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USA 45 AIRFOIL (usa45-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 45 AIRFOIL (usa45-il)
Reynolds number: 500,000
Max Cl/Cd: 90.05 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa45-il-500000.txt
Download as CSV file: xf-usa45-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 45 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3300   0.08899   0.08687  -0.0377   1.0000   0.0333
  -9.750  -0.3345   0.08495   0.08286  -0.0393   1.0000   0.0346
  -9.500  -0.6005   0.03568   0.03225  -0.0599   0.9849   0.0263
  -9.250  -0.5113   0.04696   0.04439  -0.0616   0.9876   0.0315
  -9.000  -0.4907   0.04338   0.04073  -0.0641   0.9819   0.0292
  -8.750  -0.5095   0.03203   0.02845  -0.0654   0.9693   0.0285
  -8.500  -0.4939   0.02820   0.02410  -0.0655   0.9581   0.0295
  -8.250  -0.4705   0.02600   0.02143  -0.0657   0.9473   0.0305
  -8.000  -0.4484   0.02304   0.01803  -0.0659   0.9353   0.0312
  -7.750  -0.4216   0.02121   0.01604  -0.0663   0.9209   0.0319
  -7.500  -0.3941   0.02053   0.01531  -0.0664   0.9030   0.0328
  -7.250  -0.3690   0.01978   0.01443  -0.0659   0.8815   0.0337
  -7.000  -0.3454   0.01894   0.01337  -0.0650   0.8596   0.0346
  -6.750  -0.3229   0.01805   0.01225  -0.0638   0.8363   0.0352
  -6.500  -0.3002   0.01733   0.01129  -0.0626   0.8115   0.0358
  -6.250  -0.2773   0.01693   0.01066  -0.0613   0.7848   0.0365
  -6.000  -0.2553   0.01585   0.00935  -0.0601   0.7587   0.0373
  -5.750  -0.2328   0.01502   0.00839  -0.0589   0.7313   0.0381
  -5.500  -0.2100   0.01453   0.00777  -0.0578   0.7044   0.0388
  -5.250  -0.1872   0.01416   0.00725  -0.0567   0.6765   0.0396
  -5.000  -0.1644   0.01384   0.00678  -0.0555   0.6471   0.0405
  -4.750  -0.1413   0.01358   0.00637  -0.0544   0.6179   0.0416
  -4.500  -0.1183   0.01333   0.00596  -0.0533   0.5889   0.0425
  -4.250  -0.0952   0.01311   0.00558  -0.0521   0.5617   0.0432
  -4.000  -0.0717   0.01292   0.00524  -0.0511   0.5368   0.0437
  -3.750  -0.0505   0.01244   0.00464  -0.0497   0.5163   0.0452
  -3.500  -0.0272   0.01222   0.00434  -0.0488   0.4984   0.0466
  -3.250  -0.0031   0.01210   0.00412  -0.0479   0.4831   0.0486
  -3.000   0.0216   0.01197   0.00391  -0.0471   0.4699   0.0505
  -2.750   0.0463   0.01182   0.00368  -0.0463   0.4592   0.0526
  -2.500   0.0704   0.01166   0.00347  -0.0455   0.4501   0.0567
  -2.250   0.0957   0.01152   0.00331  -0.0448   0.4418   0.0631
  -2.000   0.1195   0.01133   0.00315  -0.0439   0.4345   0.0848
  -1.750   0.1421   0.01090   0.00302  -0.0430   0.4279   0.1599
  -1.500   0.1648   0.01062   0.00295  -0.0420   0.4214   0.2365
  -1.250   0.1864   0.01024   0.00290  -0.0409   0.4157   0.3401
  -1.000   0.2064   0.00976   0.00285  -0.0394   0.4101   0.4664
  -0.750   0.2215   0.00922   0.00285  -0.0368   0.4053   0.6352
  -0.500   0.2384   0.00888   0.00293  -0.0342   0.4008   0.7642
  -0.250   0.2624   0.00875   0.00305  -0.0329   0.3962   0.8495
   0.000   0.2932   0.00882   0.00317  -0.0331   0.3913   0.8953
   0.250   0.3300   0.00905   0.00333  -0.0346   0.3860   0.9262
   0.500   0.3742   0.00925   0.00351  -0.0376   0.3813   0.9479
   0.750   0.4160   0.00947   0.00364  -0.0403   0.3761   0.9581
   1.000   0.4586   0.00976   0.00381  -0.0432   0.3714   0.9655
   1.250   0.5040   0.00997   0.00397  -0.0467   0.3674   0.9719
   1.500   0.5488   0.01013   0.00407  -0.0501   0.3630   0.9768
   1.750   0.5882   0.01031   0.00417  -0.0525   0.3590   0.9829
   2.000   0.6333   0.01052   0.00427  -0.0562   0.3542   0.9864
   2.250   0.6777   0.01061   0.00435  -0.0597   0.3508   0.9913
   2.500   0.7172   0.01069   0.00440  -0.0622   0.3472   0.9947
   2.750   0.7551   0.01075   0.00441  -0.0645   0.3438   0.9976
   3.000   0.7916   0.01090   0.00447  -0.0665   0.3401   1.0000
   3.250   0.8123   0.01099   0.00455  -0.0653   0.3373   1.0000
   3.500   0.8332   0.01105   0.00462  -0.0641   0.3347   1.0000
   3.750   0.8540   0.01113   0.00470  -0.0628   0.3320   1.0000
   4.000   0.8746   0.01122   0.00479  -0.0615   0.3293   1.0000
   4.250   0.8949   0.01136   0.00489  -0.0601   0.3266   1.0000
   4.500   0.9149   0.01161   0.00507  -0.0588   0.3233   1.0000
   4.750   0.9358   0.01169   0.00520  -0.0575   0.3213   1.0000
   5.000   0.9566   0.01180   0.00533  -0.0562   0.3188   1.0000
   5.250   0.9773   0.01192   0.00546  -0.0549   0.3162   1.0000
   5.500   0.9980   0.01206   0.00560  -0.0535   0.3135   1.0000
   5.750   1.0185   0.01225   0.00576  -0.0522   0.3107   1.0000
   6.000   1.0391   0.01250   0.00598  -0.0509   0.3075   1.0000
   6.250   1.0600   0.01258   0.00612  -0.0497   0.3047   1.0000
   6.500   1.0809   0.01268   0.00626  -0.0484   0.3013   1.0000
   6.750   1.1017   0.01281   0.00639  -0.0471   0.2980   1.0000
   7.000   1.1218   0.01304   0.00657  -0.0458   0.2942   1.0000
   7.250   1.1425   0.01316   0.00674  -0.0445   0.2903   1.0000
   7.500   1.1634   0.01324   0.00687  -0.0433   0.2861   1.0000
   7.750   1.1837   0.01340   0.00702  -0.0420   0.2822   1.0000
   8.000   1.2030   0.01368   0.00726  -0.0406   0.2783   1.0000
   8.250   1.2242   0.01376   0.00743  -0.0394   0.2744   1.0000
   8.500   1.2447   0.01389   0.00760  -0.0382   0.2698   1.0000
   8.750   1.2633   0.01412   0.00780  -0.0367   0.2651   1.0000
   9.000   1.2832   0.01431   0.00805  -0.0354   0.2610   1.0000
   9.250   1.3030   0.01447   0.00825  -0.0341   0.2554   1.0000
   9.500   1.3193   0.01474   0.00850  -0.0322   0.2487   1.0000
   9.750   1.3385   0.01492   0.00872  -0.0309   0.2407   1.0000
  10.000   1.3521   0.01522   0.00902  -0.0285   0.2333   1.0000
  10.250   1.3650   0.01555   0.00934  -0.0261   0.2225   1.0000
  10.500   1.3751   0.01605   0.00977  -0.0234   0.2066   1.0000
  10.750   1.3789   0.01690   0.01046  -0.0200   0.1813   1.0000
  11.000   1.3734   0.01829   0.01164  -0.0156   0.1485   1.0000
  11.250   1.3632   0.02009   0.01324  -0.0112   0.1190   1.0000
  11.500   1.3492   0.02230   0.01529  -0.0071   0.0905   1.0000
  11.750   1.3196   0.02591   0.01871  -0.0029   0.0480   1.0000
  12.000   1.3006   0.02944   0.02223  -0.0009   0.0281   1.0000
  12.250   1.2954   0.03221   0.02508  -0.0001   0.0240   1.0000
  12.500   1.2960   0.03464   0.02762   0.0002   0.0229   1.0000
  12.750   1.2923   0.03768   0.03077   0.0002   0.0216   1.0000
  13.000   1.2873   0.04106   0.03427  -0.0001   0.0209   1.0000
  13.250   1.2778   0.04509   0.03843  -0.0007   0.0202   1.0000
  13.500   1.2666   0.04946   0.04294  -0.0015   0.0196   1.0000
  13.750   1.2567   0.05377   0.04736  -0.0024   0.0194   1.0000
  14.000   1.2452   0.05833   0.05205  -0.0034   0.0191   1.0000
  14.250   1.2342   0.06286   0.05669  -0.0044   0.0186   1.0000
  14.500   1.2206   0.06776   0.06172  -0.0056   0.0186   1.0000
  14.750   1.2076   0.07269   0.06675  -0.0068   0.0182   1.0000
  15.000   1.1948   0.07763   0.07181  -0.0080   0.0179   1.0000
  15.250   1.1826   0.08259   0.07687  -0.0093   0.0179   1.0000
  15.500   1.1707   0.08757   0.08195  -0.0107   0.0176   1.0000
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