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NACA M3 AIRFOIL (m3-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M3 AIRFOIL (m3-il)
Reynolds number: 100,000
Max Cl/Cd: 34.58 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m3-il-100000-n5.txt
Download as CSV file: xf-m3-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M3 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.7833   0.10665   0.10104  -0.0110   1.0000   0.0438
 -13.250  -0.8415   0.08888   0.08315  -0.0233   1.0000   0.0430
 -13.000  -0.8843   0.07759   0.07165  -0.0313   1.0000   0.0425
 -12.750  -0.9174   0.06981   0.06363  -0.0358   1.0000   0.0423
 -12.500  -0.9446   0.06400   0.05756  -0.0378   1.0000   0.0423
 -12.250  -0.9671   0.05944   0.05272  -0.0379   1.0000   0.0425
 -12.000  -0.9860   0.05569   0.04869  -0.0365   1.0000   0.0427
 -11.750  -1.0012   0.05252   0.04521  -0.0339   1.0000   0.0431
 -11.500  -1.0124   0.04970   0.04207  -0.0308   1.0000   0.0434
 -11.250  -1.0172   0.04696   0.03893  -0.0281   1.0000   0.0440
 -11.000  -1.0144   0.04452   0.03621  -0.0260   1.0000   0.0448
 -10.750  -1.0024   0.04274   0.03439  -0.0248   1.0000   0.0458
 -10.500  -0.9908   0.04112   0.03263  -0.0233   1.0000   0.0469
 -10.250  -0.9784   0.03939   0.03071  -0.0218   1.0000   0.0479
 -10.000  -0.9646   0.03758   0.02866  -0.0203   1.0000   0.0489
  -9.750  -0.9492   0.03583   0.02667  -0.0190   1.0000   0.0500
  -9.500  -0.9326   0.03429   0.02488  -0.0176   1.0000   0.0514
  -9.250  -0.9150   0.03289   0.02320  -0.0163   1.0000   0.0528
  -9.000  -0.8958   0.03140   0.02171  -0.0154   1.0000   0.0542
  -8.750  -0.8765   0.03018   0.02044  -0.0144   1.0000   0.0554
  -8.500  -0.8571   0.02904   0.01923  -0.0132   1.0000   0.0568
  -8.250  -0.8377   0.02795   0.01806  -0.0120   1.0000   0.0583
  -8.000  -0.8184   0.02695   0.01697  -0.0108   1.0000   0.0602
  -7.750  -0.7989   0.02607   0.01593  -0.0094   1.0000   0.0625
  -7.500  -0.7816   0.02507   0.01497  -0.0079   1.0000   0.0648
  -7.250  -0.7639   0.02422   0.01413  -0.0064   1.0000   0.0673
  -7.000  -0.7463   0.02342   0.01328  -0.0047   1.0000   0.0702
  -6.750  -0.7285   0.02268   0.01244  -0.0030   1.0000   0.0735
  -6.500  -0.7123   0.02184   0.01165  -0.0011   1.0000   0.0776
  -6.250  -0.6947   0.02115   0.01093   0.0006   1.0000   0.0842
  -6.000  -0.6777   0.02041   0.01026   0.0023   1.0000   0.0934
  -5.750  -0.6603   0.01970   0.00962   0.0040   1.0000   0.1071
  -5.500  -0.6426   0.01903   0.00903   0.0056   1.0000   0.1271
  -5.250  -0.6249   0.01837   0.00852   0.0072   1.0000   0.1534
  -5.000  -0.6067   0.01777   0.00807   0.0087   1.0000   0.1861
  -4.750  -0.5887   0.01718   0.00768   0.0102   1.0000   0.2268
  -4.500  -0.5705   0.01662   0.00736   0.0116   1.0000   0.2745
  -4.250  -0.5529   0.01603   0.00711   0.0132   1.0000   0.3376
  -4.000  -0.5354   0.01548   0.00694   0.0149   1.0000   0.4065
  -3.750  -0.5167   0.01507   0.00681   0.0165   1.0000   0.4667
  -3.500  -0.4968   0.01478   0.00672   0.0179   1.0000   0.5160
  -3.250  -0.4761   0.01458   0.00668   0.0193   1.0000   0.5599
  -3.000  -0.4552   0.01443   0.00669   0.0207   1.0000   0.6054
  -2.750  -0.4202   0.01434   0.00675   0.0193   0.9945   0.6553
  -2.500  -0.3847   0.01429   0.00681   0.0180   0.9879   0.6970
  -2.250  -0.3478   0.01431   0.00687   0.0164   0.9817   0.7323
  -2.000  -0.3117   0.01435   0.00696   0.0151   0.9746   0.7633
  -1.750  -0.2752   0.01442   0.00706   0.0137   0.9676   0.7907
  -1.500  -0.2373   0.01449   0.00713   0.0120   0.9606   0.8155
  -1.250  -0.1995   0.01458   0.00722   0.0104   0.9531   0.8354
  -1.000  -0.1585   0.01466   0.00729   0.0080   0.9462   0.8533
  -0.750  -0.1204   0.01472   0.00734   0.0063   0.9376   0.8694
  -0.500  -0.0792   0.01476   0.00737   0.0040   0.9297   0.8839
  -0.250  -0.0418   0.01480   0.00740   0.0024   0.9190   0.8978
   0.000   0.0000   0.01480   0.00740   0.0000   0.9097   0.9097
   0.250   0.0418   0.01479   0.00740  -0.0024   0.8978   0.9190
   0.500   0.0792   0.01476   0.00737  -0.0040   0.8839   0.9297
   0.750   0.1204   0.01472   0.00734  -0.0063   0.8694   0.9376
   1.000   0.1585   0.01466   0.00729  -0.0080   0.8533   0.9463
   1.250   0.1995   0.01458   0.00722  -0.0104   0.8354   0.9531
   1.500   0.2373   0.01449   0.00713  -0.0120   0.8155   0.9606
   1.750   0.2752   0.01442   0.00706  -0.0137   0.7907   0.9676
   2.000   0.3117   0.01435   0.00696  -0.0151   0.7634   0.9746
   2.250   0.3478   0.01431   0.00687  -0.0164   0.7323   0.9817
   2.500   0.3847   0.01429   0.00681  -0.0180   0.6970   0.9879
   2.750   0.4202   0.01433   0.00675  -0.0193   0.6553   0.9945
   3.000   0.4551   0.01443   0.00668  -0.0207   0.6055   1.0000
   3.250   0.4760   0.01458   0.00668  -0.0193   0.5600   1.0000
   3.500   0.4967   0.01478   0.00672  -0.0179   0.5161   1.0000
   3.750   0.5166   0.01507   0.00680  -0.0164   0.4668   1.0000
   4.000   0.5353   0.01548   0.00693  -0.0148   0.4066   1.0000
   4.250   0.5529   0.01602   0.00711  -0.0132   0.3377   1.0000
   4.500   0.5704   0.01662   0.00736  -0.0116   0.2745   1.0000
   4.750   0.5886   0.01717   0.00768  -0.0102   0.2269   1.0000
   5.000   0.6066   0.01777   0.00807  -0.0087   0.1862   1.0000
   5.250   0.6248   0.01837   0.00851  -0.0072   0.1534   1.0000
   5.500   0.6425   0.01902   0.00902  -0.0056   0.1272   1.0000
   5.750   0.6603   0.01969   0.00961  -0.0040   0.1071   1.0000
   6.000   0.6776   0.02041   0.01025  -0.0023   0.0934   1.0000
   6.250   0.6946   0.02115   0.01093  -0.0006   0.0842   1.0000
   6.500   0.7122   0.02184   0.01164   0.0011   0.0776   1.0000
   6.750   0.7285   0.02268   0.01244   0.0030   0.0735   1.0000
   7.000   0.7462   0.02342   0.01328   0.0047   0.0702   1.0000
   7.250   0.7639   0.02422   0.01412   0.0064   0.0673   1.0000
   7.500   0.7816   0.02506   0.01497   0.0079   0.0648   1.0000
   7.750   0.7989   0.02607   0.01593   0.0094   0.0625   1.0000
   8.000   0.8184   0.02695   0.01697   0.0108   0.0602   1.0000
   8.250   0.8378   0.02795   0.01806   0.0120   0.0583   1.0000
   8.500   0.8572   0.02903   0.01923   0.0132   0.0568   1.0000
   8.750   0.8766   0.03018   0.02044   0.0143   0.0554   1.0000
   9.000   0.8959   0.03140   0.02171   0.0154   0.0542   1.0000
   9.250   0.9151   0.03289   0.02320   0.0163   0.0528   1.0000
   9.500   0.9327   0.03429   0.02489   0.0176   0.0514   1.0000
   9.750   0.9493   0.03583   0.02668   0.0189   0.0500   1.0000
  10.000   0.9648   0.03758   0.02866   0.0203   0.0489   1.0000
  10.250   0.9787   0.03939   0.03071   0.0217   0.0479   1.0000
  10.500   0.9911   0.04112   0.03264   0.0232   0.0469   1.0000
  10.750   1.0028   0.04275   0.03439   0.0247   0.0458   1.0000
  11.000   1.0148   0.04453   0.03622   0.0259   0.0448   1.0000
  11.250   1.0175   0.04697   0.03895   0.0281   0.0440   1.0000
  11.500   1.0127   0.04972   0.04209   0.0307   0.0434   1.0000
  11.750   1.0017   0.05254   0.04524   0.0338   0.0431   1.0000
  12.000   0.9864   0.05573   0.04873   0.0364   0.0427   1.0000
  12.250   0.9676   0.05948   0.05277   0.0377   0.0424   1.0000
  12.500   0.9451   0.06406   0.05762   0.0376   0.0423   1.0000
  12.750   0.9180   0.06989   0.06371   0.0356   0.0423   1.0000
  13.000   0.8846   0.07774   0.07180   0.0310   0.0425   1.0000
  13.250   0.8416   0.08915   0.08342   0.0228   0.0430   1.0000
  13.500   0.7831   0.10709   0.10149   0.0105   0.0438   1.0000
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