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NACA 65-209 (naca65209-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 65-209 (naca65209-il)
Reynolds number: 100,000
Max Cl/Cd: 43.61 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca65209-il-100000.txt
Download as CSV file: xf-naca65209-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5320   0.10841   0.10334  -0.0173   1.0000   0.0853
  -9.750  -0.5467   0.10471   0.09975  -0.0235   1.0000   0.0874
  -9.500  -0.5634   0.10037   0.09554  -0.0304   1.0000   0.0879
  -9.250  -0.5291   0.09642   0.09148  -0.0219   1.0000   0.0940
  -9.000  -0.5320   0.09255   0.08767  -0.0245   1.0000   0.0983
  -8.750  -0.5465   0.08806   0.08327  -0.0303   1.0000   0.1004
  -8.500  -0.4485   0.07630   0.07181  -0.0279   1.0000   0.1232
  -8.250  -0.5579   0.07922   0.07455  -0.0340   1.0000   0.1052
  -8.000  -0.5557   0.07591   0.07126  -0.0342   1.0000   0.1104
  -7.750  -0.5760   0.07220   0.06742  -0.0384   1.0000   0.1145
  -7.500  -0.5656   0.06814   0.06346  -0.0368   1.0000   0.1214
  -7.250  -0.5852   0.06614   0.06105  -0.0390   1.0000   0.1293
  -7.000  -0.5683   0.06174   0.05693  -0.0369   1.0000   0.1406
  -6.750  -0.5671   0.05878   0.05393  -0.0359   1.0000   0.1546
  -6.500  -0.5637   0.05586   0.05100  -0.0344   1.0000   0.1680
  -6.000  -0.5584   0.05037   0.04549  -0.0306   1.0000   0.2035
  -5.000  -0.4920   0.03333   0.02562  -0.0266   1.0000   0.0895
  -4.750  -0.4700   0.03030   0.02191  -0.0245   1.0000   0.0756
  -4.500  -0.4501   0.02839   0.01965  -0.0230   1.0000   0.0752
  -4.250  -0.4287   0.02624   0.01728  -0.0217   1.0000   0.0731
  -4.000  -0.4068   0.02420   0.01501  -0.0205   1.0000   0.0717
  -3.750  -0.3843   0.02260   0.01319  -0.0192   1.0000   0.0717
  -3.500  -0.3622   0.02154   0.01191  -0.0180   1.0000   0.0737
  -3.250  -0.3407   0.02007   0.01052  -0.0171   1.0000   0.0791
  -3.000  -0.3194   0.01909   0.00952  -0.0159   1.0000   0.0829
  -2.750  -0.2988   0.01835   0.00872  -0.0147   1.0000   0.0878
  -2.500  -0.2788   0.01746   0.00794  -0.0138   1.0000   0.0986
  -2.250  -0.2577   0.01668   0.00724  -0.0131   1.0000   0.1215
  -2.000  -0.2519   0.01385   0.00737  -0.0085   1.0000   0.7336
  -1.750  -0.2596   0.01421   0.00803   0.0012   1.0000   0.8500
  -1.500  -0.1046   0.01588   0.00918  -0.0146   1.0000   0.9959
  -1.250  -0.0924   0.01576   0.00895  -0.0141   1.0000   1.0000
  -1.000  -0.1046   0.01551   0.00868  -0.0095   1.0000   1.0000
  -0.750  -0.0746   0.01560   0.00861  -0.0119   0.9941   1.0000
  -0.500  -0.0390   0.01573   0.00861  -0.0152   0.9859   1.0000
  -0.250  -0.0054   0.01589   0.00868  -0.0179   0.9778   1.0000
   0.000   0.0310   0.01613   0.00882  -0.0211   0.9705   1.0000
   0.250   0.0580   0.01628   0.00890  -0.0224   0.9615   1.0000
   0.500   0.0979   0.01660   0.00917  -0.0259   0.9555   1.0000
   0.750   0.1221   0.01680   0.00933  -0.0264   0.9462   1.0000
   1.000   0.1593   0.01713   0.00965  -0.0292   0.9399   1.0000
   1.250   0.1882   0.01740   0.00992  -0.0304   0.9315   1.0000
   1.500   0.2227   0.01774   0.01027  -0.0325   0.9246   1.0000
   1.750   0.2551   0.01806   0.01063  -0.0342   0.9168   1.0000
   2.000   0.2864   0.01840   0.01104  -0.0355   0.9088   1.0000
   2.250   0.3248   0.01869   0.01143  -0.0381   0.9016   1.0000
   2.500   0.3531   0.01903   0.01187  -0.0388   0.8920   1.0000
   2.750   0.4023   0.01918   0.01224  -0.0429   0.8858   1.0000
   3.000   0.4315   0.01943   0.01264  -0.0435   0.8744   1.0000
   3.250   0.5291   0.01584   0.00946  -0.0480   0.8264   1.0000
   3.500   0.5552   0.01395   0.00762  -0.0423   0.7703   1.0000
   3.750   0.5709   0.01309   0.00671  -0.0368   0.6915   1.0000
   4.000   0.5560   0.01567   0.00644  -0.0276   0.1670   1.0000
   4.250   0.5690   0.01753   0.00773  -0.0253   0.1038   1.0000
   4.500   0.5871   0.01878   0.00894  -0.0236   0.0897   1.0000
   4.750   0.6063   0.02019   0.01021  -0.0222   0.0785   1.0000
   5.000   0.6309   0.02149   0.01158  -0.0213   0.0739   1.0000
   5.250   0.6582   0.02309   0.01321  -0.0208   0.0705   1.0000
   5.500   0.6870   0.02500   0.01516  -0.0206   0.0682   1.0000
   5.750   0.7151   0.02772   0.01791  -0.0206   0.0645   1.0000
   6.000   0.7420   0.02988   0.02042  -0.0199   0.0637   1.0000
   6.250   0.7682   0.03324   0.02409  -0.0193   0.0647   1.0000
   6.500   0.7935   0.03538   0.02708  -0.0171   0.0710   1.0000
   6.750   0.8180   0.03941   0.03155  -0.0157   0.0807   1.0000
   8.500   0.8495   0.07493   0.07044  -0.0089   0.1560   1.0000
   9.250   0.7142   0.08378   0.07967  -0.0079   0.1587   1.0000
   9.500   0.6759   0.09173   0.08757  -0.0144   0.1580   1.0000
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