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NACA M3 AIRFOIL (m3-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M3 AIRFOIL (m3-il)
Reynolds number: 200,000
Max Cl/Cd: 42.15 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m3-il-200000-n5.txt
Download as CSV file: xf-m3-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.9835   0.08472   0.08023  -0.0226   1.0000   0.0264
 -14.750  -1.0181   0.07475   0.06999  -0.0293   1.0000   0.0263
 -14.500  -1.0391   0.06798   0.06301  -0.0333   1.0000   0.0264
 -14.250  -1.0547   0.06261   0.05744  -0.0360   1.0000   0.0266
 -14.000  -1.0670   0.05811   0.05275  -0.0377   1.0000   0.0268
 -13.750  -1.0769   0.05426   0.04871  -0.0386   1.0000   0.0271
 -13.500  -1.0848   0.05094   0.04520  -0.0388   1.0000   0.0275
 -13.250  -1.0910   0.04804   0.04210  -0.0384   1.0000   0.0279
 -13.000  -1.0953   0.04548   0.03932  -0.0374   1.0000   0.0284
 -12.750  -1.0985   0.04316   0.03677  -0.0358   1.0000   0.0290
 -12.500  -1.1003   0.04108   0.03444  -0.0339   1.0000   0.0295
 -12.250  -1.1004   0.03925   0.03234  -0.0315   1.0000   0.0301
 -12.000  -1.0987   0.03768   0.03051  -0.0289   1.0000   0.0305
 -11.750  -1.0904   0.03583   0.02857  -0.0271   1.0000   0.0311
 -11.500  -1.0792   0.03449   0.02719  -0.0255   1.0000   0.0317
 -11.250  -1.0665   0.03334   0.02597  -0.0240   1.0000   0.0324
 -11.000  -1.0529   0.03223   0.02474  -0.0225   1.0000   0.0332
 -10.750  -1.0383   0.03108   0.02347  -0.0210   1.0000   0.0340
 -10.500  -1.0226   0.02993   0.02216  -0.0196   1.0000   0.0348
 -10.250  -1.0058   0.02880   0.02088  -0.0183   1.0000   0.0356
 -10.000  -0.9883   0.02782   0.01974  -0.0170   1.0000   0.0364
  -9.750  -0.9702   0.02682   0.01859  -0.0158   1.0000   0.0371
  -9.500  -0.9528   0.02561   0.01738  -0.0146   1.0000   0.0380
  -9.250  -0.9348   0.02468   0.01642  -0.0133   1.0000   0.0388
  -9.000  -0.9165   0.02383   0.01553  -0.0120   1.0000   0.0396
  -8.750  -0.8980   0.02305   0.01469  -0.0107   1.0000   0.0405
  -8.500  -0.8793   0.02233   0.01390  -0.0093   1.0000   0.0416
  -8.250  -0.8607   0.02164   0.01315  -0.0079   1.0000   0.0427
  -8.000  -0.8421   0.02098   0.01242  -0.0064   1.0000   0.0437
  -7.750  -0.8238   0.02036   0.01173  -0.0048   1.0000   0.0444
  -7.500  -0.8075   0.01958   0.01094  -0.0029   1.0000   0.0456
  -7.250  -0.7900   0.01896   0.01031  -0.0012   1.0000   0.0468
  -7.000  -0.7718   0.01842   0.00975   0.0004   1.0000   0.0482
  -6.750  -0.7532   0.01793   0.00923   0.0020   1.0000   0.0500
  -6.500  -0.7343   0.01749   0.00873   0.0035   1.0000   0.0522
  -6.250  -0.7161   0.01699   0.00823   0.0052   1.0000   0.0549
  -6.000  -0.6973   0.01655   0.00780   0.0067   1.0000   0.0584
  -5.500  -0.6592   0.01572   0.00698   0.0097   1.0000   0.0705
  -5.250  -0.6400   0.01531   0.00662   0.0112   1.0000   0.0819
  -5.000  -0.6121   0.01485   0.00624   0.0107   0.9978   0.1010
  -4.750  -0.5789   0.01432   0.00588   0.0091   0.9943   0.1314
  -4.500  -0.5467   0.01380   0.00554   0.0077   0.9901   0.1682
  -4.250  -0.5135   0.01331   0.00525   0.0061   0.9858   0.2098
  -4.000  -0.4802   0.01285   0.00498   0.0045   0.9817   0.2555
  -3.750  -0.4485   0.01236   0.00474   0.0033   0.9762   0.3103
  -3.500  -0.4143   0.01184   0.00453   0.0016   0.9722   0.3756
  -3.250  -0.3846   0.01137   0.00435   0.0009   0.9655   0.4414
  -3.000  -0.3517   0.01098   0.00421  -0.0003   0.9603   0.4977
  -2.750  -0.3217   0.01068   0.00409  -0.0007   0.9533   0.5438
  -2.500  -0.2904   0.01041   0.00401  -0.0013   0.9467   0.5905
  -2.250  -0.2606   0.01018   0.00395  -0.0015   0.9392   0.6338
  -2.000  -0.2300   0.01001   0.00388  -0.0019   0.9313   0.6664
  -1.750  -0.2003   0.00987   0.00384  -0.0020   0.9227   0.6949
  -1.500  -0.1701   0.00974   0.00378  -0.0021   0.9138   0.7222
  -1.250  -0.1418   0.00965   0.00376  -0.0018   0.9031   0.7471
  -1.000  -0.1122   0.00956   0.00372  -0.0017   0.8929   0.7691
  -0.750  -0.0835   0.00950   0.00370  -0.0014   0.8809   0.7885
  -0.500  -0.0557   0.00946   0.00368  -0.0010   0.8674   0.8064
  -0.250  -0.0279   0.00943   0.00367  -0.0005   0.8533   0.8230
   0.000   0.0000   0.00942   0.00366   0.0000   0.8386   0.8386
   0.250   0.0279   0.00943   0.00367   0.0005   0.8231   0.8533
   0.500   0.0557   0.00946   0.00368   0.0010   0.8064   0.8674
   0.750   0.0835   0.00950   0.00370   0.0014   0.7885   0.8809
   1.000   0.1122   0.00956   0.00372   0.0017   0.7690   0.8929
   1.250   0.1418   0.00965   0.00376   0.0018   0.7472   0.9031
   1.500   0.1701   0.00974   0.00378   0.0021   0.7222   0.9138
   1.750   0.2003   0.00987   0.00383   0.0020   0.6949   0.9227
   2.000   0.2300   0.01001   0.00388   0.0019   0.6664   0.9313
   2.250   0.2606   0.01018   0.00395   0.0015   0.6338   0.9392
   2.500   0.2904   0.01041   0.00401   0.0013   0.5904   0.9467
   2.750   0.3217   0.01068   0.00409   0.0007   0.5438   0.9533
   3.000   0.3517   0.01098   0.00421   0.0003   0.4976   0.9603
   3.250   0.3846   0.01137   0.00435  -0.0009   0.4415   0.9655
   3.500   0.4143   0.01184   0.00453  -0.0016   0.3755   0.9722
   3.750   0.4485   0.01235   0.00474  -0.0033   0.3104   0.9762
   4.000   0.4802   0.01285   0.00498  -0.0045   0.2554   0.9817
   4.250   0.5136   0.01331   0.00525  -0.0061   0.2098   0.9859
   4.500   0.5467   0.01380   0.00554  -0.0077   0.1683   0.9901
   4.750   0.5790   0.01432   0.00588  -0.0091   0.1315   0.9943
   5.000   0.6122   0.01484   0.00624  -0.0107   0.1010   0.9978
   5.250   0.6399   0.01531   0.00662  -0.0111   0.0820   1.0000
   5.500   0.6591   0.01572   0.00698  -0.0097   0.0705   1.0000
   6.000   0.6972   0.01654   0.00780  -0.0067   0.0584   1.0000
   6.250   0.7160   0.01699   0.00823  -0.0051   0.0549   1.0000
   6.500   0.7342   0.01749   0.00872  -0.0035   0.0522   1.0000
   6.750   0.7531   0.01793   0.00922  -0.0019   0.0500   1.0000
   7.000   0.7717   0.01842   0.00974  -0.0004   0.0482   1.0000
   7.250   0.7899   0.01895   0.01031   0.0013   0.0468   1.0000
   7.500   0.8075   0.01957   0.01094   0.0029   0.0456   1.0000
   7.750   0.8238   0.02035   0.01172   0.0048   0.0444   1.0000
   8.000   0.8421   0.02098   0.01242   0.0064   0.0437   1.0000
   8.250   0.8607   0.02164   0.01315   0.0079   0.0427   1.0000
   8.500   0.8794   0.02233   0.01390   0.0093   0.0416   1.0000
   8.750   0.8980   0.02305   0.01469   0.0106   0.0405   1.0000
   9.000   0.9166   0.02383   0.01553   0.0120   0.0396   1.0000
   9.250   0.9349   0.02468   0.01642   0.0133   0.0388   1.0000
   9.500   0.9530   0.02561   0.01738   0.0145   0.0380   1.0000
   9.750   0.9704   0.02682   0.01860   0.0158   0.0371   1.0000
  10.000   0.9885   0.02782   0.01974   0.0170   0.0364   1.0000
  10.250   1.0061   0.02881   0.02089   0.0183   0.0356   1.0000
  10.500   1.0228   0.02993   0.02216   0.0196   0.0348   1.0000
  10.750   1.0386   0.03109   0.02347   0.0210   0.0340   1.0000
  11.000   1.0533   0.03223   0.02475   0.0224   0.0332   1.0000
  11.250   1.0669   0.03335   0.02598   0.0239   0.0324   1.0000
  11.500   1.0797   0.03450   0.02719   0.0254   0.0317   1.0000
  11.750   1.0910   0.03584   0.02858   0.0270   0.0311   1.0000
  12.000   1.0992   0.03769   0.03053   0.0288   0.0305   1.0000
  12.250   1.1010   0.03926   0.03236   0.0314   0.0301   1.0000
  12.500   1.1010   0.04109   0.03446   0.0337   0.0295   1.0000
  12.750   1.0993   0.04318   0.03679   0.0357   0.0290   1.0000
  13.000   1.0962   0.04549   0.03934   0.0372   0.0284   1.0000
  13.250   1.0919   0.04804   0.04210   0.0382   0.0279   1.0000
  13.500   1.0858   0.05095   0.04521   0.0386   0.0275   1.0000
  13.750   1.0781   0.05427   0.04872   0.0384   0.0271   1.0000
  14.000   1.0682   0.05813   0.05277   0.0375   0.0268   1.0000
  14.250   1.0559   0.06262   0.05745   0.0358   0.0266   1.0000
  14.500   1.0408   0.06795   0.06297   0.0331   0.0264   1.0000
  14.750   1.0199   0.07469   0.06993   0.0291   0.0263   1.0000
  15.000   0.9860   0.08455   0.08006   0.0225   0.0264   1.0000
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