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USA 45 M AIRFOIL (usa45m-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA 45 M AIRFOIL (usa45m-il)
Reynolds number: 500,000
Max Cl/Cd: 90.37 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa45m-il-500000-n5.txt
Download as CSV file: xf-usa45m-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 45 M 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4170   0.11034   0.10794  -0.0181   1.0000   0.0157
 -11.000  -0.4176   0.10594   0.10356  -0.0199   1.0000   0.0162
 -10.750  -0.4386   0.09641   0.09403  -0.0246   1.0000   0.0174
 -10.500  -0.4335   0.09390   0.09155  -0.0256   1.0000   0.0177
 -10.250  -0.4261   0.09189   0.08955  -0.0262   1.0000   0.0179
 -10.000  -0.4238   0.08873   0.08641  -0.0275   1.0000   0.0181
  -9.750  -0.4231   0.08530   0.08300  -0.0289   1.0000   0.0183
  -9.500  -0.4246   0.08151   0.07924  -0.0307   1.0000   0.0186
  -9.250  -0.4279   0.07758   0.07534  -0.0327   1.0000   0.0190
  -9.000  -0.4393   0.07246   0.07026  -0.0358   1.0000   0.0192
  -8.750  -0.4655   0.06663   0.06447  -0.0397   1.0000   0.0193
  -8.500  -0.4843   0.05939   0.05716  -0.0436   0.9954   0.0196
  -8.000  -0.4963   0.03544   0.03210  -0.0551   0.9622   0.0222
  -7.750  -0.4684   0.03369   0.03019  -0.0570   0.9502   0.0225
  -7.500  -0.4386   0.03213   0.02848  -0.0588   0.9347   0.0229
  -7.250  -0.4115   0.03041   0.02657  -0.0600   0.9148   0.0235
  -7.000  -0.3927   0.02778   0.02359  -0.0594   0.8896   0.0240
  -6.750  -0.3760   0.02519   0.02060  -0.0581   0.8638   0.0246
  -6.500  -0.3594   0.02274   0.01770  -0.0564   0.8365   0.0252
  -6.250  -0.3403   0.02099   0.01555  -0.0549   0.8094   0.0261
  -6.000  -0.3195   0.01974   0.01396  -0.0536   0.7826   0.0264
  -5.750  -0.2977   0.01879   0.01271  -0.0524   0.7559   0.0266
  -5.500  -0.2751   0.01804   0.01169  -0.0514   0.7278   0.0268
  -5.250  -0.2534   0.01678   0.01014  -0.0503   0.6989   0.0271
  -5.000  -0.2304   0.01593   0.00907  -0.0494   0.6705   0.0275
  -4.750  -0.2065   0.01534   0.00830  -0.0486   0.6435   0.0278
  -4.250  -0.1576   0.01459   0.00724  -0.0472   0.5890   0.0285
  -4.000  -0.1328   0.01432   0.00683  -0.0466   0.5622   0.0290
  -3.750  -0.1079   0.01398   0.00634  -0.0459   0.5381   0.0295
  -3.500  -0.0827   0.01361   0.00584  -0.0453   0.5176   0.0299
  -3.250  -0.0575   0.01327   0.00538  -0.0447   0.4989   0.0302
  -3.000  -0.0323   0.01297   0.00497  -0.0441   0.4819   0.0307
  -2.750  -0.0069   0.01270   0.00460  -0.0436   0.4678   0.0311
  -2.500   0.0186   0.01244   0.00426  -0.0430   0.4560   0.0316
  -2.250   0.0442   0.01222   0.00396  -0.0425   0.4459   0.0320
  -2.000   0.0700   0.01200   0.00369  -0.0420   0.4370   0.0324
  -1.500   0.1217   0.01167   0.00324  -0.0410   0.4205   0.0331
  -1.250   0.1475   0.01152   0.00303  -0.0406   0.4134   0.0337
  -1.000   0.1732   0.01128   0.00278  -0.0401   0.4076   0.0351
  -0.750   0.1995   0.01117   0.00264  -0.0397   0.4014   0.0362
  -0.500   0.2258   0.01110   0.00253  -0.0393   0.3956   0.0372
  -0.250   0.2525   0.01102   0.00243  -0.0389   0.3898   0.0384
   0.000   0.2790   0.01097   0.00234  -0.0386   0.3841   0.0399
   0.250   0.3057   0.01094   0.00228  -0.0383   0.3795   0.0413
   0.500   0.3324   0.01087   0.00220  -0.0379   0.3747   0.0443
   0.750   0.3590   0.01085   0.00217  -0.0376   0.3695   0.0488
   1.000   0.3855   0.01084   0.00215  -0.0373   0.3647   0.0575
   1.250   0.4094   0.01038   0.00213  -0.0367   0.3603   0.2205
   1.500   0.4230   0.00911   0.00215  -0.0343   0.3566   0.6429
   1.750   0.4391   0.00851   0.00229  -0.0314   0.3526   0.8631
   2.000   0.4858   0.00859   0.00246  -0.0351   0.3473   0.9458
   2.250   0.5399   0.00876   0.00259  -0.0406   0.3414   0.9748
   2.500   0.5988   0.00897   0.00271  -0.0471   0.3353   0.9907
   2.750   0.6355   0.00906   0.00277  -0.0491   0.3307   0.9947
   3.000   0.6723   0.00914   0.00282  -0.0510   0.3257   0.9979
   3.250   0.7056   0.00927   0.00289  -0.0523   0.3206   1.0000
   3.500   0.7288   0.00936   0.00296  -0.0514   0.3166   1.0000
   3.750   0.7521   0.00946   0.00305  -0.0505   0.3122   1.0000
   4.000   0.7749   0.00959   0.00315  -0.0495   0.3069   1.0000
   4.250   0.7980   0.00971   0.00325  -0.0485   0.3016   1.0000
   4.500   0.8213   0.00983   0.00336  -0.0476   0.2961   1.0000
   4.750   0.8442   0.00997   0.00348  -0.0467   0.2913   1.0000
   5.000   0.8674   0.01011   0.00362  -0.0458   0.2873   1.0000
   5.250   0.8909   0.01024   0.00376  -0.0449   0.2825   1.0000
   5.500   0.9140   0.01040   0.00391  -0.0440   0.2775   1.0000
   5.750   0.9371   0.01057   0.00406  -0.0431   0.2718   1.0000
   6.000   0.9600   0.01075   0.00423  -0.0422   0.2623   1.0000
   6.250   0.9830   0.01094   0.00440  -0.0413   0.2543   1.0000
   6.500   1.0055   0.01117   0.00459  -0.0404   0.2456   1.0000
   6.750   1.0284   0.01138   0.00480  -0.0395   0.2357   1.0000
   7.000   1.0505   0.01164   0.00503  -0.0385   0.2240   1.0000
   7.250   1.0716   0.01198   0.00530  -0.0375   0.2078   1.0000
   7.500   1.0917   0.01241   0.00563  -0.0362   0.1894   1.0000
   7.750   1.1115   0.01286   0.00599  -0.0350   0.1718   1.0000
   8.000   1.1291   0.01348   0.00649  -0.0334   0.1482   1.0000
   8.250   1.1442   0.01429   0.00711  -0.0315   0.1184   1.0000
   8.500   1.1472   0.01597   0.00836  -0.0280   0.0496   1.0000
   8.750   1.1569   0.01708   0.00938  -0.0254   0.0216   1.0000
   9.000   1.1740   0.01764   0.00996  -0.0238   0.0182   1.0000
   9.250   1.1916   0.01813   0.01052  -0.0223   0.0167   1.0000
   9.500   1.2078   0.01869   0.01113  -0.0206   0.0154   1.0000
   9.750   1.2217   0.01934   0.01184  -0.0186   0.0142   1.0000
  10.000   1.2343   0.01993   0.01250  -0.0164   0.0135   1.0000
  10.250   1.2453   0.02053   0.01317  -0.0139   0.0129   1.0000
  10.500   1.2552   0.02121   0.01393  -0.0115   0.0125   1.0000
  10.750   1.2640   0.02199   0.01478  -0.0090   0.0119   1.0000
  11.000   1.2716   0.02289   0.01575  -0.0067   0.0115   1.0000
  11.250   1.2779   0.02393   0.01686  -0.0045   0.0111   1.0000
  11.500   1.2815   0.02523   0.01824  -0.0023   0.0108   1.0000
  11.750   1.2803   0.02700   0.02011  -0.0002   0.0104   1.0000
  12.000   1.2857   0.02845   0.02166   0.0010   0.0100   1.0000
  12.250   1.2868   0.03043   0.02375   0.0020   0.0100   1.0000
  12.500   1.2891   0.03249   0.02591   0.0026   0.0096   1.0000
  12.750   1.2875   0.03518   0.02872   0.0027   0.0095   1.0000
  13.000   1.2860   0.03810   0.03174   0.0025   0.0092   1.0000
  13.250   1.2827   0.04145   0.03521   0.0018   0.0090   1.0000
  13.500   1.2757   0.04545   0.03933   0.0007   0.0089   1.0000
  13.750   1.2679   0.04968   0.04368  -0.0006   0.0087   1.0000
  14.000   1.2584   0.05422   0.04833  -0.0020   0.0087   1.0000
  14.250   1.2463   0.05909   0.05332  -0.0034   0.0086   1.0000
  14.500   1.2352   0.06384   0.05818  -0.0049   0.0085   1.0000
  14.750   1.2221   0.06890   0.06334  -0.0064   0.0085   1.0000
  15.000   1.2107   0.07381   0.06835  -0.0080   0.0084   1.0000
  15.250   1.2004   0.07866   0.07328  -0.0096   0.0083   1.0000
  15.500   1.1893   0.08375   0.07846  -0.0113   0.0083   1.0000
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