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NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-209 (naca63209-il)
Reynolds number: 100,000
Max Cl/Cd: 44.54 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca63209-il-100000-n5.txt
Download as CSV file: xf-naca63209-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5673   0.08977   0.08480  -0.0177   1.0000   0.0289
  -9.250  -0.5699   0.08449   0.07956  -0.0209   1.0000   0.0283
  -9.000  -0.5755   0.07817   0.07330  -0.0257   1.0000   0.0279
  -8.750  -0.5864   0.07165   0.06680  -0.0314   1.0000   0.0274
  -8.500  -0.5994   0.06657   0.06167  -0.0347   1.0000   0.0270
  -8.250  -0.6075   0.06153   0.05650  -0.0369   1.0000   0.0266
  -8.000  -0.6114   0.05663   0.05139  -0.0383   1.0000   0.0262
  -7.750  -0.6112   0.05181   0.04630  -0.0391   1.0000   0.0259
  -7.500  -0.6066   0.04724   0.04139  -0.0393   1.0000   0.0257
  -7.250  -0.5981   0.04301   0.03677  -0.0391   1.0000   0.0257
  -7.000  -0.5862   0.03915   0.03248  -0.0386   1.0000   0.0259
  -6.750  -0.5714   0.03575   0.02862  -0.0378   1.0000   0.0265
  -6.500  -0.5538   0.03312   0.02554  -0.0370   1.0000   0.0284
  -6.250  -0.5345   0.03080   0.02272  -0.0360   1.0000   0.0301
  -6.000  -0.5143   0.02854   0.02003  -0.0349   1.0000   0.0307
  -5.750  -0.4936   0.02650   0.01765  -0.0338   1.0000   0.0314
  -5.500  -0.4734   0.02413   0.01506  -0.0328   1.0000   0.0326
  -5.250  -0.4532   0.02278   0.01367  -0.0319   1.0000   0.0352
  -5.000  -0.4325   0.02171   0.01248  -0.0308   1.0000   0.0383
  -4.750  -0.4121   0.02052   0.01118  -0.0295   1.0000   0.0402
  -4.500  -0.3922   0.01948   0.01005  -0.0281   1.0000   0.0421
  -4.250  -0.3732   0.01848   0.00900  -0.0268   1.0000   0.0443
  -4.000  -0.3543   0.01766   0.00816  -0.0257   1.0000   0.0490
  -3.750  -0.3213   0.01690   0.00731  -0.0273   0.9939   0.0574
  -3.500  -0.2855   0.01609   0.00644  -0.0294   0.9865   0.0705
  -3.250  -0.2511   0.01497   0.00567  -0.0315   0.9789   0.1278
  -3.000  -0.2221   0.01297   0.00523  -0.0333   0.9717   0.4642
  -2.750  -0.1894   0.01264   0.00532  -0.0340   0.9645   0.5989
  -2.500  -0.1624   0.01265   0.00566  -0.0328   0.9551   0.7004
  -2.250  -0.1339   0.01277   0.00582  -0.0320   0.9464   0.7530
  -2.000  -0.1019   0.01278   0.00572  -0.0324   0.9381   0.7734
  -1.750  -0.0712   0.01275   0.00560  -0.0328   0.9285   0.7892
  -1.500  -0.0389   0.01271   0.00547  -0.0334   0.9202   0.8032
  -1.250  -0.0086   0.01268   0.00534  -0.0337   0.9106   0.8166
  -1.000   0.0203   0.01265   0.00525  -0.0337   0.9005   0.8299
  -0.750   0.0502   0.01261   0.00516  -0.0338   0.8915   0.8430
  -0.500   0.0787   0.01258   0.00508  -0.0337   0.8816   0.8564
  -0.250   0.1058   0.01255   0.00502  -0.0333   0.8710   0.8701
   0.000   0.1337   0.01252   0.00497  -0.0330   0.8612   0.8840
   0.250   0.1626   0.01247   0.00491  -0.0329   0.8520   0.8981
   0.500   0.1908   0.01244   0.00489  -0.0328   0.8411   0.9130
   0.750   0.2215   0.01240   0.00487  -0.0332   0.8310   0.9280
   1.000   0.2553   0.01236   0.00483  -0.0342   0.8219   0.9426
   1.250   0.2908   0.01233   0.00486  -0.0357   0.8112   0.9574
   1.500   0.3283   0.01232   0.00489  -0.0378   0.8005   0.9726
   1.750   0.3664   0.01230   0.00492  -0.0400   0.7900   0.9900
   2.000   0.3950   0.01235   0.00502  -0.0403   0.7791   1.0000
   2.250   0.4186   0.01246   0.00516  -0.0397   0.7669   1.0000
   2.500   0.4434   0.01258   0.00532  -0.0392   0.7541   1.0000
   2.750   0.4688   0.01269   0.00549  -0.0387   0.7404   1.0000
   3.000   0.4945   0.01278   0.00566  -0.0381   0.7247   1.0000
   3.250   0.5194   0.01284   0.00577  -0.0372   0.7029   1.0000
   3.500   0.5431   0.01283   0.00573  -0.0358   0.6678   1.0000
   3.750   0.5642   0.01286   0.00555  -0.0337   0.6013   1.0000
   4.000   0.5857   0.01315   0.00557  -0.0320   0.5181   1.0000
   4.250   0.6069   0.01372   0.00577  -0.0307   0.4178   1.0000
   4.500   0.6196   0.01560   0.00641  -0.0289   0.1949   1.0000
   4.750   0.6370   0.01733   0.00742  -0.0280   0.0872   1.0000
   5.000   0.6588   0.01841   0.00838  -0.0273   0.0630   1.0000
   5.250   0.6813   0.01936   0.00938  -0.0266   0.0527   1.0000
   5.500   0.7025   0.02047   0.01057  -0.0258   0.0467   1.0000
   5.750   0.7249   0.02141   0.01160  -0.0251   0.0408   1.0000
   6.000   0.7458   0.02269   0.01290  -0.0243   0.0376   1.0000
   6.250   0.7672   0.02433   0.01457  -0.0234   0.0357   1.0000
   6.500   0.7913   0.02581   0.01620  -0.0227   0.0344   1.0000
   6.750   0.8162   0.02756   0.01817  -0.0222   0.0331   1.0000
   7.000   0.8408   0.02942   0.02026  -0.0216   0.0315   1.0000
   7.250   0.8637   0.03106   0.02211  -0.0211   0.0291   1.0000
   7.500   0.8855   0.03300   0.02427  -0.0206   0.0275   1.0000
   7.750   0.9059   0.03557   0.02710  -0.0199   0.0266   1.0000
   8.000   0.9234   0.03883   0.03069  -0.0191   0.0259   1.0000
   8.250   0.9367   0.04284   0.03514  -0.0181   0.0255   1.0000
   8.500   0.9472   0.04627   0.03904  -0.0167   0.0251   1.0000
   8.750   0.9551   0.04927   0.04262  -0.0151   0.0243   1.0000
   9.000   0.9579   0.05288   0.04672  -0.0136   0.0234   1.0000
   9.250   0.9555   0.05686   0.05111  -0.0121   0.0227   1.0000
   9.500   0.9479   0.06105   0.05563  -0.0109   0.0226   1.0000
   9.750   0.9343   0.06500   0.05982  -0.0095   0.0226   1.0000
  10.000   0.9167   0.06912   0.06412  -0.0090   0.0227   1.0000
  10.250   0.8973   0.07394   0.06911  -0.0103   0.0228   1.0000
  10.500   0.8781   0.07963   0.07493  -0.0133   0.0230   1.0000
  10.750   0.8583   0.08666   0.08206  -0.0182   0.0233   1.0000
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