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USA 40 B AIRFOIL (usa40b-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: USA 40 B AIRFOIL (usa40b-il)
Reynolds number: 100,000
Max Cl/Cd: 39.93 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa40b-il-100000.txt
Download as CSV file: xf-usa40b-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 40 B AIRFOIL                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2610   0.09768   0.09278  -0.0272   1.0000   0.1392
  -8.000  -0.2995   0.09728   0.09256  -0.0292   1.0000   0.1441
  -7.750  -0.3575   0.09743   0.09294  -0.0297   1.0000   0.1448
  -7.500  -0.2822   0.09107   0.08647  -0.0253   1.0000   0.1484
  -7.250  -0.2785   0.08931   0.08479  -0.0230   1.0000   0.1520
  -7.000  -0.2945   0.08821   0.08381  -0.0206   1.0000   0.1561
  -6.750  -0.3329   0.08813   0.08391  -0.0171   1.0000   0.1583
  -6.500  -0.4110   0.08676   0.08265  -0.0265   1.0000   0.1606
  -6.250  -0.3927   0.08458   0.08061  -0.0168   1.0000   0.1620
  -6.000  -0.3700   0.08296   0.07903  -0.0121   0.9981   0.1649
  -5.750  -0.3343   0.07575   0.07175  -0.0309   0.9839   0.1790
  -5.500  -0.2976   0.07322   0.06924  -0.0298   0.9765   0.1830
  -5.250  -0.2664   0.06701   0.06292  -0.0438   0.9631   0.1975
  -5.000  -0.2300   0.03890   0.03251  -0.0755   0.9526   0.1025
  -4.750  -0.1885   0.03530   0.02852  -0.0796   0.9431   0.1020
  -4.500  -0.1492   0.03233   0.02515  -0.0826   0.9328   0.1016
  -4.250  -0.1006   0.02949   0.02186  -0.0867   0.9254   0.1014
  -4.000  -0.0617   0.02753   0.01950  -0.0885   0.9137   0.1022
  -3.750  -0.0090   0.02535   0.01716  -0.0927   0.9076   0.1060
  -3.500   0.0300   0.02409   0.01584  -0.0942   0.8949   0.1110
  -3.250   0.0783   0.02257   0.01408  -0.0969   0.8857   0.1164
  -3.000   0.1199   0.02115   0.01281  -0.0985   0.8735   0.1250
  -2.750   0.1562   0.02007   0.01181  -0.0992   0.8583   0.1373
  -2.500   0.1922   0.01907   0.01089  -0.0996   0.8423   0.1562
  -2.250   0.2263   0.01817   0.01014  -0.0997   0.8243   0.1889
  -2.000   0.2574   0.01704   0.00934  -0.0994   0.8046   0.2553
  -1.750   0.2865   0.01608   0.00885  -0.0989   0.7832   0.3664
  -1.500   0.3147   0.01543   0.00854  -0.0978   0.7601   0.4685
  -1.250   0.3366   0.01514   0.00857  -0.0954   0.7327   0.5708
  -1.000   0.3591   0.01514   0.00863  -0.0926   0.7056   0.6592
  -0.750   0.3781   0.01528   0.00872  -0.0893   0.6747   0.7214
  -0.500   0.3960   0.01537   0.00868  -0.0857   0.6451   0.7755
  -0.250   0.4109   0.01531   0.00854  -0.0816   0.6142   0.8263
   0.000   0.4273   0.01511   0.00821  -0.0779   0.5855   0.8764
   0.250   0.4639   0.01495   0.00782  -0.0783   0.5549   0.9340
   0.500   0.5151   0.01516   0.00768  -0.0829   0.5225   1.0000
   0.750   0.5395   0.01552   0.00770  -0.0826   0.5023   1.0000
   1.000   0.5660   0.01593   0.00781  -0.0827   0.4842   1.0000
   1.250   0.5931   0.01636   0.00799  -0.0827   0.4680   1.0000
   1.500   0.6205   0.01682   0.00821  -0.0828   0.4536   1.0000
   1.750   0.6484   0.01731   0.00845  -0.0828   0.4413   1.0000
   2.000   0.6760   0.01778   0.00872  -0.0828   0.4296   1.0000
   2.250   0.7034   0.01830   0.00912  -0.0828   0.4193   1.0000
   2.500   0.7316   0.01884   0.00943  -0.0829   0.4104   1.0000
   2.750   0.7584   0.01939   0.00992  -0.0827   0.4016   1.0000
   3.000   0.7860   0.01992   0.01029  -0.0826   0.3935   1.0000
   3.250   0.8131   0.02054   0.01081  -0.0825   0.3862   1.0000
   3.500   0.8393   0.02108   0.01132  -0.0822   0.3789   1.0000
   3.750   0.8677   0.02173   0.01178  -0.0823   0.3733   1.0000
   4.000   0.8934   0.02242   0.01250  -0.0820   0.3677   1.0000
   4.250   0.9188   0.02306   0.01316  -0.0816   0.3619   1.0000
   4.500   0.9459   0.02370   0.01370  -0.0815   0.3569   1.0000
   4.750   0.9730   0.02452   0.01443  -0.0814   0.3524   1.0000
   5.000   0.9960   0.02524   0.01528  -0.0807   0.3472   1.0000
   5.250   1.0208   0.02596   0.01605  -0.0803   0.3427   1.0000
   5.500   1.0470   0.02672   0.01676  -0.0801   0.3389   1.0000
   5.750   1.0748   0.02772   0.01763  -0.0802   0.3357   1.0000
   6.000   1.0951   0.02871   0.01885  -0.0792   0.3323   1.0000
   6.250   1.1163   0.02974   0.02004  -0.0784   0.3288   1.0000
   6.500   1.1392   0.03070   0.02107  -0.0778   0.3253   1.0000
   6.750   1.1633   0.03159   0.02198  -0.0774   0.3220   1.0000
   7.000   1.1890   0.03256   0.02290  -0.0772   0.3191   1.0000
   7.250   1.2096   0.03396   0.02440  -0.0765   0.3165   1.0000
   7.500   1.2237   0.03551   0.02625  -0.0750   0.3139   1.0000
   7.750   1.2380   0.03716   0.02813  -0.0736   0.3113   1.0000
   8.000   1.2529   0.03883   0.02997  -0.0724   0.3088   1.0000
   8.250   1.2688   0.04045   0.03174  -0.0713   0.3066   1.0000
   8.500   1.2888   0.04178   0.03314  -0.0706   0.3043   1.0000
   8.750   1.3126   0.04294   0.03429  -0.0703   0.3020   1.0000
   9.000   1.3344   0.04472   0.03605  -0.0700   0.2998   1.0000
   9.250   1.3230   0.04807   0.03984  -0.0666   0.2980   1.0000
   9.500   1.2988   0.05255   0.04471  -0.0628   0.2964   1.0000
   9.750   1.0254   0.08332   0.07613  -0.0597   0.2995   1.0000
  10.000   0.8120   0.12522   0.11829  -0.0832   0.3549   1.0000
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