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NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-208 (naca64208-il)
Reynolds number: 100,000
Max Cl/Cd: 45.31 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64208-il-100000.txt
Download as CSV file: xf-naca64208-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5514   0.09410   0.08926  -0.0148   1.0000   0.0933
  -8.500  -0.5698   0.08979   0.08508  -0.0225   1.0000   0.0949
  -8.250  -0.5887   0.08553   0.08078  -0.0300   1.0000   0.0954
  -8.000  -0.5543   0.08197   0.07731  -0.0203   1.0000   0.1030
  -7.750  -0.5638   0.07713   0.07251  -0.0265   1.0000   0.1067
  -7.500  -0.5888   0.07390   0.06886  -0.0357   1.0000   0.1094
  -7.250  -0.5097   0.05761   0.05330  -0.0309   1.0000   0.1257
  -7.000  -0.5056   0.05384   0.04951  -0.0311   1.0000   0.1340
  -6.750  -0.5525   0.06099   0.05619  -0.0336   1.0000   0.1331
  -6.500  -0.5450   0.05725   0.05240  -0.0340   1.0000   0.1435
  -6.250  -0.5363   0.05391   0.04896  -0.0342   1.0000   0.1580
  -6.000  -0.5286   0.05089   0.04588  -0.0339   1.0000   0.1822
  -5.750  -0.5186   0.04843   0.04347  -0.0323   1.0000   0.2104
  -5.000  -0.4394   0.03159   0.02388  -0.0353   1.0000   0.0841
  -4.750  -0.4141   0.02831   0.01988  -0.0336   1.0000   0.0700
  -4.500  -0.3910   0.02613   0.01740  -0.0323   1.0000   0.0671
  -4.250  -0.3682   0.02447   0.01535  -0.0310   1.0000   0.0682
  -4.000  -0.3463   0.02201   0.01276  -0.0300   1.0000   0.0711
  -3.750  -0.3235   0.02036   0.01099  -0.0287   1.0000   0.0720
  -3.500  -0.3014   0.01899   0.00954  -0.0273   1.0000   0.0748
  -3.250  -0.2798   0.01792   0.00842  -0.0260   1.0000   0.0801
  -3.000  -0.2594   0.01679   0.00743  -0.0248   1.0000   0.0910
  -2.750  -0.2386   0.01578   0.00647  -0.0237   1.0000   0.1032
  -2.500  -0.2165   0.01462   0.00554  -0.0231   1.0000   0.1460
  -2.250  -0.2154   0.01212   0.00584  -0.0166   1.0000   0.7530
  -2.000  -0.2138   0.01229   0.00612  -0.0097   1.0000   0.8352
  -1.750  -0.2138   0.01237   0.00627  -0.0026   1.0000   0.8997
  -1.500  -0.0751   0.01282   0.00622  -0.0192   1.0000   0.9971
  -1.250  -0.0864   0.01258   0.00596  -0.0150   1.0000   1.0000
  -1.000  -0.1013   0.01234   0.00566  -0.0101   1.0000   1.0000
  -0.750  -0.0884   0.01235   0.00553  -0.0094   1.0000   1.0000
  -0.500  -0.0685   0.01250   0.00553  -0.0096   1.0000   1.0000
  -0.250  -0.0270   0.01286   0.00575  -0.0136   0.9934   1.0000
   0.000   0.0187   0.01323   0.00601  -0.0182   0.9845   1.0000
   0.250   0.0618   0.01357   0.00625  -0.0223   0.9752   1.0000
   0.500   0.1071   0.01392   0.00655  -0.0266   0.9670   1.0000
   0.750   0.1491   0.01422   0.00683  -0.0302   0.9576   1.0000
   1.000   0.1888   0.01450   0.00712  -0.0332   0.9476   1.0000
   1.250   0.2340   0.01478   0.00743  -0.0372   0.9399   1.0000
   1.500   0.2731   0.01502   0.00773  -0.0400   0.9299   1.0000
   1.750   0.3110   0.01527   0.00808  -0.0425   0.9199   1.0000
   2.000   0.3599   0.01541   0.00836  -0.0468   0.9127   1.0000
   2.250   0.3978   0.01556   0.00864  -0.0488   0.9012   1.0000
   2.500   0.4336   0.01569   0.00893  -0.0503   0.8891   1.0000
   2.750   0.4695   0.01575   0.00921  -0.0515   0.8762   1.0000
   3.000   0.5122   0.01449   0.00812  -0.0501   0.8428   1.0000
   3.250   0.5314   0.01322   0.00680  -0.0436   0.7875   1.0000
   3.500   0.5518   0.01288   0.00654  -0.0402   0.7440   1.0000
   3.750   0.5695   0.01257   0.00613  -0.0358   0.6611   1.0000
   4.000   0.5627   0.01584   0.00646  -0.0288   0.1424   1.0000
   4.250   0.5808   0.01759   0.00786  -0.0273   0.0992   1.0000
   4.500   0.6011   0.01907   0.00923  -0.0259   0.0839   1.0000
   4.750   0.6250   0.02046   0.01064  -0.0249   0.0764   1.0000
   5.000   0.6504   0.02254   0.01257  -0.0243   0.0706   1.0000
   5.250   0.6775   0.02394   0.01420  -0.0237   0.0647   1.0000
   5.500   0.7056   0.02606   0.01648  -0.0231   0.0629   1.0000
   5.750   0.7333   0.02855   0.01930  -0.0223   0.0630   1.0000
   6.000   0.7598   0.03164   0.02291  -0.0212   0.0656   1.0000
   6.250   0.7834   0.03476   0.02650  -0.0201   0.0664   1.0000
   6.500   0.8049   0.03830   0.03050  -0.0189   0.0677   1.0000
  10.750   0.6923   0.12340   0.11921  -0.0312   0.1113   1.0000
  11.000   0.6655   0.12821   0.12396  -0.0373   0.1101   1.0000
  11.250   0.6525   0.13234   0.12806  -0.0410   0.1055   1.0000
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