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NACA 64-209 (naca64209-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 64-209 (naca64209-il)
Reynolds number: 500,000
Max Cl/Cd: 75.81 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64209-il-500000.txt
Download as CSV file: xf-naca64209-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5477   0.08636   0.08410  -0.0241   1.0000   0.0218
  -9.250  -0.5516   0.07912   0.07688  -0.0305   1.0000   0.0218
  -9.000  -0.5627   0.07300   0.07073  -0.0361   1.0000   0.0218
  -8.750  -0.5758   0.06893   0.06661  -0.0383   1.0000   0.0218
  -8.500  -0.5869   0.06471   0.06227  -0.0395   1.0000   0.0219
  -8.250  -0.5917   0.06044   0.05786  -0.0402   1.0000   0.0219
  -8.000  -0.5922   0.05632   0.05358  -0.0405   1.0000   0.0219
  -7.750  -0.5903   0.05208   0.04913  -0.0404   1.0000   0.0219
  -7.500  -0.6156   0.03747   0.03404  -0.0396   1.0000   0.0156
  -7.250  -0.6083   0.03324   0.02951  -0.0384   1.0000   0.0152
  -7.000  -0.5991   0.02898   0.02486  -0.0367   1.0000   0.0149
  -6.750  -0.5881   0.02509   0.02050  -0.0345   1.0000   0.0153
  -6.500  -0.5763   0.02170   0.01667  -0.0321   1.0000   0.0154
  -6.250  -0.5583   0.01843   0.01296  -0.0307   0.9993   0.0156
  -6.000  -0.5254   0.01586   0.01008  -0.0321   0.9964   0.0164
  -5.750  -0.4891   0.01563   0.00984  -0.0344   0.9930   0.0172
  -5.500  -0.4541   0.01509   0.00923  -0.0361   0.9889   0.0184
  -5.250  -0.4179   0.01435   0.00836  -0.0380   0.9855   0.0206
  -5.000  -0.3812   0.01356   0.00749  -0.0402   0.9828   0.0233
  -4.750  -0.3477   0.01306   0.00700  -0.0416   0.9771   0.0272
  -4.500  -0.3135   0.01224   0.00611  -0.0433   0.9720   0.0327
  -4.250  -0.2800   0.01177   0.00564  -0.0449   0.9659   0.0366
  -4.000  -0.2479   0.01141   0.00523  -0.0459   0.9581   0.0385
  -3.750  -0.2177   0.01115   0.00492  -0.0465   0.9490   0.0396
  -3.500  -0.1896   0.01066   0.00438  -0.0466   0.9395   0.0414
  -3.250  -0.1639   0.01014   0.00381  -0.0463   0.9283   0.0432
  -3.000  -0.1381   0.00983   0.00345  -0.0459   0.9171   0.0442
  -2.750  -0.1121   0.00956   0.00315  -0.0455   0.9065   0.0458
  -2.500  -0.0859   0.00933   0.00286  -0.0452   0.8964   0.0461
  -2.250  -0.0594   0.00915   0.00262  -0.0448   0.8857   0.0455
  -2.000  -0.0326   0.00900   0.00241  -0.0445   0.8750   0.0449
  -1.750  -0.0057   0.00887   0.00223  -0.0443   0.8651   0.0444
  -1.500   0.0213   0.00876   0.00206  -0.0440   0.8556   0.0440
  -1.250   0.0486   0.00865   0.00191  -0.0439   0.8451   0.0437
  -1.000   0.0760   0.00857   0.00179  -0.0438   0.8350   0.0435
  -0.750   0.1033   0.00851   0.00167  -0.0436   0.8254   0.0434
  -0.500   0.1309   0.00845   0.00158  -0.0435   0.8153   0.0436
  -0.250   0.1585   0.00841   0.00151  -0.0434   0.8055   0.0440
   0.000   0.1861   0.00839   0.00145  -0.0433   0.7962   0.0450
   0.250   0.2138   0.00835   0.00141  -0.0432   0.7861   0.0478
   0.500   0.2394   0.00697   0.00129  -0.0439   0.7764   0.4698
   0.750   0.2656   0.00653   0.00137  -0.0438   0.7674   0.6209
   1.000   0.2912   0.00631   0.00150  -0.0432   0.7575   0.7196
   1.250   0.3174   0.00626   0.00161  -0.0427   0.7464   0.7646
   1.500   0.3436   0.00626   0.00171  -0.0422   0.7350   0.7967
   1.750   0.3694   0.00627   0.00178  -0.0416   0.7202   0.8215
   2.000   0.3935   0.00629   0.00179  -0.0404   0.6907   0.8468
   2.250   0.4146   0.00633   0.00186  -0.0385   0.6612   0.8832
   2.500   0.4353   0.00638   0.00194  -0.0365   0.6394   0.9123
   2.750   0.4591   0.00643   0.00202  -0.0355   0.6183   0.9275
   3.000   0.4821   0.00652   0.00206  -0.0343   0.5881   0.9430
   3.250   0.5064   0.00668   0.00210  -0.0334   0.5391   0.9605
   3.500   0.5348   0.00735   0.00225  -0.0340   0.4036   0.9804
   3.750   0.5561   0.00929   0.00296  -0.0343   0.1298   1.0000
   4.000   0.5796   0.01025   0.00350  -0.0341   0.0491   1.0000
   4.250   0.6060   0.01074   0.00397  -0.0340   0.0381   1.0000
   4.500   0.6303   0.01158   0.00484  -0.0336   0.0308   1.0000
   4.750   0.6566   0.01200   0.00532  -0.0334   0.0288   1.0000
   5.000   0.6820   0.01257   0.00593  -0.0331   0.0264   1.0000
   5.250   0.7070   0.01315   0.00651  -0.0329   0.0240   1.0000
   5.500   0.7278   0.01453   0.00795  -0.0319   0.0220   1.0000
   5.750   0.7507   0.01577   0.00927  -0.0311   0.0212   1.0000
   6.000   0.7757   0.01659   0.01018  -0.0307   0.0206   1.0000
   6.250   0.8005   0.01766   0.01134  -0.0302   0.0199   1.0000
   6.500   0.8254   0.01887   0.01266  -0.0297   0.0190   1.0000
   6.750   0.8502   0.01980   0.01368  -0.0293   0.0178   1.0000
   7.000   0.8745   0.02115   0.01515  -0.0289   0.0172   1.0000
   7.250   0.8981   0.02276   0.01693  -0.0283   0.0167   1.0000
   7.500   0.9205   0.02471   0.01908  -0.0276   0.0163   1.0000
   7.750   0.9411   0.02717   0.02180  -0.0267   0.0161   1.0000
  11.250   0.7008   0.10920   0.10731  -0.0320   0.0215   1.0000
  11.500   0.6926   0.11704   0.11515  -0.0361   0.0215   1.0000
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