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USA 40 B AIRFOIL (usa40b-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 40 B AIRFOIL (usa40b-il)
Reynolds number: 500,000
Max Cl/Cd: 85.11 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa40b-il-500000.txt
Download as CSV file: xf-usa40b-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3263   0.09109   0.08872  -0.0354   1.0000   0.0448
  -9.250  -0.3207   0.08936   0.08703  -0.0345   1.0000   0.0452
  -9.000  -0.5348   0.04149   0.03837  -0.0761   0.9917   0.0393
  -8.750  -0.5054   0.03974   0.03665  -0.0784   0.9881   0.0397
  -8.500  -0.4837   0.03274   0.02917  -0.0851   0.9833   0.0377
  -8.250  -0.4600   0.02774   0.02362  -0.0890   0.9769   0.0376
  -8.000  -0.4265   0.02421   0.01965  -0.0926   0.9720   0.0375
  -7.750  -0.3900   0.02179   0.01691  -0.0955   0.9666   0.0376
  -7.500  -0.3550   0.02000   0.01487  -0.0974   0.9595   0.0378
  -7.250  -0.3159   0.01852   0.01318  -0.0999   0.9558   0.0381
  -7.000  -0.2857   0.01748   0.01197  -0.1005   0.9470   0.0385
  -6.750  -0.2479   0.01652   0.01086  -0.1024   0.9413   0.0388
  -6.500  -0.2161   0.01536   0.00961  -0.1033   0.9306   0.0394
  -6.250  -0.1801   0.01451   0.00875  -0.1049   0.9201   0.0401
  -6.000  -0.1447   0.01391   0.00810  -0.1062   0.9066   0.0409
  -5.750  -0.1140   0.01338   0.00748  -0.1065   0.8883   0.0415
  -5.500  -0.0859   0.01293   0.00694  -0.1062   0.8665   0.0422
  -5.250  -0.0588   0.01253   0.00643  -0.1058   0.8415   0.0429
  -5.000  -0.0324   0.01221   0.00596  -0.1051   0.8146   0.0435
  -4.750  -0.0066   0.01195   0.00555  -0.1043   0.7876   0.0442
  -4.500   0.0180   0.01151   0.00501  -0.1035   0.7648   0.0453
  -4.250   0.0437   0.01130   0.00472  -0.1028   0.7457   0.0465
  -4.000   0.0698   0.01114   0.00447  -0.1021   0.7282   0.0479
  -3.750   0.0962   0.01102   0.00424  -0.1015   0.7119   0.0496
  -3.500   0.1221   0.01074   0.00393  -0.1009   0.6969   0.0517
  -3.250   0.1485   0.01061   0.00374  -0.1003   0.6821   0.0542
  -3.000   0.1748   0.01044   0.00350  -0.0996   0.6659   0.0575
  -2.750   0.2012   0.01031   0.00333  -0.0990   0.6477   0.0623
  -2.500   0.2273   0.01015   0.00313  -0.0984   0.6267   0.0704
  -2.250   0.2532   0.00998   0.00293  -0.0977   0.6019   0.0830
  -2.000   0.2783   0.00987   0.00276  -0.0970   0.5731   0.0987
  -1.750   0.3031   0.00976   0.00264  -0.0962   0.5390   0.1285
  -1.500   0.3273   0.00971   0.00263  -0.0954   0.5016   0.1868
  -1.250   0.3521   0.00981   0.00263  -0.0946   0.4661   0.2169
  -1.000   0.3772   0.00988   0.00264  -0.0940   0.4365   0.2444
  -0.750   0.4026   0.00991   0.00266  -0.0934   0.4133   0.2809
  -0.500   0.4281   0.00987   0.00271  -0.0928   0.3950   0.3433
  -0.250   0.4537   0.00978   0.00277  -0.0923   0.3800   0.4204
   0.000   0.4787   0.00965   0.00286  -0.0917   0.3672   0.5125
   0.250   0.5033   0.00961   0.00301  -0.0908   0.3554   0.6017
   0.500   0.5292   0.00966   0.00314  -0.0901   0.3454   0.6552
   1.000   0.5809   0.00990   0.00338  -0.0886   0.3278   0.7166
   1.250   0.6065   0.01006   0.00351  -0.0879   0.3200   0.7381
   1.500   0.6328   0.01018   0.00362  -0.0873   0.3134   0.7557
   1.750   0.6587   0.01030   0.00373  -0.0866   0.3069   0.7732
   2.000   0.6837   0.01050   0.00387  -0.0857   0.3003   0.7895
   2.250   0.7101   0.01057   0.00396  -0.0852   0.2953   0.8046
   2.500   0.7357   0.01067   0.00406  -0.0844   0.2897   0.8191
   2.750   0.7601   0.01083   0.00419  -0.0835   0.2839   0.8352
   3.000   0.7857   0.01090   0.00429  -0.0828   0.2796   0.8513
   3.250   0.8109   0.01093   0.00438  -0.0820   0.2752   0.8723
   3.500   0.8410   0.01094   0.00449  -0.0823   0.2707   0.9177
   3.750   0.8781   0.01124   0.00471  -0.0843   0.2654   1.0000
   4.000   0.9056   0.01138   0.00485  -0.0841   0.2624   1.0000
   4.250   0.9325   0.01156   0.00500  -0.0838   0.2589   1.0000
   4.500   0.9588   0.01177   0.00517  -0.0834   0.2555   1.0000
   4.750   0.9844   0.01205   0.00538  -0.0829   0.2521   1.0000
   5.000   1.0095   0.01237   0.00565  -0.0823   0.2486   1.0000
   5.250   1.0361   0.01254   0.00583  -0.0820   0.2463   1.0000
   5.500   1.0622   0.01273   0.00602  -0.0815   0.2435   1.0000
   5.750   1.0878   0.01295   0.00622  -0.0810   0.2407   1.0000
   6.000   1.1129   0.01321   0.00645  -0.0805   0.2380   1.0000
   6.250   1.1373   0.01355   0.00674  -0.0798   0.2353   1.0000
   6.500   1.1617   0.01393   0.00710  -0.0792   0.2327   1.0000
   6.750   1.1872   0.01412   0.00732  -0.0786   0.2309   1.0000
   7.000   1.2123   0.01433   0.00756  -0.0781   0.2286   1.0000
   7.250   1.2371   0.01457   0.00781  -0.0775   0.2264   1.0000
   7.500   1.2614   0.01482   0.00805  -0.0768   0.2240   1.0000
   7.750   1.2851   0.01512   0.00834  -0.0761   0.2218   1.0000
   8.000   1.3083   0.01553   0.00872  -0.0753   0.2195   1.0000
   8.250   1.3317   0.01601   0.00919  -0.0746   0.2174   1.0000
   8.500   1.3556   0.01624   0.00948  -0.0739   0.2162   1.0000
   8.750   1.3791   0.01650   0.00979  -0.0731   0.2146   1.0000
   9.000   1.4022   0.01677   0.01009  -0.0723   0.2127   1.0000
   9.250   1.4248   0.01704   0.01040  -0.0714   0.2107   1.0000
   9.500   1.4471   0.01735   0.01073  -0.0705   0.2090   1.0000
   9.750   1.4688   0.01769   0.01108  -0.0695   0.2073   1.0000
  10.000   1.4899   0.01810   0.01148  -0.0685   0.2053   1.0000
  10.250   1.5116   0.01871   0.01208  -0.0677   0.2031   1.0000
  10.500   1.5324   0.01907   0.01251  -0.0666   0.2020   1.0000
  10.750   1.5517   0.01937   0.01289  -0.0652   0.2008   1.0000
  11.000   1.5704   0.01971   0.01329  -0.0637   0.1995   1.0000
  11.250   1.5887   0.02007   0.01372  -0.0622   0.1981   1.0000
  11.500   1.6063   0.02042   0.01412  -0.0607   0.1964   1.0000
  11.750   1.6226   0.02074   0.01448  -0.0589   0.1943   1.0000
  12.000   1.6379   0.02109   0.01484  -0.0571   0.1919   1.0000
  12.250   1.6539   0.02170   0.01543  -0.0556   0.1891   1.0000
  12.500   1.6686   0.02212   0.01594  -0.0538   0.1871   1.0000
  12.750   1.6831   0.02250   0.01642  -0.0521   0.1850   1.0000
  13.000   1.6974   0.02292   0.01693  -0.0504   0.1826   1.0000
  13.250   1.7112   0.02340   0.01747  -0.0488   0.1801   1.0000
  13.500   1.7238   0.02401   0.01810  -0.0471   0.1777   1.0000
  13.750   1.7351   0.02483   0.01892  -0.0454   0.1751   1.0000
  14.000   1.7480   0.02548   0.01969  -0.0440   0.1729   1.0000
  14.250   1.7609   0.02613   0.02045  -0.0426   0.1702   1.0000
  14.500   1.7729   0.02689   0.02129  -0.0413   0.1672   1.0000
  14.750   1.7822   0.02787   0.02229  -0.0399   0.1640   1.0000
  15.000   1.7895   0.02907   0.02353  -0.0385   0.1609   1.0000
  15.250   1.8023   0.02996   0.02455  -0.0376   0.1575   1.0000
  15.500   1.8111   0.03116   0.02583  -0.0366   0.1534   1.0000
  15.750   1.8152   0.03281   0.02749  -0.0355   0.1497   1.0000
  16.000   1.8241   0.03418   0.02897  -0.0348   0.1458   1.0000
  16.250   1.8294   0.03590   0.03077  -0.0341   0.1408   1.0000
  16.500   1.8294   0.03819   0.03309  -0.0335   0.1361   1.0000
  16.750   1.8315   0.04039   0.03537  -0.0331   0.1294   1.0000
  17.000   1.8267   0.04337   0.03840  -0.0328   0.1235   1.0000
  17.250   1.8185   0.04686   0.04193  -0.0329   0.1164   1.0000
  17.500   1.8065   0.05095   0.04608  -0.0332   0.1102   1.0000
  18.000   1.7685   0.06158   0.05687  -0.0355   0.1004   1.0000
  18.250   1.7442   0.06805   0.06343  -0.0375   0.0969   1.0000
  18.500   1.7160   0.07538   0.07088  -0.0401   0.0944   1.0000
  18.750   1.6900   0.08264   0.07827  -0.0428   0.0920   1.0000
  19.000   1.6607   0.09059   0.08635  -0.0461   0.0900   1.0000
  19.250   1.6298   0.09900   0.09487  -0.0497   0.0881   1.0000
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