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USA-35B AIRFOIL (usa35b-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: USA-35B AIRFOIL (usa35b-il)
Reynolds number: 50,000
Max Cl/Cd: 36.23 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa35b-il-50000-n5.txt
Download as CSV file: xf-usa35b-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA-35B AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3126   0.10078   0.09366  -0.0322   1.0000   0.1485
  -9.500  -0.3182   0.09862   0.09161  -0.0320   1.0000   0.1508
  -9.000  -0.3682   0.08907   0.08226  -0.0379   1.0000   0.0928
  -8.750  -0.3663   0.08663   0.07987  -0.0356   1.0000   0.0911
  -8.500  -0.3713   0.08400   0.07732  -0.0347   1.0000   0.0896
  -8.250  -0.3779   0.08116   0.07455  -0.0345   1.0000   0.0882
  -7.750  -0.3897   0.06976   0.06286  -0.0440   0.9974   0.0805
  -7.500  -0.3609   0.06531   0.05829  -0.0489   0.9888   0.0797
  -7.250  -0.3311   0.06072   0.05351  -0.0543   0.9796   0.0786
  -7.000  -0.2988   0.05587   0.04838  -0.0602   0.9706   0.0776
  -6.750  -0.2674   0.05131   0.04347  -0.0652   0.9604   0.0768
  -6.500  -0.2352   0.04721   0.03892  -0.0696   0.9501   0.0771
  -6.250  -0.1975   0.04337   0.03450  -0.0743   0.9419   0.0786
  -6.000  -0.1643   0.04031   0.03090  -0.0771   0.9311   0.0796
  -5.750  -0.1286   0.03769   0.02776  -0.0797   0.9218   0.0801
  -5.500  -0.0908   0.03538   0.02498  -0.0823   0.9130   0.0808
  -5.250  -0.0570   0.03363   0.02304  -0.0840   0.9028   0.0822
  -5.000  -0.0188   0.03221   0.02146  -0.0862   0.8948   0.0853
  -4.750   0.0124   0.03106   0.02007  -0.0870   0.8832   0.0889
  -4.500   0.0502   0.02974   0.01840  -0.0886   0.8751   0.0923
  -4.250   0.0813   0.02865   0.01717  -0.0890   0.8638   0.0951
  -4.000   0.1125   0.02778   0.01627  -0.0894   0.8534   0.0995
  -3.750   0.1473   0.02698   0.01526  -0.0902   0.8446   0.1074
  -3.500   0.1755   0.02633   0.01464  -0.0901   0.8329   0.1154
  -3.250   0.2092   0.02559   0.01383  -0.0908   0.8245   0.1280
  -3.000   0.2373   0.02507   0.01337  -0.0907   0.8132   0.1475
  -2.750   0.2662   0.02451   0.01294  -0.0908   0.8028   0.1845
  -2.500   0.2966   0.02347   0.01245  -0.0914   0.7940   0.2816
  -2.250   0.3133   0.02198   0.01251  -0.0889   0.7834   0.6150
  -2.000   0.3602   0.02114   0.01198  -0.0904   0.7757   1.0000
  -1.750   0.3853   0.02139   0.01193  -0.0899   0.7636   1.0000
  -1.500   0.4133   0.02153   0.01179  -0.0896   0.7534   1.0000
  -1.250   0.4420   0.02163   0.01164  -0.0894   0.7434   1.0000
  -1.000   0.4674   0.02186   0.01168  -0.0888   0.7317   1.0000
  -0.750   0.4961   0.02196   0.01156  -0.0885   0.7221   1.0000
  -0.500   0.5226   0.02216   0.01160  -0.0880   0.7112   1.0000
  -0.250   0.5483   0.02242   0.01171  -0.0874   0.7004   1.0000
   0.000   0.5779   0.02249   0.01162  -0.0872   0.6918   1.0000
   0.250   0.6018   0.02287   0.01190  -0.0865   0.6804   1.0000
   0.500   0.6295   0.02308   0.01199  -0.0861   0.6713   1.0000
   0.750   0.6556   0.02336   0.01219  -0.0856   0.6612   1.0000
   1.000   0.6810   0.02371   0.01247  -0.0851   0.6511   1.0000
   1.250   0.7094   0.02391   0.01258  -0.0847   0.6422   1.0000
   1.500   0.7329   0.02437   0.01301  -0.0840   0.6312   1.0000
   1.750   0.7617   0.02456   0.01312  -0.0837   0.6226   1.0000
   2.000   0.7847   0.02506   0.01363  -0.0829   0.6114   1.0000
   2.250   0.8101   0.02544   0.01399  -0.0823   0.6013   1.0000
   2.500   0.8365   0.02577   0.01430  -0.0817   0.5914   1.0000
   2.750   0.8590   0.02632   0.01488  -0.0809   0.5801   1.0000
   3.000   0.8871   0.02655   0.01505  -0.0804   0.5709   1.0000
   3.250   0.9086   0.02713   0.01572  -0.0795   0.5588   1.0000
   3.500   0.9317   0.02763   0.01625  -0.0786   0.5475   1.0000
   3.750   0.9596   0.02780   0.01638  -0.0780   0.5374   1.0000
   4.000   0.9795   0.02834   0.01702  -0.0767   0.5236   1.0000
   4.250   1.0007   0.02878   0.01750  -0.0755   0.5099   1.0000
   4.500   1.0228   0.02913   0.01788  -0.0743   0.4965   1.0000
   4.750   1.0460   0.02939   0.01817  -0.0732   0.4837   1.0000
   5.000   1.0687   0.02970   0.01851  -0.0721   0.4709   1.0000
   5.250   1.0874   0.03028   0.01918  -0.0707   0.4572   1.0000
   5.500   1.1067   0.03083   0.01984  -0.0693   0.4440   1.0000
   5.750   1.1268   0.03133   0.02039  -0.0680   0.4313   1.0000
   6.000   1.1482   0.03173   0.02083  -0.0668   0.4193   1.0000
   6.250   1.1680   0.03224   0.02140  -0.0655   0.4067   1.0000
   6.500   1.1847   0.03298   0.02226  -0.0639   0.3936   1.0000
   6.750   1.2021   0.03369   0.02306  -0.0625   0.3811   1.0000
   7.000   1.2207   0.03433   0.02374  -0.0610   0.3691   1.0000
   7.250   1.2414   0.03484   0.02425  -0.0598   0.3577   1.0000
   7.500   1.2547   0.03590   0.02546  -0.0580   0.3453   1.0000
   7.750   1.2697   0.03691   0.02657  -0.0564   0.3342   1.0000
   8.000   1.2892   0.03767   0.02733  -0.0552   0.3240   1.0000
   8.250   1.3008   0.03888   0.02871  -0.0533   0.3129   1.0000
   8.500   1.3109   0.04011   0.03004  -0.0514   0.3018   1.0000
   8.750   1.3225   0.04103   0.03097  -0.0493   0.2907   1.0000
   9.000   1.3266   0.04233   0.03236  -0.0468   0.2794   1.0000
   9.250   1.3263   0.04401   0.03417  -0.0443   0.2684   1.0000
   9.500   1.3285   0.04547   0.03567  -0.0420   0.2573   1.0000
   9.750   1.3303   0.04697   0.03721  -0.0400   0.2462   1.0000
  10.000   1.3232   0.04954   0.03996  -0.0382   0.2359   1.0000
  10.250   1.3213   0.05174   0.04223  -0.0368   0.2259   1.0000
  10.500   1.3211   0.05384   0.04436  -0.0356   0.2160   1.0000
  10.750   1.3134   0.05712   0.04784  -0.0349   0.2068   1.0000
  11.000   1.3123   0.05966   0.05042  -0.0342   0.1980   1.0000
  11.250   1.3071   0.06289   0.05380  -0.0339   0.1891   1.0000
  11.500   1.3011   0.06638   0.05742  -0.0338   0.1805   1.0000
  11.750   1.3005   0.06899   0.05998  -0.0335   0.1714   1.0000
  12.000   1.2875   0.07380   0.06504  -0.0342   0.1628   1.0000
  12.250   1.2817   0.07744   0.06872  -0.0345   0.1540   1.0000
  12.500   1.2739   0.08152   0.07287  -0.0350   0.1452   1.0000
  12.750   1.2616   0.08659   0.07808  -0.0361   0.1371   1.0000
  13.000   1.2600   0.08969   0.08108  -0.0363   0.1288   1.0000
  13.250   1.2417   0.09632   0.08798  -0.0385   0.1220   1.0000
  13.500   1.2427   0.09915   0.09070  -0.0387   0.1151   1.0000
  13.750   1.2221   0.10668   0.09852  -0.0417   0.1100   1.0000
  14.000   1.2174   0.11101   0.10289  -0.0429   0.1048   1.0000
  14.250   1.2078   0.11655   0.10850  -0.0450   0.1007   1.0000
  14.500   1.1774   0.12715   0.11936  -0.0504   0.0976   1.0000
  14.750   1.1562   0.13609   0.12842  -0.0550   0.0943   1.0000
  15.000   1.1705   0.13643   0.12870  -0.0543   0.0904   1.0000
  15.250   1.0972   0.16080   0.15320  -0.0688   0.0880   1.0000
  15.500   1.0750   0.17290   0.16525  -0.0757   0.0846   1.0000
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