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NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 63-209 (naca63209-il)
Reynolds number: 500,000
Max Cl/Cd: 78.03 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca63209-il-500000.txt
Download as CSV file: xf-naca63209-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-209                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4787   0.08191   0.07980  -0.0191   1.0000   0.0206
  -9.500  -0.4850   0.07510   0.07300  -0.0227   1.0000   0.0207
  -9.250  -0.4955   0.06681   0.06470  -0.0279   1.0000   0.0206
  -9.000  -0.5118   0.05985   0.05769  -0.0332   1.0000   0.0206
  -8.750  -0.5306   0.05464   0.05241  -0.0368   1.0000   0.0206
  -8.500  -0.5510   0.05084   0.04853  -0.0381   1.0000   0.0206
  -8.250  -0.5625   0.04664   0.04420  -0.0387   1.0000   0.0206
  -6.500  -0.5616   0.02516   0.02059  -0.0357   1.0000   0.0185
  -6.250  -0.5471   0.02150   0.01649  -0.0337   1.0000   0.0178
  -6.000  -0.5312   0.01942   0.01414  -0.0318   1.0000   0.0180
  -5.750  -0.4990   0.01760   0.01207  -0.0329   0.9973   0.0188
  -5.500  -0.4623   0.01681   0.01108  -0.0349   0.9938   0.0202
  -5.250  -0.4275   0.01561   0.00972  -0.0364   0.9894   0.0208
  -5.000  -0.3948   0.01303   0.00700  -0.0379   0.9855   0.0222
  -4.750  -0.3587   0.01210   0.00604  -0.0400   0.9820   0.0237
  -4.500  -0.3247   0.01158   0.00548  -0.0414   0.9752   0.0264
  -4.250  -0.2888   0.01096   0.00480  -0.0433   0.9699   0.0284
  -4.000  -0.2574   0.01019   0.00394  -0.0442   0.9605   0.0309
  -3.750  -0.2262   0.00962   0.00334  -0.0450   0.9513   0.0363
  -3.500  -0.1969   0.00921   0.00286  -0.0453   0.9411   0.0443
  -3.250  -0.1704   0.00877   0.00247  -0.0450   0.9290   0.0673
  -3.000  -0.1470   0.00744   0.00202  -0.0451   0.9168   0.2917
  -2.750  -0.1230   0.00656   0.00184  -0.0448   0.9054   0.4906
  -2.500  -0.0971   0.00632   0.00177  -0.0444   0.8947   0.5641
  -2.000  -0.0440   0.00614   0.00168  -0.0435   0.8732   0.6379
  -1.750  -0.0173   0.00608   0.00167  -0.0431   0.8627   0.6706
  -1.500   0.0093   0.00607   0.00167  -0.0427   0.8527   0.7015
  -1.250   0.0358   0.00606   0.00169  -0.0421   0.8425   0.7284
  -1.000   0.0631   0.00605   0.00168  -0.0419   0.8319   0.7441
  -0.750   0.0903   0.00605   0.00166  -0.0416   0.8220   0.7577
  -0.500   0.1175   0.00606   0.00164  -0.0413   0.8124   0.7695
  -0.250   0.1449   0.00605   0.00164  -0.0411   0.8019   0.7807
   0.000   0.1724   0.00606   0.00165  -0.0409   0.7918   0.7919
   0.250   0.1998   0.00609   0.00165  -0.0407   0.7821   0.8034
   0.500   0.2270   0.00610   0.00167  -0.0405   0.7718   0.8145
   0.750   0.2542   0.00611   0.00170  -0.0402   0.7611   0.8254
   1.000   0.2812   0.00613   0.00174  -0.0399   0.7506   0.8365
   1.250   0.3082   0.00616   0.00178  -0.0396   0.7396   0.8480
   1.500   0.3349   0.00620   0.00181  -0.0392   0.7274   0.8600
   1.750   0.3611   0.00622   0.00186  -0.0387   0.7134   0.8718
   2.000   0.3866   0.00624   0.00189  -0.0380   0.6949   0.8839
   2.250   0.4112   0.00628   0.00191  -0.0370   0.6669   0.8967
   2.500   0.4354   0.00635   0.00193  -0.0361   0.6403   0.9103
   2.750   0.4592   0.00641   0.00198  -0.0350   0.6156   0.9252
   3.000   0.4827   0.00647   0.00203  -0.0339   0.5909   0.9421
   3.250   0.5076   0.00658   0.00208  -0.0331   0.5519   0.9613
   3.500   0.5392   0.00691   0.00216  -0.0341   0.4790   0.9837
   3.750   0.5653   0.00783   0.00244  -0.0346   0.3330   1.0000
   4.000   0.5854   0.00936   0.00305  -0.0343   0.1361   1.0000
   4.250   0.6091   0.01036   0.00363  -0.0341   0.0504   1.0000
   4.500   0.6354   0.01092   0.00415  -0.0340   0.0372   1.0000
   4.750   0.6610   0.01158   0.00484  -0.0337   0.0307   1.0000
   5.000   0.6873   0.01205   0.00533  -0.0336   0.0270   1.0000
   5.250   0.7114   0.01289   0.00621  -0.0332   0.0242   1.0000
   5.500   0.7336   0.01408   0.00750  -0.0324   0.0228   1.0000
   5.750   0.7587   0.01474   0.00823  -0.0320   0.0220   1.0000
   6.000   0.7830   0.01561   0.00917  -0.0314   0.0210   1.0000
   6.250   0.8077   0.01641   0.01002  -0.0310   0.0198   1.0000
   6.500   0.8323   0.01721   0.01088  -0.0306   0.0186   1.0000
   6.750   0.8564   0.01827   0.01201  -0.0302   0.0179   1.0000
   7.000   0.8800   0.01960   0.01342  -0.0297   0.0173   1.0000
   7.250   0.9027   0.02174   0.01569  -0.0290   0.0167   1.0000
   7.500   0.9238   0.02502   0.01924  -0.0282   0.0163   1.0000
   7.750   0.9439   0.02716   0.02173  -0.0272   0.0156   1.0000
   8.000   0.9649   0.02882   0.02366  -0.0263   0.0150   1.0000
   8.250   0.9803   0.03227   0.02750  -0.0248   0.0150   1.0000
   8.500   0.9899   0.03661   0.03228  -0.0230   0.0152   1.0000
  16.000   0.7005   0.19362   0.19184  -0.0820   0.0139   1.0000
  16.250   0.7045   0.19719   0.19541  -0.0838   0.0130   1.0000
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