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USA 40 B AIRFOIL (usa40b-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 40 B AIRFOIL (usa40b-il)
Reynolds number: 100,000
Max Cl/Cd: 45.34 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa40b-il-100000-n5.txt
Download as CSV file: xf-usa40b-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3027   0.09235   0.08707  -0.0363   1.0000   0.0544
  -8.750  -0.3074   0.08892   0.08371  -0.0368   1.0000   0.0543
  -8.500  -0.3148   0.08547   0.08034  -0.0372   1.0000   0.0542
  -8.250  -0.3250   0.08212   0.07708  -0.0372   1.0000   0.0540
  -8.000  -0.3401   0.07886   0.07393  -0.0367   1.0000   0.0536
  -7.500  -0.4392   0.04656   0.04066  -0.0665   0.9856   0.0498
  -7.250  -0.4129   0.04218   0.03593  -0.0716   0.9769   0.0500
  -7.000  -0.3813   0.03890   0.03235  -0.0757   0.9698   0.0504
  -6.750  -0.3526   0.03625   0.02942  -0.0783   0.9603   0.0509
  -6.500  -0.3209   0.03400   0.02691  -0.0809   0.9518   0.0517
  -6.250  -0.2859   0.03192   0.02455  -0.0837   0.9436   0.0530
  -6.000  -0.2512   0.02971   0.02192  -0.0860   0.9319   0.0545
  -5.750  -0.2119   0.02752   0.01928  -0.0886   0.9206   0.0556
  -5.500  -0.1715   0.02579   0.01731  -0.0910   0.9091   0.0565
  -5.250  -0.1388   0.02464   0.01610  -0.0919   0.8947   0.0576
  -5.000  -0.1055   0.02358   0.01494  -0.0928   0.8819   0.0589
  -4.750  -0.0694   0.02255   0.01375  -0.0942   0.8702   0.0609
  -4.500  -0.0377   0.02168   0.01271  -0.0946   0.8548   0.0634
  -4.250  -0.0068   0.02093   0.01200  -0.0950   0.8385   0.0657
  -4.000   0.0247   0.02020   0.01119  -0.0953   0.8216   0.0684
  -3.750   0.0561   0.01950   0.01035  -0.0955   0.8039   0.0714
  -3.500   0.0868   0.01884   0.00970  -0.0957   0.7853   0.0749
  -3.250   0.1175   0.01832   0.00905  -0.0957   0.7662   0.0809
  -3.000   0.1469   0.01781   0.00850  -0.0957   0.7469   0.0880
  -2.750   0.1756   0.01734   0.00796  -0.0955   0.7271   0.0970
  -2.500   0.2034   0.01695   0.00754  -0.0952   0.7069   0.1108
  -2.250   0.2303   0.01660   0.00724  -0.0947   0.6864   0.1332
  -2.000   0.2563   0.01631   0.00707  -0.0941   0.6645   0.1754
  -1.750   0.2816   0.01606   0.00691  -0.0934   0.6407   0.2257
  -1.500   0.3065   0.01580   0.00676  -0.0927   0.6155   0.2755
  -1.250   0.3314   0.01561   0.00665  -0.0918   0.5885   0.3312
  -1.000   0.3560   0.01547   0.00656  -0.0909   0.5597   0.3920
  -0.750   0.3795   0.01537   0.00652  -0.0898   0.5312   0.4590
  -0.500   0.4019   0.01531   0.00662  -0.0882   0.5041   0.5459
  -0.250   0.4233   0.01541   0.00678  -0.0863   0.4799   0.6317
   0.000   0.4453   0.01560   0.00690  -0.0845   0.4584   0.6892
   0.250   0.4679   0.01580   0.00698  -0.0829   0.4400   0.7308
   0.500   0.4907   0.01600   0.00704  -0.0815   0.4243   0.7622
   0.750   0.5145   0.01618   0.00710  -0.0803   0.4102   0.7892
   1.000   0.5382   0.01632   0.00714  -0.0791   0.3978   0.8135
   1.250   0.5621   0.01648   0.00717  -0.0779   0.3869   0.8399
   1.500   0.5880   0.01654   0.00722  -0.0772   0.3761   0.8721
   1.750   0.6288   0.01662   0.00724  -0.0795   0.3657   0.9909
   2.000   0.6554   0.01694   0.00742  -0.0793   0.3572   1.0000
   2.250   0.6821   0.01731   0.00758  -0.0792   0.3500   1.0000
   2.500   0.7092   0.01763   0.00781  -0.0790   0.3421   1.0000
   2.750   0.7356   0.01800   0.00801  -0.0788   0.3354   1.0000
   3.000   0.7622   0.01837   0.00826  -0.0786   0.3292   1.0000
   3.250   0.7888   0.01872   0.00854  -0.0783   0.3229   1.0000
   3.500   0.8150   0.01912   0.00881  -0.0780   0.3177   1.0000
   3.750   0.8414   0.01955   0.00911  -0.0778   0.3132   1.0000
   4.000   0.8677   0.01993   0.00948  -0.0775   0.3080   1.0000
   4.250   0.8937   0.02034   0.00983  -0.0772   0.3031   1.0000
   4.500   0.9195   0.02078   0.01015  -0.0768   0.2989   1.0000
   4.750   0.9455   0.02124   0.01055  -0.0765   0.2949   1.0000
   5.000   0.9710   0.02168   0.01101  -0.0761   0.2905   1.0000
   5.250   0.9965   0.02213   0.01144  -0.0757   0.2865   1.0000
   5.500   1.0220   0.02261   0.01187  -0.0753   0.2832   1.0000
   5.750   1.0477   0.02313   0.01231  -0.0750   0.2803   1.0000
   6.000   1.0731   0.02368   0.01286  -0.0747   0.2774   1.0000
   6.250   1.0976   0.02421   0.01346  -0.0742   0.2741   1.0000
   6.500   1.1220   0.02476   0.01404  -0.0737   0.2708   1.0000
   6.750   1.1464   0.02529   0.01459  -0.0732   0.2678   1.0000
   7.000   1.1709   0.02583   0.01510  -0.0727   0.2650   1.0000
   7.250   1.1960   0.02642   0.01563  -0.0724   0.2627   1.0000
   7.500   1.2197   0.02709   0.01636  -0.0719   0.2604   1.0000
   7.750   1.2421   0.02778   0.01719  -0.0712   0.2579   1.0000
   8.000   1.2644   0.02849   0.01800  -0.0705   0.2554   1.0000
   8.250   1.2868   0.02920   0.01879  -0.0698   0.2531   1.0000
   8.500   1.3093   0.02991   0.01957  -0.0692   0.2510   1.0000
   8.750   1.3320   0.03061   0.02029  -0.0685   0.2490   1.0000
   9.000   1.3553   0.03128   0.02097  -0.0680   0.2470   1.0000
   9.250   1.3798   0.03201   0.02168  -0.0677   0.2452   1.0000
   9.500   1.3967   0.03297   0.02284  -0.0664   0.2430   1.0000
   9.750   1.4130   0.03397   0.02403  -0.0651   0.2408   1.0000
  10.000   1.4292   0.03496   0.02520  -0.0638   0.2385   1.0000
  10.250   1.4455   0.03589   0.02627  -0.0625   0.2363   1.0000
  10.500   1.4629   0.03674   0.02721  -0.0614   0.2341   1.0000
  10.750   1.4821   0.03747   0.02798  -0.0604   0.2319   1.0000
  11.000   1.5048   0.03804   0.02853  -0.0599   0.2297   1.0000
  11.250   1.5174   0.03908   0.02970  -0.0583   0.2273   1.0000
  11.500   1.5186   0.04050   0.03139  -0.0554   0.2247   1.0000
  11.750   1.5204   0.04182   0.03292  -0.0525   0.2223   1.0000
  12.000   1.5235   0.04308   0.03434  -0.0500   0.2201   1.0000
  12.250   1.5304   0.04415   0.03550  -0.0479   0.2178   1.0000
  12.500   1.5452   0.04482   0.03620  -0.0466   0.2155   1.0000
  12.750   1.5680   0.04527   0.03661  -0.0461   0.2134   1.0000
  13.000   1.5588   0.04735   0.03892  -0.0432   0.2115   1.0000
  13.250   1.5340   0.05060   0.04248  -0.0400   0.2096   1.0000
  13.500   1.5051   0.05469   0.04685  -0.0379   0.2074   1.0000
  13.750   1.4688   0.06014   0.05256  -0.0372   0.2051   1.0000
  14.000   1.4226   0.06764   0.06030  -0.0383   0.2026   1.0000
  14.250   1.4074   0.07229   0.06507  -0.0393   0.2004   1.0000
  14.500   1.4513   0.06974   0.06249  -0.0375   0.1989   1.0000
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