.00496  -0.0367   0.8435   0.8578
   0.750   0.2262   0.01260   0.00499  -0.0360   0.8353   0.8790
   1.000   0.2512   0.01261   0.00508  -0.0349   0.8253   0.9071
   1.250   0.2868   0.01255   0.00512  -0.0357   0.8176   0.9478
   1.500   0.3279   0.01253   0.00517  -0.0384   0.8091   0.9681
   1.750   0.3662   0.01255   0.00525  -0.0407   0.8000   0.9822
   2.000   0.4041   0.01255   0.00532  -0.0429   0.7919   0.9997
   2.250   0.4256   0.01269   0.00552  -0.0420   0.7808   1.0000
   2.500   0.4490   0.01281   0.00570  -0.0413   0.7695   1.0000
   2.750   0.4735   0.01292   0.00586  -0.0406   0.7577   1.0000
   3.000   0.4984   0.01301   0.00603  -0.0399   0.7437   1.0000
   3.250   0.5203   0.01287   0.00587  -0.0378   0.7085   1.0000
   3.500   0.5390   0.01272   0.00545  -0.0348   0.6357   1.0000
   3.750   0.5600   0.01291   0.00539  -0.0329   0.5611   1.0000
   4.000   0.5807   0.01337   0.00552  -0.0313   0.4590   1.0000
   4.250   0.5888   0.01560   0.00617  -0.0288   0.1743   1.0000
   4.500   0.6064   0.01716   0.00714  -0.0277   0.0819   1.0000
   4.750   0.6278   0.01817   0.00807  -0.0269   0.0634   1.0000
   5.000   0.6502   0.01902   0.00895  -0.0262   0.0528   1.0000
   5.250   0.6710   0.02011   0.01009  -0.0252   0.0480   1.0000
   5.500   0.6928   0.02112   0.01122  -0.0243   0.0438   1.0000
   5.750   0.7146   0.02218   0.01231  -0.0236   0.0391   1.0000
   6.000   0.7359   0.02378   0.01390  -0.0228   0.0363   1.0000
   6.250   0.7603   0.02521   0.01548  -0.0222   0.0349   1.0000
   6.500   0.7855   0.02690   0.01736  -0.0216   0.0335   1.0000
   6.750   0.8108   0.02884   0.01953  -0.0211   0.0323   1.0000
   7.000   0.8352   0.03097   0.02194  -0.0205   0.0311   1.0000
   7.250   0.8572   0.03274   0.02395  -0.0199   0.0289   1.0000
   7.500   0.8774   0.03472   0.02612  -0.0194   0.0270   1.0000
   7.750   0.8957   0.03777   0.02951  -0.0186   0.0262   1.0000
   8.000   0.9099   0.04172   0.03388  -0.0175   0.0257   1.0000
   8.250   0.9210   0.04545   0.03805  -0.0161   0.0254   1.0000
   8.500   0.9296   0.04900   0.04208  -0.0146   0.0252   1.0000
   8.750   0.9346   0.05246   0.04601  -0.0130   0.0248   1.0000
   9.000   0.9349   0.05611   0.05012  -0.0113   0.0241   1.0000
   9.250   0.9301   0.06006   0.05446  -0.0097   0.0234   1.0000
   9.500   0.9207   0.06412   0.05880  -0.0084   0.0231   1.0000
   9.750   0.9049   0.06795   0.06283  -0.0070   0.0230   1.0000
  10.000   0.8874   0.07218   0.06722  -0.0071   0.0231   1.0000
  10.250   0.8681   0.07726   0.07244  -0.0089   0.0231   1.0000
  10.500   0.8498   0.08323   0.07851  -0.0123   0.0235   1.0000
  10.750   0.8317   0.09054   0.08590  -0.0174   0.0237   1.0000
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