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NACA6409 9% (n6409-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA6409 9% (n6409-il)
Reynolds number: 100,000
Max Cl/Cd: 61.59 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n6409-il-100000.txt
Download as CSV file: xf-n6409-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA6409 9%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3419   0.11534   0.11101  -0.0253   1.0000   0.0710
  -7.750  -0.3605   0.11553   0.11130  -0.0234   1.0000   0.0713
  -7.500  -0.3803   0.11566   0.11152  -0.0212   1.0000   0.0715
  -7.250  -0.3942   0.11522   0.11116  -0.0216   1.0000   0.0717
  -7.000  -0.4029   0.11420   0.11020  -0.0241   1.0000   0.0719
  -6.750  -0.3972   0.10789   0.10394  -0.0177   1.0000   0.0729
  -6.500  -0.3818   0.10360   0.09964  -0.0157   0.9982   0.0750
  -6.250  -0.3565   0.09959   0.09559  -0.0207   0.9917   0.0788
  -6.000  -0.3184   0.09657   0.09249  -0.0431   0.9779   0.0854
  -5.750  -0.3002   0.09073   0.08666  -0.0438   0.9730   0.0869
  -5.500  -0.2835   0.08706   0.08299  -0.0420   0.9667   0.0899
  -5.250  -0.2538   0.08310   0.07899  -0.0485   0.9592   0.0954
  -5.000  -0.2147   0.07811   0.07385  -0.0648   0.9478   0.1011
  -4.750  -0.1923   0.07430   0.07006  -0.0638   0.9437   0.1042
  -4.500  -0.1685   0.07120   0.06688  -0.0680   0.9335   0.1111
  -4.250  -0.1291   0.06659   0.06216  -0.0761   0.9279   0.1193
  -4.000  -0.0862   0.06259   0.05792  -0.0870   0.9180   0.1311
  -3.750  -0.0428   0.05990   0.05496  -0.0941   0.9107   0.1448
  -3.500  -0.0229   0.05567   0.05081  -0.0942   0.9037   0.1478
  -3.250   0.0241   0.05203   0.04700  -0.1007   0.8999   0.1634
  -3.000   0.0502   0.04968   0.04453  -0.1028   0.8894   0.1784
  -2.750   0.1305   0.04163   0.03534  -0.1169   0.8868   0.1302
  -2.500   0.1772   0.03451   0.02741  -0.1216   0.8825   0.0976
  -2.250   0.2152   0.03192   0.02414  -0.1237   0.8751   0.0993
  -2.000   0.2621   0.02931   0.02109  -0.1271   0.8717   0.1032
  -1.750   0.2899   0.02855   0.02009  -0.1271   0.8617   0.1130
  -1.500   0.3352   0.02705   0.01835  -0.1298   0.8576   0.1271
  -1.250   0.3637   0.02638   0.01754  -0.1298   0.8480   0.1436
  -1.000   0.4080   0.02529   0.01645  -0.1324   0.8436   0.1692
  -0.750   0.4579   0.02418   0.01532  -0.1358   0.8412   0.2041
  -0.500   0.4815   0.02385   0.01506  -0.1350   0.8298   0.2322
  -0.250   0.5291   0.02277   0.01408  -0.1380   0.8269   0.2835
   0.000   0.5532   0.02237   0.01386  -0.1371   0.8159   0.3328
   0.250   0.6039   0.01980   0.01294  -0.1406   0.8133   1.0000
   0.500   0.6312   0.01992   0.01272  -0.1401   0.8027   1.0000
   0.750   0.6748   0.01948   0.01202  -0.1423   0.7982   1.0000
   1.000   0.6997   0.01964   0.01204  -0.1416   0.7871   1.0000
   1.250   0.7430   0.01919   0.01142  -0.1437   0.7826   1.0000
   1.500   0.7658   0.01944   0.01159  -0.1427   0.7712   1.0000
   1.750   0.7958   0.01948   0.01153  -0.1428   0.7625   1.0000
   2.000   0.8301   0.01934   0.01130  -0.1435   0.7549   1.0000
   2.250   0.8548   0.01961   0.01151  -0.1428   0.7448   1.0000
   2.500   0.8924   0.01939   0.01122  -0.1441   0.7387   1.0000
   2.750   0.9136   0.01980   0.01161  -0.1429   0.7279   1.0000
   3.000   0.9463   0.01982   0.01158  -0.1435   0.7208   1.0000
   3.250   0.9712   0.02011   0.01188  -0.1429   0.7114   1.0000
   3.500   0.9964   0.02045   0.01222  -0.1424   0.7027   1.0000
   3.750   1.0273   0.02055   0.01230  -0.1427   0.6953   1.0000
   4.000   1.0486   0.02107   0.01286  -0.1416   0.6860   1.0000
   4.250   1.0818   0.02111   0.01290  -0.1423   0.6794   1.0000
   4.500   1.1003   0.02175   0.01362  -0.1408   0.6698   1.0000
   4.750   1.1351   0.02177   0.01362  -0.1417   0.6638   1.0000
   5.000   1.1512   0.02252   0.01452  -0.1399   0.6540   1.0000
   5.250   1.1845   0.02262   0.01463  -0.1406   0.6477   1.0000
   5.500   1.2014   0.02334   0.01549  -0.1389   0.6382   1.0000
   5.750   1.2292   0.02367   0.01588  -0.1388   0.6309   1.0000
   6.000   1.2514   0.02419   0.01653  -0.1379   0.6222   1.0000
   6.250   1.2742   0.02472   0.01718  -0.1370   0.6138   1.0000
   6.500   1.3029   0.02494   0.01750  -0.1369   0.6057   1.0000
   6.750   1.3205   0.02563   0.01836  -0.1352   0.5959   1.0000
   7.000   1.3487   0.02560   0.01843  -0.1347   0.5846   1.0000
   7.250   1.3755   0.02477   0.01759  -0.1331   0.5639   1.0000
   7.500   1.4006   0.02394   0.01669  -0.1312   0.5406   1.0000
   7.750   1.4181   0.02377   0.01661  -0.1286   0.5204   1.0000
   8.000   1.4383   0.02346   0.01626  -0.1264   0.4984   1.0000
   8.250   1.4468   0.02356   0.01649  -0.1225   0.4755   1.0000
   8.500   1.4553   0.02363   0.01663  -0.1185   0.4500   1.0000
   8.750   1.4565   0.02388   0.01696  -0.1135   0.4190   1.0000
   9.000   1.4481   0.02436   0.01742  -0.1069   0.3771   1.0000
   9.250   1.4292   0.02561   0.01830  -0.0992   0.3049   1.0000
   9.500   1.4017   0.02824   0.02022  -0.0918   0.2150   1.0000
   9.750   1.3746   0.03169   0.02305  -0.0858   0.1508   1.0000
  10.000   1.3535   0.03519   0.02619  -0.0810   0.1176   1.0000
  10.250   1.3387   0.03846   0.02932  -0.0774   0.1014   1.0000
  10.500   1.3299   0.04146   0.03233  -0.0745   0.0907   1.0000
  10.750   1.3233   0.04441   0.03526  -0.0720   0.0833   1.0000
  11.000   1.3222   0.04701   0.03785  -0.0700   0.0764   1.0000
  11.250   1.3266   0.04929   0.04013  -0.0680   0.0703   1.0000
  11.500   1.3383   0.05111   0.04192  -0.0664   0.0655   1.0000
  11.750   1.3726   0.05233   0.04300  -0.0651   0.0607   1.0000
  12.000   1.3965   0.05400   0.04487  -0.0642   0.0571   1.0000
  12.250   1.4203   0.05589   0.04681  -0.0635   0.0535   1.0000
  12.500   1.4911   0.05987   0.05088  -0.0662   0.0506   1.0000
  12.750   1.5013   0.06303   0.05441  -0.0646   0.0502   1.0000
  13.000   1.5013   0.06619   0.05794  -0.0625   0.0497   1.0000
  13.250   1.4964   0.06952   0.06163  -0.0604   0.0492   1.0000
  13.500   1.4878   0.07308   0.06553  -0.0584   0.0487   1.0000
  13.750   1.4767   0.07697   0.06977  -0.0567   0.0483   1.0000
  14.000   1.4639   0.08122   0.07434  -0.0554   0.0482   1.0000
  14.250   1.4487   0.08586   0.07928  -0.0546   0.0483   1.0000
  14.500   1.4321   0.09091   0.08462  -0.0542   0.0485   1.0000
  14.750   1.4136   0.09629   0.09027  -0.0545   0.0489   1.0000
  15.000   1.3943   0.10200   0.09622  -0.0553   0.0492   1.0000
  15.250   1.3743   0.10807   0.10251  -0.0568   0.0496   1.0000
  15.500   1.3547   0.11450   0.10914  -0.0588   0.0500   1.0000
  15.750   1.3385   0.12133   0.11614  -0.0612   0.0505   1.0000
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