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USA 40 B AIRFOIL (usa40b-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: USA 40 B AIRFOIL (usa40b-il)
Reynolds number: 200,000
Max Cl/Cd: 56.44 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa40b-il-200000.txt
Download as CSV file: xf-usa40b-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2792   0.09735   0.09372  -0.0311   1.0000   0.0759
  -8.750  -0.2809   0.09471   0.09112  -0.0314   1.0000   0.0780
  -8.500  -0.3464   0.08987   0.08646  -0.0386   1.0000   0.0808
  -8.250  -0.3328   0.08679   0.08340  -0.0356   1.0000   0.0815
  -8.000  -0.3172   0.08541   0.08206  -0.0323   1.0000   0.0824
  -7.750  -0.3163   0.08391   0.08063  -0.0298   1.0000   0.0832
  -7.500  -0.3236   0.08254   0.07933  -0.0271   1.0000   0.0840
  -7.250  -0.3415   0.08144   0.07832  -0.0237   1.0000   0.0846
  -7.000  -0.3371   0.06554   0.06228  -0.0563   0.9839   0.0923
  -6.750  -0.3016   0.06406   0.06086  -0.0560   0.9786   0.0933
  -6.500  -0.2689   0.06172   0.05853  -0.0584   0.9721   0.0952
  -6.000  -0.2306   0.02884   0.02273  -0.0906   0.9448   0.0635
  -5.750  -0.1894   0.02600   0.01963  -0.0939   0.9409   0.0631
  -5.500  -0.1556   0.02398   0.01733  -0.0952   0.9311   0.0631
  -5.250  -0.1131   0.02215   0.01520  -0.0980   0.9259   0.0635
  -5.000  -0.0790   0.02038   0.01333  -0.0992   0.9155   0.0643
  -4.750  -0.0380   0.01919   0.01213  -0.1015   0.9078   0.0662
  -4.500  -0.0049   0.01833   0.01119  -0.1021   0.8939   0.0682
  -4.250   0.0293   0.01746   0.01016  -0.1027   0.8796   0.0702
  -4.000   0.0622   0.01664   0.00918  -0.1031   0.8640   0.0719
  -3.750   0.0922   0.01570   0.00830  -0.1031   0.8466   0.0744
  -3.500   0.1213   0.01512   0.00768  -0.1028   0.8278   0.0777
  -3.250   0.1494   0.01455   0.00702  -0.1023   0.8080   0.0821
  -3.000   0.1766   0.01404   0.00651  -0.1017   0.7879   0.0883
  -2.750   0.2032   0.01350   0.00594  -0.1011   0.7678   0.0963
  -2.500   0.2294   0.01304   0.00545  -0.1003   0.7475   0.1099
  -2.250   0.2551   0.01264   0.00509  -0.0996   0.7269   0.1357
  -2.000   0.2806   0.01232   0.00492  -0.0988   0.7060   0.1950
  -1.750   0.3054   0.01204   0.00477  -0.0980   0.6845   0.2581
  -1.500   0.3297   0.01181   0.00470  -0.0971   0.6603   0.3170
  -1.250   0.3534   0.01160   0.00464  -0.0960   0.6330   0.3909
  -1.000   0.3759   0.01138   0.00462  -0.0946   0.6016   0.4786
  -0.750   0.3970   0.01129   0.00470  -0.0928   0.5659   0.5738
  -0.500   0.4180   0.01142   0.00480  -0.0908   0.5290   0.6432
  -0.250   0.4395   0.01168   0.00492  -0.0890   0.4965   0.6937
   0.000   0.4611   0.01196   0.00506  -0.0872   0.4692   0.7335
   0.250   0.4827   0.01224   0.00519  -0.0854   0.4476   0.7662
   0.500   0.5043   0.01245   0.00531  -0.0836   0.4297   0.7949
   0.750   0.5262   0.01261   0.00539  -0.0819   0.4145   0.8230
   1.000   0.5481   0.01272   0.00544  -0.0803   0.4020   0.8497
   1.250   0.5705   0.01283   0.00546  -0.0788   0.3910   0.8788
   1.500   0.6016   0.01286   0.00551  -0.0790   0.3796   0.9150
   1.750   0.6451   0.01315   0.00565  -0.0822   0.3684   1.0000
   2.000   0.6730   0.01343   0.00581  -0.0823   0.3592   1.0000
   2.250   0.7008   0.01381   0.00602  -0.0824   0.3514   1.0000
   2.500   0.7284   0.01408   0.00621  -0.0824   0.3438   1.0000
   2.750   0.7559   0.01446   0.00643  -0.0823   0.3374   1.0000
   3.000   0.7834   0.01480   0.00670  -0.0822   0.3313   1.0000
   3.250   0.8105   0.01510   0.00694  -0.0820   0.3253   1.0000
   3.500   0.8377   0.01549   0.00720  -0.0819   0.3201   1.0000
   3.750   0.8648   0.01591   0.00755  -0.0817   0.3150   1.0000
   4.000   0.8914   0.01620   0.00783  -0.0814   0.3098   1.0000
   4.250   0.9181   0.01654   0.00810  -0.0811   0.3052   1.0000
   4.500   0.9454   0.01705   0.00847  -0.0810   0.3011   1.0000
   4.750   0.9719   0.01746   0.00889  -0.0807   0.2974   1.0000
   5.000   0.9981   0.01781   0.00927  -0.0804   0.2935   1.0000
   5.250   1.0244   0.01819   0.00963  -0.0801   0.2899   1.0000
   5.500   1.0510   0.01862   0.00999  -0.0798   0.2866   1.0000
   5.750   1.0786   0.01923   0.01050  -0.0798   0.2835   1.0000
   6.000   1.1044   0.01973   0.01104  -0.0794   0.2807   1.0000
   6.250   1.1294   0.02012   0.01151  -0.0789   0.2776   1.0000
   6.500   1.1546   0.02054   0.01197  -0.0785   0.2744   1.0000
   6.750   1.1804   0.02099   0.01240  -0.0781   0.2716   1.0000
   7.000   1.2067   0.02149   0.01287  -0.0779   0.2692   1.0000
   7.250   1.2338   0.02218   0.01350  -0.0779   0.2669   1.0000
   7.500   1.2592   0.02292   0.01429  -0.0776   0.2647   1.0000
   7.750   1.2828   0.02345   0.01494  -0.0769   0.2627   1.0000
   8.000   1.3063   0.02403   0.01564  -0.0763   0.2604   1.0000
   8.250   1.3301   0.02464   0.01632  -0.0757   0.2582   1.0000
   8.500   1.3541   0.02516   0.01689  -0.0751   0.2558   1.0000
   8.750   1.3788   0.02562   0.01733  -0.0747   0.2533   1.0000
   9.000   1.4051   0.02622   0.01786  -0.0746   0.2506   1.0000
   9.250   1.4279   0.02707   0.01878  -0.0740   0.2481   1.0000
   9.500   1.4481   0.02771   0.01959  -0.0730   0.2462   1.0000
   9.750   1.4688   0.02844   0.02047  -0.0720   0.2442   1.0000
  10.000   1.4893   0.02914   0.02128  -0.0711   0.2420   1.0000
  10.250   1.5103   0.02974   0.02196  -0.0702   0.2397   1.0000
  10.500   1.5330   0.03026   0.02251  -0.0696   0.2374   1.0000
  10.750   1.5581   0.03082   0.02303  -0.0693   0.2352   1.0000
  11.000   1.5818   0.03190   0.02411  -0.0691   0.2328   1.0000
  11.250   1.5950   0.03262   0.02507  -0.0671   0.2307   1.0000
  11.500   1.6096   0.03345   0.02609  -0.0655   0.2285   1.0000
  11.750   1.6249   0.03428   0.02707  -0.0640   0.2262   1.0000
  12.000   1.6414   0.03501   0.02791  -0.0626   0.2240   1.0000
  12.250   1.6603   0.03562   0.02858  -0.0616   0.2220   1.0000
  12.500   1.6839   0.03617   0.02911  -0.0612   0.2199   1.0000
  12.750   1.7098   0.03730   0.03021  -0.0614   0.2175   1.0000
  13.000   1.7100   0.03833   0.03153  -0.0580   0.2155   1.0000
  13.250   1.7116   0.03936   0.03278  -0.0549   0.2130   1.0000
  13.500   1.7140   0.04010   0.03365  -0.0517   0.2102   1.0000
  13.750   1.7232   0.04039   0.03399  -0.0493   0.2075   1.0000
  14.000   1.7609   0.03974   0.03313  -0.0504   0.2036   1.0000
  14.250   1.2459   0.09740   0.09263  -0.0521   0.1986   1.0000
  14.500   1.2810   0.09441   0.08967  -0.0498   0.1976   1.0000
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