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NACA M18 AIRFOIL (m18-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA M18 AIRFOIL (m18-il)
Reynolds number: 1,000,000
Max Cl/Cd: 127.23 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m18-il-1000000.txt
Download as CSV file: xf-m18-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M18 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3435   0.08385   0.08164  -0.0215   0.7524   0.0239
  -9.000  -0.3407   0.08069   0.07844  -0.0223   0.7417   0.0240
  -8.750  -0.4632   0.08156   0.07936  -0.0226   0.7723   0.0237
  -8.500  -0.4642   0.07811   0.07585  -0.0247   0.7590   0.0239
  -8.250  -0.4613   0.07512   0.07280  -0.0261   0.7462   0.0240
  -8.000  -0.4545   0.07205   0.06966  -0.0278   0.7344   0.0242
  -7.750  -0.4462   0.06897   0.06651  -0.0293   0.7237   0.0244
  -7.500  -0.4364   0.06595   0.06340  -0.0308   0.7132   0.0247
  -7.250  -0.4256   0.06271   0.06008  -0.0322   0.7038   0.0253
  -7.000  -0.4148   0.05878   0.05602  -0.0337   0.6950   0.0262
  -6.750  -0.4308   0.04096   0.03763  -0.0364   0.6922   0.0284
  -6.500  -0.4127   0.03959   0.03616  -0.0360   0.6833   0.0286
  -6.250  -0.3937   0.03810   0.03457  -0.0356   0.6755   0.0288
  -6.000  -0.3741   0.03652   0.03287  -0.0352   0.6679   0.0292
  -5.750  -0.3534   0.03508   0.03132  -0.0348   0.6612   0.0297
  -5.500  -0.3334   0.03291   0.02899  -0.0343   0.6552   0.0306
  -5.250  -0.3302   0.02406   0.01916  -0.0305   0.6511   0.0339
  -5.000  -0.3070   0.02273   0.01773  -0.0300   0.6454   0.0343
  -4.750  -0.2917   0.01672   0.01073  -0.0269   0.6412   0.0281
  -4.500  -0.2663   0.01537   0.00918  -0.0265   0.6356   0.0282
  -4.250  -0.2401   0.01434   0.00799  -0.0262   0.6298   0.0284
  -4.000  -0.2130   0.01351   0.00708  -0.0260   0.6248   0.0286
  -3.750  -0.1858   0.01288   0.00638  -0.0258   0.6191   0.0289
  -3.500  -0.1584   0.01239   0.00582  -0.0257   0.6137   0.0291
  -3.250  -0.1307   0.01193   0.00533  -0.0256   0.6091   0.0294
  -3.000  -0.1030   0.01153   0.00490  -0.0255   0.6038   0.0297
  -2.750  -0.0754   0.01120   0.00450  -0.0254   0.5985   0.0301
  -2.500  -0.0476   0.01088   0.00417  -0.0254   0.5936   0.0305
  -2.250  -0.0198   0.01062   0.00389  -0.0253   0.5880   0.0312
  -2.000   0.0079   0.01038   0.00360  -0.0252   0.5822   0.0318
  -1.750   0.0357   0.01013   0.00333  -0.0251   0.5767   0.0323
  -1.500   0.0636   0.00992   0.00309  -0.0251   0.5705   0.0327
  -1.250   0.0914   0.00978   0.00290  -0.0250   0.5644   0.0330
  -1.000   0.1190   0.00951   0.00261  -0.0249   0.5587   0.0335
  -0.750   0.1464   0.00926   0.00233  -0.0248   0.5521   0.0345
  -0.500   0.1742   0.00911   0.00217  -0.0247   0.5457   0.0356
  -0.250   0.2023   0.00899   0.00204  -0.0247   0.5384   0.0368
   0.000   0.2304   0.00892   0.00193  -0.0247   0.5310   0.0382
   0.250   0.2586   0.00882   0.00183  -0.0248   0.5230   0.0402
   0.500   0.2865   0.00875   0.00174  -0.0248   0.5152   0.0443
   0.750   0.3143   0.00862   0.00168  -0.0248   0.5074   0.0624
   1.000   0.3414   0.00846   0.00167  -0.0247   0.4998   0.1174
   1.500   0.3952   0.00813   0.00170  -0.0246   0.4848   0.2666
   1.750   0.4004   0.00623   0.00169  -0.0201   0.4794   0.8907
   2.000   0.4301   0.00635   0.00189  -0.0201   0.4722   0.9504
   2.250   0.4602   0.00654   0.00205  -0.0203   0.4654   0.9683
   2.500   0.4989   0.00676   0.00221  -0.0226   0.4578   0.9748
   2.750   0.5423   0.00699   0.00239  -0.0260   0.4511   0.9799
   3.000   0.5916   0.00724   0.00259  -0.0307   0.4445   0.9847
   3.250   0.6421   0.00748   0.00275  -0.0357   0.4382   0.9879
   3.500   0.6847   0.00760   0.00287  -0.0390   0.4341   0.9913
   3.750   0.7239   0.00773   0.00298  -0.0415   0.4298   0.9942
   4.000   0.7608   0.00782   0.00303  -0.0437   0.4247   0.9953
   4.250   0.7925   0.00787   0.00307  -0.0447   0.4202   0.9960
   4.500   0.8240   0.00791   0.00311  -0.0457   0.4160   0.9967
   4.750   0.8552   0.00799   0.00317  -0.0466   0.4115   0.9974
   5.000   0.8862   0.00811   0.00326  -0.0476   0.4066   0.9982
   5.250   0.9180   0.00814   0.00332  -0.0486   0.4034   0.9990
   5.500   0.9496   0.00820   0.00339  -0.0496   0.3992   0.9997
   5.750   0.9780   0.00829   0.00348  -0.0500   0.3945   1.0000
   6.000   1.0036   0.00840   0.00358  -0.0497   0.3901   1.0000
   6.250   1.0295   0.00844   0.00365  -0.0495   0.3854   1.0000
   6.500   1.0549   0.00854   0.00374  -0.0493   0.3786   1.0000
   6.750   1.0803   0.00864   0.00384  -0.0490   0.3721   1.0000
   7.000   1.1051   0.00877   0.00395  -0.0486   0.3610   1.0000
   7.250   1.1299   0.00889   0.00406  -0.0482   0.3493   1.0000
   7.500   1.1540   0.00907   0.00420  -0.0477   0.3356   1.0000
   7.750   1.1773   0.00931   0.00438  -0.0472   0.3184   1.0000
   8.000   1.1996   0.00963   0.00462  -0.0465   0.2968   1.0000
   8.250   1.2200   0.01012   0.00496  -0.0455   0.2671   1.0000
   8.500   1.2392   0.01068   0.00537  -0.0443   0.2396   1.0000
   8.750   1.2578   0.01124   0.00581  -0.0431   0.2146   1.0000
   9.000   1.2741   0.01192   0.00633  -0.0414   0.1842   1.0000
   9.250   1.2823   0.01311   0.00718  -0.0386   0.1297   1.0000
   9.500   1.2924   0.01401   0.00792  -0.0360   0.1024   1.0000
   9.750   1.2995   0.01498   0.00870  -0.0329   0.0701   1.0000
  10.000   1.3005   0.01614   0.00967  -0.0288   0.0424   1.0000
  10.250   1.3058   0.01695   0.01043  -0.0254   0.0312   1.0000
  10.500   1.3118   0.01765   0.01111  -0.0220   0.0262   1.0000
  10.750   1.3099   0.01836   0.01184  -0.0173   0.0236   1.0000
  11.000   1.3160   0.01910   0.01262  -0.0144   0.0221   1.0000
  11.250   1.3234   0.02006   0.01361  -0.0123   0.0206   1.0000
  11.500   1.3295   0.02132   0.01492  -0.0105   0.0191   1.0000
  11.750   1.3406   0.02238   0.01603  -0.0094   0.0184   1.0000
  12.000   1.3505   0.02363   0.01733  -0.0084   0.0177   1.0000
  12.250   1.3589   0.02508   0.01883  -0.0075   0.0170   1.0000
  12.500   1.3649   0.02682   0.02062  -0.0067   0.0163   1.0000
  12.750   1.3656   0.02914   0.02303  -0.0058   0.0156   1.0000
  13.000   1.3740   0.03081   0.02477  -0.0054   0.0153   1.0000
  13.250   1.3804   0.03272   0.02674  -0.0050   0.0150   1.0000
  13.500   1.3854   0.03478   0.02888  -0.0046   0.0146   1.0000
  13.750   1.3895   0.03697   0.03113  -0.0043   0.0142   1.0000
  14.000   1.3928   0.03926   0.03348  -0.0041   0.0139   1.0000
  14.250   1.3936   0.04181   0.03610  -0.0038   0.0135   1.0000
  14.500   1.3916   0.04471   0.03907  -0.0036   0.0132   1.0000
  14.750   1.3854   0.04812   0.04255  -0.0035   0.0129   1.0000
  15.000   1.3751   0.05213   0.04667  -0.0035   0.0126   1.0000
  15.250   1.3742   0.05517   0.04979  -0.0037   0.0125   1.0000
  15.500   1.3747   0.05808   0.05277  -0.0039   0.0124   1.0000
  15.750   1.3740   0.06119   0.05597  -0.0042   0.0122   1.0000
  16.000   1.3728   0.06442   0.05927  -0.0046   0.0120   1.0000
  16.250   1.3711   0.06776   0.06269  -0.0051   0.0118   1.0000
  16.500   1.3685   0.07122   0.06623  -0.0056   0.0117   1.0000
  16.750   1.3657   0.07478   0.06986  -0.0062   0.0115   1.0000
  17.000   1.3628   0.07839   0.07355  -0.0069   0.0113   1.0000
  17.250   1.3598   0.08203   0.07726  -0.0076   0.0111   1.0000
  17.500   1.3567   0.08570   0.08100  -0.0084   0.0110   1.0000
  17.750   1.3525   0.08957   0.08493  -0.0093   0.0108   1.0000
  18.000   1.3485   0.09345   0.08888  -0.0102   0.0107   1.0000
  18.250   1.3438   0.09745   0.09294  -0.0112   0.0106   1.0000
  18.500   1.3374   0.10170   0.09726  -0.0123   0.0104   1.0000
  18.750   1.3305   0.10599   0.10162  -0.0134   0.0102   1.0000
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