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NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-209 (naca65209-il)
Reynolds number: 100,000
Max Cl/Cd: 42.12 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65209-il-100000-n5.txt
Download as CSV file: xf-naca65209-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5416   0.08511   0.08016  -0.0318   1.0000   0.0258
  -9.000  -0.5451   0.08014   0.07523  -0.0347   1.0000   0.0253
  -8.750  -0.5526   0.07528   0.07038  -0.0379   1.0000   0.0250
  -8.500  -0.5625   0.07118   0.06627  -0.0395   1.0000   0.0247
  -8.250  -0.5699   0.06702   0.06206  -0.0406   1.0000   0.0243
  -8.000  -0.5751   0.06273   0.05765  -0.0413   1.0000   0.0244
  -7.750  -0.5773   0.05861   0.05334  -0.0414   1.0000   0.0247
  -7.500  -0.5765   0.05471   0.04921  -0.0409   1.0000   0.0251
  -7.250  -0.5725   0.05120   0.04539  -0.0398   1.0000   0.0258
  -7.000  -0.5668   0.04805   0.04190  -0.0382   1.0000   0.0263
  -6.750  -0.5606   0.04461   0.03817  -0.0366   1.0000   0.0262
  -6.500  -0.5528   0.04129   0.03448  -0.0347   1.0000   0.0262
  -6.250  -0.5432   0.03833   0.03116  -0.0328   1.0000   0.0263
  -6.000  -0.5317   0.03572   0.02814  -0.0307   1.0000   0.0265
  -5.750  -0.5191   0.03301   0.02506  -0.0288   1.0000   0.0268
  -5.500  -0.5069   0.02996   0.02177  -0.0274   1.0000   0.0287
  -5.250  -0.4912   0.02855   0.02022  -0.0260   1.0000   0.0311
  -5.000  -0.4665   0.02654   0.01785  -0.0258   0.9978   0.0324
  -4.750  -0.4330   0.02443   0.01536  -0.0270   0.9930   0.0335
  -4.500  -0.3995   0.02268   0.01328  -0.0281   0.9882   0.0351
  -4.250  -0.3656   0.02164   0.01196  -0.0293   0.9831   0.0385
  -4.000  -0.3340   0.01997   0.01028  -0.0304   0.9782   0.0412
  -3.750  -0.3025   0.01883   0.00913  -0.0315   0.9728   0.0437
  -3.500  -0.2703   0.01795   0.00816  -0.0327   0.9672   0.0471
  -3.250  -0.2377   0.01721   0.00729  -0.0341   0.9616   0.0540
  -3.000  -0.2053   0.01658   0.00657  -0.0354   0.9556   0.0644
  -2.750  -0.1701   0.01577   0.00585  -0.0372   0.9514   0.0924
  -2.500  -0.1577   0.01318   0.00582  -0.0353   0.9432   0.6348
  -2.250  -0.1329   0.01327   0.00615  -0.0332   0.9378   0.7508
  -2.000  -0.1151   0.01353   0.00648  -0.0295   0.9291   0.8097
  -1.750  -0.0914   0.01379   0.00671  -0.0270   0.9239   0.8499
  -1.500  -0.0649   0.01378   0.00657  -0.0266   0.9159   0.8614
  -1.250  -0.0314   0.01372   0.00635  -0.0278   0.9109   0.8704
  -1.000  -0.0034   0.01369   0.00623  -0.0279   0.9033   0.8798
  -0.750   0.0291   0.01365   0.00609  -0.0289   0.8979   0.8879
  -0.500   0.0577   0.01363   0.00601  -0.0291   0.8908   0.8976
  -0.250   0.0895   0.01359   0.00591  -0.0300   0.8849   0.9062
   0.000   0.1208   0.01357   0.00586  -0.0308   0.8788   0.9150
   0.250   0.1510   0.01356   0.00582  -0.0314   0.8721   0.9251
   0.500   0.1867   0.01352   0.00579  -0.0330   0.8672   0.9328
   0.750   0.2182   0.01353   0.00582  -0.0340   0.8598   0.9424
   1.000   0.2542   0.01350   0.00581  -0.0358   0.8548   0.9510
   1.250   0.2897   0.01352   0.00592  -0.0377   0.8476   0.9594
   1.500   0.3271   0.01351   0.00597  -0.0398   0.8419   0.9675
   1.750   0.3637   0.01354   0.00609  -0.0419   0.8349   0.9764
   2.000   0.4022   0.01354   0.00620  -0.0444   0.8284   0.9845
   2.250   0.4399   0.01356   0.00640  -0.0467   0.8209   0.9937
   2.500   0.4696   0.01359   0.00655  -0.0473   0.8129   1.0000
   2.750   0.4886   0.01358   0.00664  -0.0454   0.7992   1.0000
   3.000   0.5070   0.01323   0.00630  -0.0424   0.7696   1.0000
   3.250   0.5213   0.01280   0.00576  -0.0380   0.7067   1.0000
   3.500   0.5370   0.01275   0.00538  -0.0345   0.6125   1.0000
   3.750   0.5455   0.01382   0.00526  -0.0304   0.3690   1.0000
   4.000   0.5495   0.01639   0.00624  -0.0275   0.0936   1.0000
   4.250   0.5692   0.01740   0.00705  -0.0264   0.0625   1.0000
   4.500   0.5903   0.01825   0.00799  -0.0254   0.0543   1.0000
   4.750   0.6115   0.01909   0.00889  -0.0244   0.0477   1.0000
   5.000   0.6321   0.02006   0.00992  -0.0234   0.0425   1.0000
   5.250   0.6531   0.02108   0.01104  -0.0224   0.0398   1.0000
   5.500   0.6749   0.02228   0.01229  -0.0215   0.0377   1.0000
   5.750   0.6982   0.02365   0.01370  -0.0208   0.0360   1.0000
   6.000   0.7229   0.02533   0.01547  -0.0204   0.0346   1.0000
   6.250   0.7485   0.02770   0.01793  -0.0202   0.0326   1.0000
   6.500   0.7735   0.02900   0.01956  -0.0196   0.0304   1.0000
   6.750   0.7982   0.03120   0.02210  -0.0189   0.0294   1.0000
   7.000   0.8208   0.03373   0.02504  -0.0180   0.0286   1.0000
   7.250   0.8408   0.03658   0.02834  -0.0168   0.0281   1.0000
   7.500   0.8580   0.03954   0.03176  -0.0154   0.0272   1.0000
   7.750   0.8733   0.04199   0.03459  -0.0143   0.0253   1.0000
   8.000   0.8873   0.04428   0.03708  -0.0134   0.0238   1.0000
   8.250   0.8968   0.04765   0.04079  -0.0120   0.0232   1.0000
   8.500   0.9028   0.05139   0.04490  -0.0104   0.0230   1.0000
   8.750   0.9052   0.05529   0.04917  -0.0087   0.0229   1.0000
   9.000   0.9036   0.05934   0.05354  -0.0070   0.0229   1.0000
   9.250   0.8978   0.06341   0.05793  -0.0053   0.0231   1.0000
   9.500   0.8838   0.06768   0.06249  -0.0034   0.0234   1.0000
   9.750   0.8616   0.07223   0.06728  -0.0020   0.0239   1.0000
  10.000   0.8388   0.07750   0.07272  -0.0028   0.0244   1.0000
  10.250   0.8169   0.08381   0.07915  -0.0060   0.0249   1.0000
  10.500   0.7963   0.09184   0.08725  -0.0116   0.0255   1.0000
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