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USA 35 AIRFOIL (usa35-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: USA 35 AIRFOIL (usa35-il)
Reynolds number: 200,000
Max Cl/Cd: 66.51 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa35-il-200000.txt
Download as CSV file: xf-usa35-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 35 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750   0.0499   0.10062   0.09679  -0.0950   0.9146   0.0736
  -9.500   0.0542   0.09804   0.09419  -0.0955   0.9013   0.0752
  -9.250   0.0309   0.09349   0.08962  -0.1016   0.8875   0.0775
  -9.000   0.0477   0.09126   0.08732  -0.0994   0.8779   0.0779
  -8.750   0.0611   0.08920   0.08526  -0.0982   0.8650   0.0786
  -8.500   0.0710   0.08703   0.08304  -0.0978   0.8538   0.0797
  -8.250   0.0776   0.08460   0.08057  -0.0982   0.8416   0.0813
  -8.000   0.0505   0.07871   0.07465  -0.1071   0.8281   0.0848
  -7.750   0.0695   0.07709   0.07296  -0.1043   0.8180   0.0854
  -7.500   0.0848   0.07547   0.07132  -0.1030   0.8051   0.0864
  -7.250   0.0517   0.06725   0.06295  -0.1204   0.7925   0.0925
  -7.000   0.0679   0.06562   0.06135  -0.1171   0.7805   0.0930
  -6.750   0.0854   0.06464   0.06033  -0.1138   0.7690   0.0936
  -6.500   0.0730   0.05652   0.05176  -0.1282   0.7579   0.1014
  -6.250   0.0934   0.05466   0.04999  -0.1263   0.7464   0.1019
  -6.000   0.1123   0.05337   0.04868  -0.1246   0.7357   0.1026
  -5.750   0.1297   0.05201   0.04731  -0.1237   0.7247   0.1038
  -5.500   0.1084   0.03244   0.02585  -0.1337   0.7195   0.0772
  -5.250   0.1308   0.03020   0.02330  -0.1337   0.7114   0.0769
  -5.000   0.1522   0.02817   0.02105  -0.1333   0.7012   0.0766
  -4.750   0.1760   0.02626   0.01871  -0.1330   0.6933   0.0766
  -4.500   0.2001   0.02479   0.01685  -0.1325   0.6847   0.0770
  -4.250   0.2254   0.02353   0.01541  -0.1323   0.6766   0.0781
  -4.000   0.2533   0.02298   0.01481  -0.1324   0.6702   0.0800
  -3.750   0.2789   0.02227   0.01397  -0.1320   0.6623   0.0821
  -3.500   0.3061   0.02151   0.01288  -0.1316   0.6553   0.0839
  -3.250   0.3338   0.02070   0.01187  -0.1315   0.6486   0.0856
  -3.000   0.3598   0.02018   0.01139  -0.1311   0.6404   0.0878
  -2.750   0.3875   0.01977   0.01081  -0.1309   0.6335   0.0910
  -2.500   0.4155   0.01928   0.01019  -0.1308   0.6276   0.0940
  -2.250   0.4421   0.01891   0.00986  -0.1305   0.6213   0.0970
  -2.000   0.4700   0.01864   0.00947  -0.1303   0.6157   0.1007
  -1.750   0.4983   0.01824   0.00907  -0.1303   0.6109   0.1048
  -1.500   0.5254   0.01805   0.00887  -0.1301   0.6057   0.1093
  -1.250   0.5519   0.01773   0.00862  -0.1298   0.6000   0.1141
  -1.000   0.5796   0.01756   0.00843  -0.1296   0.5948   0.1203
  -0.750   0.6082   0.01735   0.00821  -0.1297   0.5904   0.1272
  -0.500   0.6349   0.01722   0.00815  -0.1294   0.5856   0.1361
  -0.250   0.6613   0.01708   0.00810  -0.1291   0.5804   0.1482
   0.000   0.6887   0.01691   0.00803  -0.1290   0.5753   0.1697
   0.250   0.7167   0.01656   0.00796  -0.1291   0.5706   0.2486
   0.500   0.7409   0.01605   0.00816  -0.1288   0.5658   0.4434
   0.750   0.7593   0.01543   0.00842  -0.1268   0.5608   0.6888
   1.000   0.8034   0.01505   0.00848  -0.1287   0.5553   1.0000
   1.250   0.8311   0.01526   0.00849  -0.1287   0.5508   1.0000
   1.500   0.8572   0.01554   0.00865  -0.1283   0.5460   1.0000
   1.750   0.8811   0.01574   0.00881  -0.1276   0.5403   1.0000
   2.000   0.9073   0.01592   0.00888  -0.1272   0.5349   1.0000
   2.250   0.9357   0.01615   0.00893  -0.1273   0.5299   1.0000
   2.500   0.9604   0.01643   0.00917  -0.1267   0.5245   1.0000
   2.750   0.9845   0.01664   0.00936  -0.1261   0.5187   1.0000
   3.000   1.0111   0.01684   0.00946  -0.1258   0.5133   1.0000
   3.250   1.0406   0.01715   0.00959  -0.1261   0.5084   1.0000
   3.500   1.0623   0.01741   0.00990  -0.1250   0.5025   1.0000
   3.750   1.0864   0.01762   0.01008  -0.1244   0.4964   1.0000
   4.000   1.1137   0.01782   0.01016  -0.1243   0.4910   1.0000
   4.250   1.1391   0.01814   0.01042  -0.1239   0.4854   1.0000
   4.500   1.1604   0.01838   0.01069  -0.1228   0.4788   1.0000
   4.750   1.1858   0.01858   0.01082  -0.1224   0.4732   1.0000
   5.000   1.2152   0.01888   0.01096  -0.1228   0.4681   1.0000
   5.250   1.2325   0.01914   0.01133  -0.1210   0.4614   1.0000
   5.500   1.2554   0.01933   0.01148  -0.1202   0.4552   1.0000
   5.750   1.2830   0.01953   0.01152  -0.1202   0.4499   1.0000
   6.000   1.2998   0.01982   0.01191  -0.1184   0.4431   1.0000
   6.250   1.3208   0.02004   0.01211  -0.1172   0.4370   1.0000
   6.500   1.3464   0.02026   0.01221  -0.1170   0.4321   1.0000
   6.750   1.3644   0.02062   0.01263  -0.1154   0.4262   1.0000
   7.000   1.3823   0.02090   0.01293  -0.1139   0.4201   1.0000
   7.250   1.4046   0.02112   0.01305  -0.1131   0.4149   1.0000
   7.500   1.4234   0.02151   0.01345  -0.1117   0.4096   1.0000
   7.750   1.4381   0.02190   0.01390  -0.1097   0.4043   1.0000
   8.000   1.4560   0.02224   0.01421  -0.1082   0.3996   1.0000
   8.250   1.4828   0.02256   0.01440  -0.1083   0.3953   1.0000
   8.500   1.4914   0.02313   0.01509  -0.1054   0.3904   1.0000
   8.750   1.5053   0.02361   0.01562  -0.1034   0.3855   1.0000
   9.000   1.5242   0.02402   0.01597  -0.1023   0.3810   1.0000
   9.250   1.5462   0.02449   0.01638  -0.1017   0.3767   1.0000
   9.500   1.5548   0.02520   0.01721  -0.0992   0.3720   1.0000
   9.750   1.5688   0.02581   0.01785  -0.0975   0.3675   1.0000
  10.000   1.5887   0.02628   0.01826  -0.0967   0.3633   1.0000
  10.250   1.6075   0.02690   0.01886  -0.0958   0.3591   1.0000
  10.500   1.6139   0.02781   0.01989  -0.0933   0.3545   1.0000
  10.750   1.6261   0.02856   0.02068  -0.0917   0.3499   1.0000
  11.000   1.6473   0.02905   0.02108  -0.0911   0.3455   1.0000
  11.250   1.6572   0.03000   0.02210  -0.0893   0.3410   1.0000
  11.500   1.6615   0.03115   0.02335  -0.0870   0.3361   1.0000
  11.750   1.6731   0.03201   0.02423  -0.0855   0.3314   1.0000
  12.000   1.6993   0.03239   0.02448  -0.0856   0.3268   1.0000
  12.250   1.6933   0.03412   0.02641  -0.0826   0.3222   1.0000
  12.500   1.6981   0.03542   0.02778  -0.0807   0.3172   1.0000
  12.750   1.7147   0.03614   0.02844  -0.0799   0.3124   1.0000
  13.000   1.7196   0.03760   0.02997  -0.0782   0.3075   1.0000
  13.250   1.7162   0.03953   0.03204  -0.0761   0.3022   1.0000
  13.500   1.7256   0.04070   0.03319  -0.0749   0.2972   1.0000
  13.750   1.7345   0.04202   0.03451  -0.0737   0.2920   1.0000
  14.000   1.7245   0.04464   0.03729  -0.0716   0.2862   1.0000
  14.250   1.7312   0.04609   0.03873  -0.0706   0.2810   1.0000
  14.500   1.7361   0.04781   0.04046  -0.0694   0.2757   1.0000
  14.750   1.7257   0.05087   0.04368  -0.0679   0.2700   1.0000
  15.000   1.7331   0.05242   0.04521  -0.0671   0.2652   1.0000
  15.250   1.7387   0.05423   0.04703  -0.0663   0.2605   1.0000
  15.500   1.7271   0.05776   0.05072  -0.0653   0.2553   1.0000
  15.750   1.7319   0.05971   0.05268  -0.0646   0.2511   1.0000
  16.000   1.7552   0.05977   0.05262  -0.0642   0.2474   1.0000
  16.250   1.7339   0.06458   0.05768  -0.0634   0.2431   1.0000
  16.500   1.7303   0.06759   0.06078  -0.0630   0.2391   1.0000
  16.750   1.7391   0.06917   0.06235  -0.0627   0.2357   1.0000
  17.000   1.7535   0.07013   0.06326  -0.0622   0.2322   1.0000
  17.250   1.7315   0.07543   0.06879  -0.0621   0.2285   1.0000
  17.500   1.7263   0.07881   0.07228  -0.0621   0.2249   1.0000
  17.750   1.7356   0.08037   0.07382  -0.0620   0.2218   1.0000
  18.000   1.7586   0.08020   0.07354  -0.0615   0.2188   1.0000
  18.250   1.7296   0.08669   0.08031  -0.0620   0.2158   1.0000
  18.500   1.7142   0.09157   0.08535  -0.0625   0.2127   1.0000
  18.750   1.7161   0.09417   0.08801  -0.0627   0.2099   1.0000
  19.000   1.7333   0.09467   0.08847  -0.0625   0.2075   1.0000
  19.250   1.7487   0.09538   0.08915  -0.0623   0.2049   1.0000
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