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NACA M17 AIRFOIL (m17-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA M17 AIRFOIL (m17-il)
Reynolds number: 50,000
Max Cl/Cd: 35.59 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m17-il-50000-n5.txt
Download as CSV file: xf-m17-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M17 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4308   0.10887   0.10263  -0.0019   1.0000   0.0894
  -8.250  -0.4333   0.10683   0.10069  -0.0064   1.0000   0.0925
  -8.000  -0.4369   0.10519   0.09913  -0.0128   1.0000   0.0935
  -7.750  -0.4226   0.09897   0.09296  -0.0099   1.0000   0.0965
  -7.500  -0.4129   0.09515   0.08918  -0.0105   1.0000   0.1004
  -7.250  -0.4060   0.09187   0.08591  -0.0137   1.0000   0.1043
  -7.000  -0.4010   0.09008   0.08412  -0.0215   1.0000   0.1080
  -6.750  -0.3904   0.08544   0.07951  -0.0228   1.0000   0.1096
  -6.500  -0.3782   0.08106   0.07519  -0.0215   1.0000   0.1134
  -6.250  -0.3668   0.07896   0.07301  -0.0267   1.0000   0.1223
  -6.000  -0.3571   0.07463   0.06877  -0.0263   1.0000   0.1263
  -5.750  -0.3486   0.07190   0.06608  -0.0267   1.0000   0.1335
  -5.250  -0.2976   0.06598   0.05968  -0.0378   0.9623   0.1527
  -5.000  -0.2738   0.06054   0.05430  -0.0388   0.9468   0.1572
  -4.500  -0.1980   0.05104   0.04375  -0.0486   0.9150   0.0962
  -4.000  -0.1382   0.04409   0.03580  -0.0513   0.8869   0.0778
  -3.750  -0.1128   0.04155   0.03290  -0.0516   0.8737   0.0775
  -3.500  -0.0870   0.03934   0.03022  -0.0516   0.8614   0.0797
  -3.250  -0.0624   0.03727   0.02779  -0.0513   0.8491   0.0801
  -3.000  -0.0360   0.03546   0.02544  -0.0508   0.8373   0.0786
  -2.750  -0.0107   0.03369   0.02333  -0.0504   0.8261   0.0782
  -2.500   0.0152   0.03211   0.02139  -0.0498   0.8159   0.0779
  -2.250   0.0416   0.03070   0.01959  -0.0493   0.8060   0.0779
  -2.000   0.0688   0.02946   0.01801  -0.0489   0.7956   0.0782
  -1.750   0.0965   0.02837   0.01656  -0.0485   0.7864   0.0788
  -1.500   0.1234   0.02737   0.01543  -0.0482   0.7772   0.0815
  -1.250   0.1514   0.02674   0.01466  -0.0482   0.7676   0.0869
  -1.000   0.1828   0.02605   0.01363  -0.0482   0.7598   0.0914
  -0.750   0.2141   0.02545   0.01277  -0.0485   0.7503   0.0937
  -0.500   0.2426   0.02483   0.01208  -0.0483   0.7424   0.0972
  -0.250   0.2691   0.02442   0.01158  -0.0479   0.7338   0.1023
   0.000   0.2947   0.02409   0.01113  -0.0472   0.7259   0.1094
   0.250   0.3195   0.02377   0.01077  -0.0465   0.7182   0.1220
   0.500   0.3436   0.02343   0.01060  -0.0460   0.7102   0.1549
   1.000   0.4392   0.02141   0.01028  -0.0538   0.6951   1.0000
   1.250   0.4635   0.02168   0.01035  -0.0530   0.6880   1.0000
   1.500   0.4878   0.02206   0.01059  -0.0526   0.6800   1.0000
   1.750   0.5120   0.02236   0.01077  -0.0519   0.6733   1.0000
   2.000   0.5360   0.02278   0.01111  -0.0515   0.6655   1.0000
   2.250   0.5600   0.02311   0.01136  -0.0508   0.6588   1.0000
   2.500   0.5838   0.02357   0.01180  -0.0503   0.6516   1.0000
   2.750   0.6077   0.02396   0.01215  -0.0497   0.6446   1.0000
   3.000   0.6313   0.02442   0.01260  -0.0491   0.6377   1.0000
   3.250   0.6549   0.02490   0.01310  -0.0486   0.6306   1.0000
   3.500   0.6786   0.02533   0.01356  -0.0480   0.6242   1.0000
   3.750   0.7016   0.02591   0.01421  -0.0475   0.6165   1.0000
   4.000   0.7256   0.02629   0.01460  -0.0467   0.6106   1.0000
   4.250   0.7477   0.02699   0.01545  -0.0464   0.6021   1.0000
   4.500   0.7721   0.02731   0.01581  -0.0455   0.5964   1.0000
   4.750   0.7933   0.02811   0.01676  -0.0451   0.5872   1.0000
   5.000   0.8171   0.02849   0.01724  -0.0442   0.5805   1.0000
   5.500   0.8604   0.02970   0.01879  -0.0428   0.5620   1.0000
   5.750   0.8851   0.02978   0.01898  -0.0416   0.5537   1.0000
   6.000   0.9055   0.03035   0.01975  -0.0406   0.5419   1.0000
   6.250   0.9268   0.03078   0.02040  -0.0396   0.5307   1.0000
   6.500   0.9506   0.03092   0.02072  -0.0384   0.5210   1.0000
   6.750   0.9732   0.03120   0.02123  -0.0373   0.5104   1.0000
   7.000   0.9930   0.03183   0.02213  -0.0362   0.4984   1.0000
   7.250   1.0137   0.03235   0.02298  -0.0351   0.4868   1.0000
   7.500   1.0358   0.03266   0.02357  -0.0339   0.4754   1.0000
   7.750   1.0567   0.03249   0.02369  -0.0321   0.4573   1.0000
   8.000   1.0744   0.03031   0.02145  -0.0280   0.4055   1.0000
   8.250   1.0830   0.03043   0.02154  -0.0252   0.3440   1.0000
   8.500   1.0851   0.03148   0.02203  -0.0219   0.2479   1.0000
   8.750   1.0748   0.03433   0.02415  -0.0190   0.1659   1.0000
   9.000   1.0612   0.03762   0.02700  -0.0166   0.1090   1.0000
   9.250   1.0484   0.04110   0.03018  -0.0149   0.0846   1.0000
   9.500   1.0400   0.04456   0.03351  -0.0140   0.0729   1.0000
   9.750   1.0351   0.04783   0.03679  -0.0132   0.0661   1.0000
  10.000   1.0308   0.05111   0.04011  -0.0127   0.0610   1.0000
  10.250   1.0274   0.05435   0.04336  -0.0121   0.0570   1.0000
  10.500   1.0276   0.05720   0.04636  -0.0115   0.0528   1.0000
  10.750   1.0274   0.06012   0.04934  -0.0109   0.0494   1.0000
  11.000   1.0273   0.06296   0.05221  -0.0100   0.0470   1.0000
  11.250   1.0345   0.06502   0.05440  -0.0085   0.0451   1.0000
  11.500   1.0450   0.06682   0.05643  -0.0068   0.0428   1.0000
  11.750   1.0553   0.06877   0.05855  -0.0053   0.0402   1.0000
  12.000   1.0662   0.07073   0.06063  -0.0038   0.0377   1.0000
  12.250   1.0878   0.07218   0.06222  -0.0011   0.0359   1.0000
  12.500   1.0985   0.07501   0.06540   0.0000   0.0351   1.0000
  12.750   1.1023   0.07857   0.06930   0.0004   0.0346   1.0000
  13.000   1.0997   0.08276   0.07380   0.0001   0.0342   1.0000
  13.250   1.0924   0.08746   0.07879  -0.0009   0.0339   1.0000
  13.500   1.0818   0.09265   0.08425  -0.0025   0.0337   1.0000
  13.750   1.0689   0.09831   0.09016  -0.0046   0.0337   1.0000
  14.000   1.0541   0.10449   0.09656  -0.0074   0.0337   1.0000
  14.250   1.0380   0.11123   0.10350  -0.0107   0.0339   1.0000
  14.500   1.0212   0.11862   0.11106  -0.0147   0.0341   1.0000
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