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NACA M27 AIRFOIL (m27-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M27 AIRFOIL (m27-il)
Reynolds number: 1,000,000
Max Cl/Cd: 135.9 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m27-il-1000000.txt
Download as CSV file: xf-m27-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M27 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1823   0.09298   0.08993  -0.0155   0.5507   0.0159
  -7.500  -0.1758   0.09016   0.08713  -0.0177   0.5483   0.0163
  -7.250  -0.1700   0.08750   0.08447  -0.0195   0.5455   0.0168
  -7.000  -0.1580   0.08417   0.08110  -0.0230   0.5428   0.0178
  -6.750  -0.1427   0.08039   0.07728  -0.0288   0.5402   0.0181
  -6.500  -0.1265   0.07675   0.07357  -0.0331   0.5372   0.0181
  -6.250  -0.1133   0.07267   0.06945  -0.0351   0.5345   0.0182
  -6.000  -0.0997   0.06979   0.06656  -0.0355   0.5318   0.0184
  -5.750  -0.0831   0.06727   0.06402  -0.0367   0.5288   0.0185
  -5.500  -0.0648   0.06485   0.06155  -0.0382   0.5257   0.0187
  -5.250  -0.0451   0.06244   0.05909  -0.0399   0.5226   0.0190
  -5.000  -0.0242   0.06000   0.05658  -0.0416   0.5194   0.0195
  -4.750  -0.0020   0.05744   0.05398  -0.0434   0.5171   0.0205
  -4.500   0.0330   0.05406   0.05044  -0.0473   0.5146   0.0216
  -4.250   0.0576   0.05121   0.04750  -0.0487   0.5117   0.0217
  -4.000   0.0819   0.04847   0.04465  -0.0498   0.5087   0.0217
  -3.750   0.0986   0.04510   0.04121  -0.0502   0.5056   0.0220
  -3.500   0.1203   0.04331   0.03938  -0.0506   0.5028   0.0223
  -3.250   0.1437   0.04161   0.03763  -0.0511   0.5005   0.0226
  -3.000   0.1684   0.03985   0.03581  -0.0517   0.4977   0.0230
  -2.750   0.1941   0.03801   0.03388  -0.0523   0.4948   0.0238
  -2.000   0.2826   0.03161   0.02702  -0.0530   0.4863   0.0259
  -1.750   0.3039   0.02879   0.02409  -0.0528   0.4841   0.0264
  -1.500   0.3290   0.02766   0.02292  -0.0530   0.4814   0.0267
  -1.250   0.3551   0.02652   0.02169  -0.0531   0.4785   0.0272
  -1.000   0.3818   0.02531   0.02037  -0.0532   0.4754   0.0279
  -0.750   0.4140   0.02360   0.01844  -0.0526   0.4722   0.0307
  -0.500   0.4390   0.02044   0.01504  -0.0517   0.4704   0.0314
  -0.250   0.4656   0.01966   0.01422  -0.0519   0.4679   0.0318
   0.000   0.4928   0.01894   0.01343  -0.0520   0.4652   0.0323
   0.250   0.5204   0.01812   0.01251  -0.0520   0.4624   0.0332
   0.500   0.5506   0.01711   0.01126  -0.0516   0.4595   0.0366
   0.750   0.5763   0.01509   0.00902  -0.0512   0.4565   0.0381
   1.000   0.6044   0.01464   0.00854  -0.0515   0.4543   0.0390
   1.250   0.6329   0.01407   0.00790  -0.0516   0.4517   0.0408
   1.500   0.6614   0.01327   0.00692  -0.0516   0.4491   0.0457
   1.750   0.6897   0.01294   0.00655  -0.0519   0.4463   0.0471
   2.000   0.7187   0.01066   0.00378  -0.0510   0.4436   0.0317
   2.250   0.7460   0.01049   0.00361  -0.0510   0.4408   0.0324
   2.500   0.7736   0.01032   0.00345  -0.0511   0.4385   0.0330
   2.750   0.8012   0.01020   0.00333  -0.0512   0.4359   0.0337
   3.000   0.8287   0.01012   0.00325  -0.0513   0.4332   0.0347
   3.250   0.8561   0.01010   0.00321  -0.0514   0.4305   0.0357
   3.500   0.8835   0.01013   0.00322  -0.0516   0.4274   0.0366
   3.750   0.9109   0.01010   0.00319  -0.0517   0.4250   0.0384
   4.000   0.9389   0.01008   0.00320  -0.0519   0.4227   0.0415
   4.250   0.9667   0.01007   0.00323  -0.0522   0.4201   0.0507
   4.500   0.9942   0.01008   0.00334  -0.0524   0.4174   0.0919
   4.750   1.0218   0.01016   0.00344  -0.0527   0.4147   0.1101
   5.000   1.0488   0.01027   0.00359  -0.0529   0.4114   0.1400
   5.250   1.0724   0.00989   0.00380  -0.0526   0.4095   0.5160
   5.500   1.0859   0.00898   0.00404  -0.0495   0.4076   0.9699
   5.750   1.1319   0.00928   0.00434  -0.0537   0.4046   0.9837
   6.000   1.1982   0.00962   0.00465  -0.0627   0.4011   0.9881
   6.250   1.2407   0.00992   0.00489  -0.0665   0.3962   0.9913
   6.500   1.2844   0.01005   0.00504  -0.0704   0.3922   0.9942
   6.750   1.3403   0.01018   0.00516  -0.0771   0.3875   0.9968
   7.000   1.3831   0.01041   0.00535  -0.0811   0.3808   0.9990
   7.250   1.4184   0.01049   0.00545  -0.0832   0.3770   1.0000
   7.500   1.4433   0.01062   0.00560  -0.0831   0.3721   1.0000
   7.750   1.4670   0.01087   0.00581  -0.0830   0.3657   1.0000
   8.000   1.4918   0.01098   0.00594  -0.0828   0.3604   1.0000
   8.250   1.5150   0.01122   0.00616  -0.0826   0.3531   1.0000
   8.500   1.5380   0.01145   0.00639  -0.0823   0.3442   1.0000
   8.750   1.5589   0.01185   0.00672  -0.0817   0.3291   1.0000
   9.000   1.5753   0.01258   0.00729  -0.0806   0.3033   1.0000
   9.250   1.5790   0.01409   0.00848  -0.0778   0.2547   1.0000
   9.500   1.5577   0.01651   0.01054  -0.0713   0.1981   1.0000
   9.750   1.5280   0.01811   0.01210  -0.0630   0.1830   1.0000
  10.000   1.4988   0.02026   0.01423  -0.0560   0.1684   1.0000
  10.250   1.4685   0.02356   0.01744  -0.0507   0.1438   1.0000
  10.500   1.4405   0.02746   0.02124  -0.0468   0.1180   1.0000
  10.750   1.4129   0.03187   0.02557  -0.0439   0.0915   1.0000
  11.000   1.3855   0.03661   0.03024  -0.0416   0.0642   1.0000
  11.250   1.3598   0.04142   0.03500  -0.0397   0.0401   1.0000
  11.500   1.3420   0.04575   0.03931  -0.0385   0.0212   1.0000
  11.750   1.3395   0.04867   0.04227  -0.0379   0.0182   1.0000
  12.000   1.3405   0.05129   0.04495  -0.0374   0.0173   1.0000
  12.250   1.3408   0.05397   0.04769  -0.0370   0.0165   1.0000
  12.500   1.3402   0.05683   0.05061  -0.0366   0.0159   1.0000
  12.750   1.3379   0.05994   0.05378  -0.0363   0.0152   1.0000
  13.000   1.3347   0.06315   0.05707  -0.0359   0.0145   1.0000
  13.250   1.3346   0.06606   0.06004  -0.0357   0.0141   1.0000
  13.500   1.3348   0.06897   0.06300  -0.0356   0.0138   1.0000
  13.750   1.3348   0.07192   0.06602  -0.0354   0.0134   1.0000
  14.000   1.3330   0.07512   0.06929  -0.0354   0.0131   1.0000
  14.250   1.3322   0.07821   0.07244  -0.0353   0.0128   1.0000
  14.500   1.3294   0.08163   0.07592  -0.0354   0.0125   1.0000
  14.750   1.3276   0.08492   0.07927  -0.0354   0.0122   1.0000
  15.000   1.3224   0.08869   0.08311  -0.0356   0.0119   1.0000
  15.250   1.3169   0.09253   0.08702  -0.0357   0.0116   1.0000
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