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NACA M2 (nacam2-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA M2 (nacam2-il)
Reynolds number: 50,000
Max Cl/Cd: 23.59 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nacam2-il-50000-n5.txt
Download as CSV file: xf-nacam2-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M2                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.7316   0.09235   0.08528  -0.0078   1.0000   0.0509
  -9.750  -0.7409   0.08658   0.07950  -0.0112   1.0000   0.0507
  -9.500  -0.7532   0.08136   0.07424  -0.0135   1.0000   0.0504
  -9.250  -0.7656   0.07646   0.06925  -0.0146   1.0000   0.0502
  -9.000  -0.7759   0.07142   0.06402  -0.0155   1.0000   0.0502
  -8.750  -0.7841   0.06639   0.05870  -0.0159   1.0000   0.0505
  -8.500  -0.7897   0.06149   0.05334  -0.0157   1.0000   0.0510
  -8.250  -0.7788   0.05844   0.05039  -0.0152   1.0000   0.0535
  -8.000  -0.7712   0.05493   0.04662  -0.0147   1.0000   0.0553
  -7.750  -0.7636   0.05082   0.04208  -0.0139   1.0000   0.0564
  -7.500  -0.7528   0.04684   0.03760  -0.0130   1.0000   0.0576
  -7.250  -0.7389   0.04341   0.03360  -0.0120   1.0000   0.0607
  -7.000  -0.7225   0.04025   0.02966  -0.0107   1.0000   0.0639
  -6.750  -0.7025   0.03737   0.02660  -0.0101   1.0000   0.0662
  -6.500  -0.6806   0.03506   0.02397  -0.0094   1.0000   0.0692
  -6.250  -0.6579   0.03318   0.02168  -0.0086   1.0000   0.0749
  -6.000  -0.6334   0.03111   0.01927  -0.0079   1.0000   0.0784
  -5.750  -0.6086   0.02932   0.01739  -0.0072   1.0000   0.0816
  -5.500  -0.5834   0.02780   0.01570  -0.0065   1.0000   0.0856
  -5.250  -0.5579   0.02651   0.01410  -0.0056   1.0000   0.0910
  -5.000  -0.5347   0.02531   0.01297  -0.0049   1.0000   0.1001
  -4.750  -0.5109   0.02417   0.01175  -0.0041   1.0000   0.1094
  -4.500  -0.4873   0.02302   0.01054  -0.0032   1.0000   0.1211
  -4.250  -0.4644   0.02177   0.00936  -0.0025   1.0000   0.1442
  -4.000  -0.4432   0.02028   0.00831  -0.0018   1.0000   0.2078
  -3.750  -0.4263   0.01874   0.00763  -0.0003   1.0000   0.3563
  -3.500  -0.4128   0.01750   0.00748   0.0030   1.0000   0.5573
  -3.250  -0.3949   0.01708   0.00783   0.0077   1.0000   0.7371
  -3.000  -0.3640   0.01724   0.00802   0.0097   1.0000   0.8357
  -2.750  -0.3202   0.01747   0.00801   0.0083   1.0000   0.8954
  -2.500  -0.2679   0.01759   0.00778   0.0044   1.0000   0.9362
  -2.250  -0.2114   0.01751   0.00738  -0.0013   1.0000   0.9632
  -2.000  -0.1555   0.01729   0.00688  -0.0074   1.0000   0.9858
  -1.750  -0.1112   0.01698   0.00639  -0.0115   1.0000   1.0000
  -1.500  -0.0942   0.01670   0.00604  -0.0103   1.0000   1.0000
  -1.250  -0.0774   0.01648   0.00573  -0.0090   1.0000   1.0000
  -1.000  -0.0611   0.01630   0.00551  -0.0074   1.0000   1.0000
  -0.750  -0.0453   0.01616   0.00534  -0.0057   1.0000   1.0000
  -0.500  -0.0299   0.01607   0.00522  -0.0039   1.0000   1.0000
  -0.250  -0.0149   0.01601   0.00514  -0.0020   1.0000   1.0000
   0.000   0.0000   0.01599   0.00512   0.0000   1.0000   1.0000
   0.250   0.0149   0.01601   0.00514   0.0020   1.0000   1.0000
   0.500   0.0299   0.01607   0.00522   0.0039   1.0000   1.0000
   0.750   0.0453   0.01616   0.00533   0.0057   1.0000   1.0000
   1.000   0.0611   0.01630   0.00551   0.0074   1.0000   1.0000
   1.250   0.0774   0.01647   0.00573   0.0090   1.0000   1.0000
   1.500   0.0942   0.01670   0.00603   0.0103   1.0000   1.0000
   1.750   0.1112   0.01697   0.00639   0.0115   1.0000   1.0000
   2.000   0.1555   0.01729   0.00688   0.0074   0.9858   1.0000
   2.250   0.2114   0.01751   0.00738   0.0013   0.9632   1.0000
   2.500   0.2678   0.01759   0.00778  -0.0044   0.9362   1.0000
   2.750   0.3202   0.01747   0.00801  -0.0083   0.8954   1.0000
   3.000   0.3640   0.01724   0.00802  -0.0097   0.8357   1.0000
   3.250   0.3949   0.01708   0.00783  -0.0077   0.7372   1.0000
   3.500   0.4128   0.01750   0.00748  -0.0030   0.5576   1.0000
   3.750   0.4263   0.01874   0.00763   0.0003   0.3564   1.0000
   4.000   0.4432   0.02028   0.00831   0.0018   0.2078   1.0000
   4.250   0.4644   0.02177   0.00936   0.0025   0.1443   1.0000
   4.500   0.4873   0.02302   0.01054   0.0032   0.1211   1.0000
   4.750   0.5109   0.02417   0.01175   0.0041   0.1094   1.0000
   5.000   0.5347   0.02531   0.01297   0.0049   0.1001   1.0000
   5.250   0.5579   0.02651   0.01410   0.0056   0.0909   1.0000
   5.500   0.5834   0.02779   0.01570   0.0065   0.0856   1.0000
   5.750   0.6086   0.02932   0.01739   0.0072   0.0816   1.0000
   6.000   0.6334   0.03111   0.01927   0.0079   0.0784   1.0000
   6.250   0.6579   0.03318   0.02168   0.0086   0.0749   1.0000
   6.500   0.6806   0.03506   0.02396   0.0094   0.0692   1.0000
   6.750   0.7025   0.03737   0.02659   0.0101   0.0662   1.0000
   7.000   0.7225   0.04025   0.02966   0.0107   0.0639   1.0000
   7.250   0.7389   0.04342   0.03360   0.0120   0.0607   1.0000
   7.500   0.7528   0.04684   0.03760   0.0130   0.0576   1.0000
   7.750   0.7636   0.05082   0.04208   0.0139   0.0564   1.0000
   8.000   0.7713   0.05493   0.04662   0.0147   0.0553   1.0000
   8.250   0.7789   0.05844   0.05039   0.0152   0.0535   1.0000
   8.500   0.7897   0.06150   0.05335   0.0157   0.0510   1.0000
   8.750   0.7842   0.06640   0.05871   0.0159   0.0505   1.0000
   9.000   0.7760   0.07143   0.06404   0.0155   0.0502   1.0000
   9.250   0.7658   0.07648   0.06927   0.0146   0.0502   1.0000
   9.500   0.7535   0.08140   0.07428   0.0134   0.0504   1.0000
   9.750   0.7413   0.08663   0.07955   0.0111   0.0507   1.0000
  10.000   0.7320   0.09241   0.08533   0.0076   0.0509   1.0000
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