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NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-209 (naca65209-il)
Reynolds number: 200,000
Max Cl/Cd: 59.33 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65209-il-200000.txt
Download as CSV file: xf-naca65209-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-209                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5310   0.08901   0.08548  -0.0262   1.0000   0.0389
  -9.000  -0.5316   0.08489   0.08140  -0.0284   1.0000   0.0401
  -8.750  -0.5350   0.08024   0.07679  -0.0317   1.0000   0.0405
  -8.500  -0.5446   0.07489   0.07148  -0.0366   1.0000   0.0407
  -8.250  -0.5571   0.07062   0.06719  -0.0390   1.0000   0.0412
  -8.000  -0.5631   0.06648   0.06299  -0.0405   1.0000   0.0418
  -7.750  -0.5662   0.06256   0.05898  -0.0414   1.0000   0.0430
  -7.500  -0.5675   0.05877   0.05501  -0.0416   1.0000   0.0451
  -7.250  -0.5689   0.05816   0.05384  -0.0400   1.0000   0.0476
  -7.000  -0.5734   0.05310   0.04855  -0.0385   1.0000   0.0483
  -6.750  -0.5682   0.04784   0.04346  -0.0376   1.0000   0.0500
  -6.500  -0.5620   0.04538   0.04100  -0.0356   1.0000   0.0516
  -6.250  -0.5569   0.04318   0.03870  -0.0333   1.0000   0.0540
  -6.000  -0.5494   0.04502   0.03982  -0.0292   1.0000   0.0609
  -5.750  -0.5470   0.03827   0.03317  -0.0283   1.0000   0.0634
  -5.500  -0.5367   0.03610   0.03101  -0.0267   1.0000   0.0667
  -5.250  -0.5265   0.03430   0.02877  -0.0247   1.0000   0.0766
  -5.000  -0.4952   0.03156   0.02592  -0.0274   0.9962   0.0914
  -4.500  -0.4162   0.02271   0.01556  -0.0277   0.9897   0.0443
  -4.250  -0.3801   0.02027   0.01277  -0.0290   0.9863   0.0426
  -4.000  -0.3415   0.01897   0.01123  -0.0310   0.9832   0.0454
  -3.750  -0.3079   0.01752   0.00962  -0.0319   0.9784   0.0460
  -3.500  -0.2721   0.01645   0.00844  -0.0335   0.9740   0.0474
  -3.250  -0.2364   0.01496   0.00702  -0.0355   0.9707   0.0528
  -3.000  -0.2027   0.01424   0.00628  -0.0370   0.9652   0.0589
  -2.750  -0.1673   0.01340   0.00543  -0.0389   0.9600   0.0686
  -2.500  -0.1355   0.01089   0.00451  -0.0415   0.9566   0.4377
  -2.250  -0.1145   0.01027   0.00494  -0.0393   0.9496   0.7298
  -2.000  -0.0854   0.01047   0.00530  -0.0383   0.9445   0.7957
  -1.750  -0.0604   0.01076   0.00563  -0.0364   0.9388   0.8353
  -1.500  -0.0387   0.01099   0.00585  -0.0338   0.9317   0.8624
  -1.250  -0.0098   0.01110   0.00594  -0.0330   0.9277   0.8805
  -1.000   0.0146   0.01107   0.00586  -0.0323   0.9191   0.8902
  -0.750   0.0473   0.01101   0.00574  -0.0331   0.9146   0.8981
  -0.500   0.0723   0.01099   0.00568  -0.0324   0.9068   0.9070
  -0.250   0.1023   0.01092   0.00556  -0.0328   0.9014   0.9162
   0.000   0.1295   0.01089   0.00553  -0.0326   0.8944   0.9246
   0.250   0.1595   0.01083   0.00545  -0.0329   0.8885   0.9332
   0.500   0.1889   0.01079   0.00541  -0.0332   0.8824   0.9428
   0.750   0.2239   0.01075   0.00538  -0.0347   0.8761   0.9497
   1.000   0.2591   0.01068   0.00531  -0.0361   0.8716   0.9576
   1.250   0.2977   0.01068   0.00537  -0.0386   0.8644   0.9638
   1.500   0.3355   0.01062   0.00535  -0.0407   0.8590   0.9708
   1.750   0.3777   0.01060   0.00541  -0.0440   0.8522   0.9756
   2.000   0.4170   0.01048   0.00535  -0.0463   0.8446   0.9819
   2.250   0.4553   0.01015   0.00506  -0.0478   0.8280   0.9874
   2.500   0.4887   0.00964   0.00453  -0.0478   0.7963   0.9950
   2.750   0.5146   0.00924   0.00403  -0.0465   0.7525   1.0000
   3.000   0.5299   0.00915   0.00389  -0.0438   0.7190   1.0000
   3.250   0.5429   0.00915   0.00376  -0.0406   0.6621   1.0000
   3.500   0.5440   0.00992   0.00361  -0.0351   0.4522   1.0000
   3.750   0.5348   0.01294   0.00467  -0.0299   0.0841   1.0000
   4.000   0.5548   0.01384   0.00547  -0.0287   0.0614   1.0000
   4.250   0.5751   0.01479   0.00641  -0.0276   0.0532   1.0000
   4.500   0.5964   0.01575   0.00741  -0.0266   0.0496   1.0000
   4.750   0.6189   0.01675   0.00847  -0.0257   0.0466   1.0000
   5.000   0.6421   0.01778   0.00946  -0.0251   0.0427   1.0000
   5.250   0.6661   0.01997   0.01161  -0.0245   0.0402   1.0000
   5.500   0.6933   0.02178   0.01354  -0.0242   0.0395   1.0000
   5.750   0.7207   0.02380   0.01574  -0.0238   0.0393   1.0000
   6.000   0.7478   0.02711   0.01927  -0.0235   0.0400   1.0000
  10.000   0.7142   0.08323   0.08019  -0.0054   0.0505   1.0000
  10.250   0.6966   0.09044   0.08744  -0.0093   0.0508   1.0000
  10.500   0.6805   0.09873   0.09573  -0.0147   0.0509   1.0000
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