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NACA M18 (nacam18-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA M18 (nacam18-il)
Reynolds number: 50,000
Max Cl/Cd: 26.18 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nacam18-il-50000-n5.txt
Download as CSV file: xf-nacam18-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M18                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3519   0.10127   0.09481  -0.0244   1.0000   0.1362
  -8.000  -0.3504   0.09819   0.09181  -0.0264   1.0000   0.1393
  -7.750  -0.3672   0.09605   0.08983  -0.0306   1.0000   0.1435
  -7.500  -0.3940   0.09516   0.08906  -0.0333   1.0000   0.1448
  -7.000  -0.3650   0.08684   0.08085  -0.0336   0.9832   0.1489
  -6.750  -0.3441   0.08291   0.07685  -0.0373   0.9657   0.1548
  -6.250  -0.3182   0.06756   0.06045  -0.0552   0.9293   0.0834
  -6.000  -0.2967   0.06409   0.05695  -0.0560   0.9165   0.0819
  -5.750  -0.2787   0.06074   0.05345  -0.0570   0.9034   0.0803
  -5.500  -0.2618   0.05746   0.04994  -0.0577   0.8909   0.0787
  -5.250  -0.2446   0.05423   0.04642  -0.0581   0.8796   0.0772
  -5.000  -0.2288   0.05133   0.04322  -0.0578   0.8671   0.0762
  -4.750  -0.2119   0.04882   0.04040  -0.0573   0.8555   0.0767
  -4.500  -0.1933   0.04644   0.03766  -0.0567   0.8456   0.0776
  -4.250  -0.1746   0.04419   0.03505  -0.0558   0.8351   0.0781
  -4.000  -0.1552   0.04204   0.03253  -0.0548   0.8249   0.0779
  -3.750  -0.1334   0.03993   0.03001  -0.0539   0.8166   0.0776
  -3.500  -0.1122   0.03814   0.02786  -0.0529   0.8062   0.0777
  -3.250  -0.0883   0.03638   0.02570  -0.0521   0.7986   0.0780
  -3.000  -0.0649   0.03491   0.02389  -0.0513   0.7887   0.0786
  -2.750  -0.0391   0.03355   0.02214  -0.0505   0.7812   0.0804
  -2.500  -0.0131   0.03249   0.02065  -0.0499   0.7720   0.0830
  -2.250   0.0136   0.03139   0.01943  -0.0496   0.7647   0.0857
  -2.000   0.0403   0.03053   0.01844  -0.0494   0.7557   0.0880
  -1.750   0.0711   0.02962   0.01731  -0.0494   0.7490   0.0908
  -1.500   0.1043   0.02890   0.01640  -0.0501   0.7400   0.0946
  -1.250   0.1390   0.02812   0.01546  -0.0508   0.7340   0.1007
  -1.000   0.1672   0.02779   0.01508  -0.0510   0.7247   0.1099
  -0.750   0.1951   0.02720   0.01446  -0.0506   0.7185   0.1209
  -0.500   0.2190   0.02688   0.01417  -0.0500   0.7095   0.1375
  -0.250   0.2431   0.02633   0.01372  -0.0491   0.7032   0.1725
   0.000   0.2623   0.02568   0.01359  -0.0480   0.6951   0.2574
   0.250   0.3968   0.02376   0.01319  -0.0669   0.6883   1.0000
   0.500   0.4197   0.02403   0.01324  -0.0661   0.6807   1.0000
   0.750   0.4425   0.02428   0.01330  -0.0653   0.6730   1.0000
   1.000   0.4653   0.02452   0.01335  -0.0644   0.6661   1.0000
   1.250   0.4874   0.02487   0.01358  -0.0637   0.6579   1.0000
   1.500   0.5110   0.02500   0.01352  -0.0627   0.6524   1.0000
   1.750   0.5316   0.02554   0.01402  -0.0620   0.6431   1.0000
   2.000   0.5549   0.02571   0.01404  -0.0611   0.6373   1.0000
   2.250   0.5752   0.02628   0.01458  -0.0603   0.6287   1.0000
   2.500   0.5979   0.02653   0.01473  -0.0594   0.6223   1.0000
   2.750   0.6184   0.02703   0.01519  -0.0585   0.6147   1.0000
   3.000   0.6398   0.02744   0.01556  -0.0576   0.6076   1.0000
   3.250   0.6622   0.02774   0.01578  -0.0566   0.6015   1.0000
   3.500   0.6807   0.02841   0.01648  -0.0557   0.5929   1.0000
   3.750   0.7047   0.02857   0.01657  -0.0547   0.5878   1.0000
   4.000   0.7207   0.02945   0.01751  -0.0536   0.5786   1.0000
   4.250   0.7437   0.02969   0.01771  -0.0527   0.5728   1.0000
   4.500   0.7602   0.03052   0.01860  -0.0515   0.5646   1.0000
   4.750   0.7812   0.03091   0.01900  -0.0505   0.5580   1.0000
   5.000   0.8000   0.03152   0.01963  -0.0494   0.5510   1.0000
   5.250   0.8172   0.03223   0.02041  -0.0481   0.5433   1.0000
   5.500   0.8436   0.03222   0.02037  -0.0474   0.5388   1.0000
   5.750   0.8516   0.03364   0.02192  -0.0456   0.5288   1.0000
   6.000   0.8771   0.03370   0.02199  -0.0449   0.5239   1.0000
   6.250   0.8842   0.03514   0.02356  -0.0430   0.5144   1.0000
   6.500   0.9081   0.03533   0.02379  -0.0421   0.5091   1.0000
   6.750   0.9151   0.03677   0.02535  -0.0402   0.5003   1.0000
   7.000   0.9364   0.03714   0.02578  -0.0392   0.4944   1.0000
   7.250   0.9456   0.03844   0.02719  -0.0374   0.4866   1.0000
   7.500   0.9610   0.03926   0.02811  -0.0361   0.4797   1.0000
   7.750   0.9925   0.03895   0.02787  -0.0358   0.4759   1.0000
   8.000   0.9810   0.04173   0.03079  -0.0327   0.4649   1.0000
   8.250   1.0124   0.04143   0.03060  -0.0325   0.4610   1.0000
   8.500   0.9951   0.04468   0.03397  -0.0292   0.4499   1.0000
   8.750   1.0267   0.04435   0.03376  -0.0290   0.4459   1.0000
   9.000   0.9980   0.04850   0.03797  -0.0253   0.4343   1.0000
   9.250   1.0322   0.04794   0.03757  -0.0251   0.4305   1.0000
   9.500   0.9940   0.05327   0.04292  -0.0220   0.4178   1.0000
   9.750   1.0296   0.05231   0.04215  -0.0214   0.4145   1.0000
  10.000   0.9955   0.05822   0.04810  -0.0199   0.4011   1.0000
  10.250   1.0312   0.05660   0.04664  -0.0187   0.3965   1.0000
  10.500   1.0180   0.06039   0.05051  -0.0178   0.3843   1.0000
  11.000   1.0135   0.06587   0.05618  -0.0163   0.3630   1.0000
  11.250   1.0221   0.06735   0.05779  -0.0155   0.3541   1.0000
  11.750   1.0386   0.07055   0.06131  -0.0140   0.3376   1.0000
  12.250   1.0494   0.07448   0.06552  -0.0128   0.3199   1.0000
  12.750   1.0297   0.08267   0.07392  -0.0130   0.2949   1.0000
  13.000   1.0384   0.08329   0.07468  -0.0121   0.2815   1.0000
  13.250   1.0980   0.07408   0.06568  -0.0081   0.2602   1.0000
  13.500   1.0890   0.07764   0.06933  -0.0083   0.2433   1.0000
  13.750   1.0816   0.08112   0.07288  -0.0085   0.2256   1.0000
  14.000   1.0809   0.08353   0.07535  -0.0085   0.2048   1.0000
  14.250   1.0797   0.08620   0.07802  -0.0087   0.1819   1.0000
  14.500   1.0797   0.08861   0.08028  -0.0087   0.1560   1.0000
  14.750   1.0771   0.09141   0.08276  -0.0087   0.1328   1.0000
  15.000   1.0695   0.09541   0.08651  -0.0092   0.1166   1.0000
  15.250   1.0618   0.09959   0.09050  -0.0098   0.1040   1.0000
  15.500   1.0556   0.10381   0.09469  -0.0106   0.0931   1.0000
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