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USA 45 M AIRFOIL (usa45m-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 45 M AIRFOIL (usa45m-il)
Reynolds number: 100,000
Max Cl/Cd: 47.96 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa45m-il-100000-n5.txt
Download as CSV file: xf-usa45m-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3941   0.11197   0.10691  -0.0258   1.0000   0.0643
 -10.000  -0.3995   0.10846   0.10347  -0.0291   1.0000   0.0646
  -9.750  -0.4042   0.10466   0.09973  -0.0322   1.0000   0.0647
  -9.500  -0.3937   0.09973   0.09482  -0.0307   1.0000   0.0655
  -9.250  -0.3795   0.09651   0.09160  -0.0285   1.0000   0.0667
  -9.000  -0.3716   0.09363   0.08874  -0.0280   1.0000   0.0682
  -8.750  -0.3674   0.09079   0.08594  -0.0282   1.0000   0.0704
  -8.500  -0.3686   0.08764   0.08285  -0.0294   1.0000   0.0728
  -8.250  -0.3789   0.08412   0.07943  -0.0321   1.0000   0.0756
  -8.000  -0.4014   0.08030   0.07570  -0.0357   1.0000   0.0769
  -7.750  -0.4319   0.07665   0.07190  -0.0392   1.0000   0.0781
  -7.500  -0.4446   0.07374   0.06883  -0.0387   1.0000   0.0783
  -7.250  -0.4272   0.06886   0.06426  -0.0369   1.0000   0.0799
  -7.000  -0.4245   0.06611   0.06154  -0.0352   1.0000   0.0807
  -6.750  -0.4417   0.05695   0.05175  -0.0348   1.0000   0.0518
  -6.500  -0.4309   0.05346   0.04816  -0.0349   0.9964   0.0514
  -6.000  -0.3776   0.04498   0.03883  -0.0411   0.9736   0.0518
  -5.750  -0.3501   0.04134   0.03495  -0.0430   0.9621   0.0513
  -5.500  -0.3218   0.03815   0.03141  -0.0446   0.9499   0.0509
  -5.250  -0.2926   0.03533   0.02821  -0.0459   0.9369   0.0508
  -5.000  -0.2628   0.03318   0.02561  -0.0467   0.9226   0.0516
  -4.750  -0.2326   0.03151   0.02347  -0.0473   0.9068   0.0525
  -4.500  -0.2025   0.02941   0.02104  -0.0479   0.8902   0.0527
  -4.250  -0.1717   0.02767   0.01899  -0.0484   0.8724   0.0527
  -4.000  -0.1407   0.02598   0.01701  -0.0488   0.8529   0.0529
  -3.750  -0.1116   0.02450   0.01529  -0.0488   0.8303   0.0532
  -3.500  -0.0819   0.02323   0.01380  -0.0488   0.8065   0.0537
  -3.250  -0.0538   0.02219   0.01258  -0.0486   0.7802   0.0546
  -3.000  -0.0262   0.02139   0.01161  -0.0482   0.7525   0.0564
  -2.750   0.0010   0.02071   0.01075  -0.0477   0.7244   0.0584
  -2.500   0.0277   0.02006   0.00990  -0.0470   0.6963   0.0594
  -2.250   0.0538   0.01946   0.00912  -0.0463   0.6688   0.0602
  -2.000   0.0794   0.01894   0.00845  -0.0455   0.6431   0.0612
  -1.750   0.1043   0.01851   0.00787  -0.0446   0.6192   0.0623
  -1.500   0.1288   0.01816   0.00737  -0.0437   0.5975   0.0636
  -1.250   0.1530   0.01787   0.00694  -0.0427   0.5778   0.0649
  -1.000   0.1764   0.01748   0.00647  -0.0418   0.5604   0.0686
  -0.750   0.2010   0.01729   0.00615  -0.0410   0.5448   0.0735
  -0.500   0.2261   0.01716   0.00586  -0.0403   0.5309   0.0777
  -0.250   0.2511   0.01697   0.00556  -0.0396   0.5184   0.0835
   0.000   0.2764   0.01683   0.00533  -0.0389   0.5072   0.0953
   0.250   0.2903   0.01460   0.00535  -0.0367   0.4979   0.6745
   0.750   0.4429   0.01472   0.00545  -0.0545   0.4710   1.0000
   1.000   0.4652   0.01489   0.00546  -0.0535   0.4631   1.0000
   1.250   0.4877   0.01509   0.00551  -0.0525   0.4560   1.0000
   1.500   0.5103   0.01528   0.00559  -0.0515   0.4488   1.0000
   1.750   0.5330   0.01551   0.00567  -0.0505   0.4425   1.0000
   2.000   0.5559   0.01572   0.00581  -0.0496   0.4356   1.0000
   2.250   0.5789   0.01596   0.00593  -0.0487   0.4299   1.0000
   2.500   0.6020   0.01621   0.00612  -0.0478   0.4238   1.0000
   2.750   0.6250   0.01645   0.00631  -0.0470   0.4177   1.0000
   3.000   0.6483   0.01673   0.00647  -0.0461   0.4127   1.0000
   3.250   0.6714   0.01699   0.00675  -0.0453   0.4066   1.0000
   3.500   0.6947   0.01727   0.00698  -0.0444   0.4011   1.0000
   3.750   0.7182   0.01757   0.00719  -0.0436   0.3964   1.0000
   4.000   0.7410   0.01786   0.00754  -0.0428   0.3903   1.0000
   4.250   0.7643   0.01815   0.00781  -0.0419   0.3849   1.0000
   4.500   0.7878   0.01847   0.00807  -0.0411   0.3803   1.0000
   4.750   0.8104   0.01878   0.00847  -0.0402   0.3742   1.0000
   5.000   0.8335   0.01909   0.00877  -0.0394   0.3689   1.0000
   5.250   0.8568   0.01942   0.00908  -0.0386   0.3640   1.0000
   5.500   0.8791   0.01975   0.00952  -0.0377   0.3577   1.0000
   5.750   0.9022   0.02006   0.00983  -0.0369   0.3525   1.0000
   6.000   0.9249   0.02041   0.01023  -0.0361   0.3470   1.0000
   6.250   0.9470   0.02075   0.01068  -0.0352   0.3408   1.0000
   6.500   0.9701   0.02106   0.01097  -0.0343   0.3356   1.0000
   6.750   0.9917   0.02145   0.01150  -0.0334   0.3294   1.0000
   7.000   1.0138   0.02179   0.01191  -0.0325   0.3234   1.0000
   7.250   1.0362   0.02213   0.01229  -0.0316   0.3182   1.0000
   7.500   1.0571   0.02257   0.01290  -0.0306   0.3117   1.0000
   7.750   1.0791   0.02292   0.01330  -0.0297   0.3063   1.0000
   8.000   1.0998   0.02336   0.01388  -0.0287   0.3002   1.0000
   8.250   1.1199   0.02369   0.01433  -0.0275   0.2927   1.0000
   8.500   1.1382   0.02397   0.01473  -0.0261   0.2829   1.0000
   8.750   1.1555   0.02417   0.01497  -0.0246   0.2716   1.0000
   9.000   1.1722   0.02444   0.01531  -0.0230   0.2603   1.0000
   9.250   1.1885   0.02487   0.01590  -0.0214   0.2484   1.0000
   9.500   1.2032   0.02531   0.01643  -0.0197   0.2348   1.0000
   9.750   1.2169   0.02586   0.01704  -0.0178   0.2209   1.0000
  10.000   1.2275   0.02653   0.01772  -0.0157   0.2041   1.0000
  10.250   1.2362   0.02736   0.01857  -0.0134   0.1872   1.0000
  10.500   1.2386   0.02844   0.01960  -0.0104   0.1661   1.0000
  10.750   1.2342   0.02994   0.02102  -0.0069   0.1421   1.0000
  11.250   1.2183   0.03413   0.02506  -0.0014   0.0939   1.0000
  11.500   1.1938   0.03804   0.02877   0.0005   0.0561   1.0000
  11.750   1.1712   0.04252   0.03321   0.0009   0.0459   1.0000
  12.000   1.1533   0.04721   0.03799   0.0003   0.0421   1.0000
  12.250   1.1386   0.05200   0.04291  -0.0010   0.0402   1.0000
  12.500   1.1220   0.05736   0.04840  -0.0027   0.0385   1.0000
  13.000   1.0929   0.06804   0.05936  -0.0062   0.0362   1.0000
  13.250   1.0801   0.07325   0.06472  -0.0079   0.0353   1.0000
  13.500   1.0671   0.07856   0.07017  -0.0097   0.0345   1.0000
  13.750   1.0542   0.08401   0.07575  -0.0116   0.0337   1.0000
  14.000   1.0426   0.08942   0.08130  -0.0136   0.0331   1.0000
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