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NACA M9 AIRFOIL (m9-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA M9 AIRFOIL (m9-il)
Reynolds number: 100,000
Max Cl/Cd: 43.54 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m9-il-100000.txt
Download as CSV file: xf-m9-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M9 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.1625   0.10081   0.09724  -0.0175   0.9545   0.0804
  -8.750  -0.1643   0.10039   0.09677  -0.0238   0.9238   0.0826
  -8.500  -0.1741   0.10051   0.09686  -0.0266   0.8967   0.0830
  -8.250  -0.1481   0.09208   0.08836  -0.0227   0.8794   0.0846
  -8.000  -0.1381   0.08866   0.08489  -0.0211   0.8607   0.0865
  -7.750  -0.1324   0.08607   0.08226  -0.0205   0.8439   0.0886
  -7.500  -0.1284   0.08364   0.07980  -0.0205   0.8284   0.0913
  -7.250  -0.1280   0.08175   0.07788  -0.0213   0.8141   0.0943
  -7.000  -0.1398   0.08187   0.07800  -0.0237   0.8004   0.0961
  -6.750  -0.1452   0.08176   0.07783  -0.0298   0.7885   0.0968
  -6.500  -0.1243   0.07399   0.07007  -0.0230   0.7765   0.0993
  -6.250  -0.1126   0.07093   0.06697  -0.0218   0.7645   0.1028
  -6.000  -0.1067   0.06849   0.06445  -0.0224   0.7544   0.1068
  -5.750  -0.0999   0.06843   0.06433  -0.0339   0.7420   0.1117
  -5.500  -0.0906   0.06309   0.05899  -0.0314   0.7329   0.1131
  -5.250  -0.0782   0.05937   0.05524  -0.0283   0.7231   0.1156
  -5.000  -0.0639   0.05660   0.05244  -0.0288   0.7129   0.1206
  -4.750  -0.0459   0.05388   0.04957  -0.0364   0.7048   0.1286
  -4.500  -0.0395   0.06363   0.05899  -0.0404   0.7168   0.1308
  -4.250  -0.0213   0.06136   0.05665  -0.0403   0.7066   0.1370
  -4.000   0.0053   0.05886   0.05402  -0.0449   0.6964   0.1456
  -3.750   0.0260   0.05701   0.05205  -0.0450   0.6880   0.1559
  -3.500   0.0468   0.05452   0.04955  -0.0456   0.6779   0.1637
  -3.250   0.0723   0.05247   0.04733  -0.0475   0.6708   0.1748
  -3.000   0.0988   0.05066   0.04545  -0.0492   0.6613   0.1868
  -2.750   0.1236   0.04887   0.04351  -0.0499   0.6546   0.1989
  -2.500   0.1540   0.04734   0.04185  -0.0522   0.6459   0.2095
  -2.250   0.2065   0.03823   0.03181  -0.0622   0.6405   0.1430
  -2.000   0.2298   0.03621   0.02968  -0.0616   0.6346   0.1397
  -1.750   0.2603   0.03319   0.02635  -0.0632   0.6266   0.1388
  -1.500   0.2913   0.02849   0.02096  -0.0645   0.6216   0.1388
  -1.250   0.3201   0.02587   0.01782  -0.0649   0.6159   0.1467
  -1.000   0.3479   0.02527   0.01709  -0.0648   0.6088   0.1547
  -0.750   0.3743   0.02555   0.01734  -0.0637   0.6035   0.1632
  -0.500   0.4020   0.02550   0.01722  -0.0636   0.5960   0.1735
  -0.250   0.4288   0.02591   0.01759  -0.0627   0.5893   0.1851
   0.000   0.4557   0.02621   0.01779  -0.0618   0.5832   0.1972
   0.250   0.4821   0.02663   0.01822  -0.0611   0.5745   0.2108
   0.500   0.5088   0.02647   0.01785  -0.0598   0.5688   0.2271
   0.750   0.5351   0.02654   0.01788  -0.0596   0.5591   0.2483
   1.000   0.5612   0.02599   0.01714  -0.0585   0.5532   0.2740
   1.250   0.5863   0.02567   0.01681  -0.0582   0.5448   0.3053
   1.500   0.6124   0.02515   0.01610  -0.0574   0.5386   0.3401
   1.750   0.6380   0.02474   0.01564  -0.0569   0.5324   0.3635
   2.000   0.6643   0.02465   0.01552  -0.0567   0.5247   0.3804
   2.250   0.6918   0.02430   0.01500  -0.0560   0.5193   0.3949
   2.500   0.7177   0.02451   0.01526  -0.0559   0.5106   0.4051
   2.750   0.7451   0.02432   0.01494  -0.0553   0.5041   0.4161
   3.000   0.7726   0.02437   0.01505  -0.0553   0.4960   0.4264
   3.250   0.8021   0.02430   0.01490  -0.0553   0.4884   0.4363
   3.500   0.8307   0.02438   0.01497  -0.0553   0.4805   0.4418
   3.750   0.8587   0.02441   0.01494  -0.0549   0.4718   0.4422
   4.000   0.8857   0.02457   0.01508  -0.0546   0.4628   0.4412
   4.250   0.9133   0.02452   0.01494  -0.0540   0.4539   0.4404
   4.500   0.9388   0.02476   0.01523  -0.0535   0.4434   0.4399
   4.750   0.9667   0.02462   0.01494  -0.0528   0.4354   0.4401
   5.000   0.9908   0.02494   0.01535  -0.0523   0.4232   0.4404
   5.250   1.0162   0.02510   0.01547  -0.0516   0.4129   0.4404
   5.500   1.0425   0.02510   0.01538  -0.0508   0.4029   0.4399
   5.750   1.0657   0.02548   0.01583  -0.0502   0.3905   0.4396
   6.000   1.0906   0.02573   0.01601  -0.0495   0.3804   0.4394
   6.250   1.1157   0.02592   0.01615  -0.0488   0.3708   0.4395
   6.500   1.1382   0.02654   0.01687  -0.0482   0.3608   0.4398
   6.750   1.1643   0.02674   0.01696  -0.0476   0.3538   0.4404
   7.000   1.1854   0.02760   0.01798  -0.0470   0.3452   0.4411
   7.250   1.2105   0.02797   0.01831  -0.0464   0.3390   0.4424
   7.500   1.2329   0.02878   0.01920  -0.0458   0.3328   0.4439
   7.750   1.2543   0.02956   0.02012  -0.0452   0.3263   0.4459
   8.000   1.2809   0.02988   0.02034  -0.0448   0.3218   0.4498
   8.250   1.2992   0.03106   0.02179  -0.0441   0.3162   0.4549
   8.500   1.3189   0.03206   0.02298  -0.0435   0.3113   0.4641
   8.750   1.3403   0.03238   0.02364  -0.0426   0.3078   0.6467
   9.000   1.3831   0.03328   0.02497  -0.0462   0.3035   1.0000
   9.250   1.3945   0.03510   0.02710  -0.0452   0.2990   1.0000
   9.500   1.4122   0.03624   0.02835  -0.0443   0.2950   1.0000
   9.750   1.4378   0.03663   0.02867  -0.0438   0.2915   1.0000
  10.000   1.4547   0.03793   0.03009  -0.0429   0.2878   1.0000
  10.250   1.4577   0.04017   0.03265  -0.0414   0.2834   1.0000
  10.500   1.4719   0.04140   0.03399  -0.0404   0.2795   1.0000
  10.750   1.4992   0.04163   0.03417  -0.0399   0.2762   1.0000
  11.000   1.5143   0.04309   0.03573  -0.0390   0.2731   1.0000
  11.250   1.4899   0.04732   0.04036  -0.0365   0.2702   1.0000
  12.250   1.5024   0.05523   0.04868  -0.0311   0.2586   1.0000
  13.000   0.9175   0.16256   0.15561  -0.0807   0.2930   0.4625
  13.250   0.9737   0.16677   0.16068  -0.0809   0.2895   1.0000
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