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NACA M18 AIRFOIL (m18-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA M18 AIRFOIL (m18-il)
Reynolds number: 500,000
Max Cl/Cd: 103.53 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m18-il-500000.txt
Download as CSV file: xf-m18-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4127   0.10622   0.10410  -0.0100   1.0000   0.0292
  -9.500  -0.4063   0.10296   0.10082  -0.0120   0.9397   0.0297
  -9.250  -0.4070   0.10014   0.09788  -0.0119   0.8975   0.0303
  -9.000  -0.3339   0.08261   0.08015  -0.0286   0.8184   0.0333
  -8.750  -0.3290   0.07944   0.07692  -0.0275   0.8056   0.0336
  -8.500  -0.3249   0.07646   0.07389  -0.0276   0.7936   0.0339
  -8.250  -0.3222   0.07325   0.07064  -0.0283   0.7818   0.0341
  -8.000  -0.3220   0.06975   0.06711  -0.0295   0.7713   0.0344
  -7.750  -0.3276   0.06561   0.06292  -0.0322   0.7618   0.0347
  -7.500  -0.4171   0.06961   0.06678  -0.0322   0.7815   0.0342
  -7.250  -0.4071   0.06682   0.06390  -0.0330   0.7698   0.0346
  -7.000  -0.3964   0.06384   0.06082  -0.0339   0.7591   0.0351
  -6.750  -0.3846   0.06057   0.05744  -0.0350   0.7485   0.0360
  -6.500  -0.3718   0.05200   0.04833  -0.0388   0.7412   0.0393
  -6.250  -0.3668   0.04728   0.04354  -0.0384   0.7324   0.0400
  -6.000  -0.3497   0.04567   0.04185  -0.0380   0.7239   0.0404
  -5.750  -0.3313   0.04408   0.04018  -0.0377   0.7154   0.0410
  -5.500  -0.3124   0.04219   0.03817  -0.0374   0.7078   0.0419
  -5.250  -0.2902   0.03866   0.03402  -0.0362   0.7007   0.0465
  -5.000  -0.2799   0.03354   0.02872  -0.0354   0.6946   0.0477
  -4.750  -0.2580   0.03214   0.02727  -0.0351   0.6870   0.0483
  -4.500  -0.2356   0.03090   0.02592  -0.0347   0.6804   0.0491
  -4.250  -0.2126   0.02950   0.02439  -0.0343   0.6740   0.0506
  -4.000  -0.1845   0.02978   0.02412  -0.0328   0.6675   0.0552
  -3.750  -0.1741   0.01916   0.01232  -0.0291   0.6638   0.0396
  -3.500  -0.1473   0.01805   0.01107  -0.0288   0.6577   0.0391
  -3.250  -0.1208   0.01663   0.00946  -0.0285   0.6514   0.0389
  -3.000  -0.0936   0.01572   0.00836  -0.0282   0.6455   0.0389
  -2.750  -0.0657   0.01505   0.00758  -0.0281   0.6390   0.0391
  -2.500  -0.0382   0.01425   0.00665  -0.0279   0.6330   0.0396
  -2.250  -0.0108   0.01342   0.00575  -0.0278   0.6273   0.0401
  -2.000   0.0166   0.01282   0.00512  -0.0276   0.6211   0.0406
  -1.750   0.0437   0.01240   0.00466  -0.0274   0.6152   0.0413
  -1.500   0.0711   0.01206   0.00431  -0.0272   0.6091   0.0421
  -1.250   0.0984   0.01176   0.00399  -0.0271   0.6026   0.0430
  -1.000   0.1255   0.01153   0.00370  -0.0268   0.5964   0.0440
  -0.750   0.1530   0.01128   0.00345  -0.0267   0.5894   0.0452
  -0.500   0.1805   0.01113   0.00326  -0.0265   0.5829   0.0466
  -0.250   0.2073   0.01084   0.00298  -0.0263   0.5764   0.0496
   0.000   0.2349   0.01069   0.00283  -0.0262   0.5694   0.0528
   0.250   0.2622   0.01055   0.00267  -0.0260   0.5629   0.0587
   0.500   0.2893   0.01030   0.00256  -0.0258   0.5555   0.0885
   0.750   0.3152   0.01005   0.00252  -0.0255   0.5488   0.1683
   1.000   0.3400   0.00958   0.00251  -0.0252   0.5414   0.3136
   1.250   0.3595   0.00792   0.00274  -0.0231   0.5350   0.9363
   1.500   0.4044   0.00828   0.00304  -0.0262   0.5275   0.9655
   1.750   0.4664   0.00869   0.00334  -0.0333   0.5192   0.9796
   2.000   0.5370   0.00902   0.00358  -0.0425   0.5107   0.9915
   2.250   0.5992   0.00913   0.00359  -0.0499   0.5030   0.9988
   2.500   0.6321   0.00917   0.00359  -0.0512   0.4964   1.0000
   2.750   0.6583   0.00921   0.00358  -0.0510   0.4894   1.0000
   3.000   0.6844   0.00927   0.00358  -0.0508   0.4828   1.0000
   3.250   0.7105   0.00931   0.00361  -0.0506   0.4763   1.0000
   3.500   0.7366   0.00940   0.00364  -0.0504   0.4712   1.0000
   3.750   0.7627   0.00947   0.00370  -0.0502   0.4667   1.0000
   4.000   0.7888   0.00953   0.00377  -0.0500   0.4617   1.0000
   4.250   0.8146   0.00963   0.00383  -0.0498   0.4570   1.0000
   4.500   0.8405   0.00975   0.00392  -0.0496   0.4526   1.0000
   4.750   0.8663   0.00981   0.00402  -0.0493   0.4480   1.0000
   5.000   0.8919   0.00991   0.00410  -0.0491   0.4430   1.0000
   5.250   0.9172   0.01008   0.00422  -0.0488   0.4382   1.0000
   5.500   0.9426   0.01015   0.00435  -0.0484   0.4340   1.0000
   5.750   0.9677   0.01024   0.00447  -0.0481   0.4292   1.0000
   6.000   0.9924   0.01040   0.00461  -0.0476   0.4244   1.0000
   6.250   1.0170   0.01053   0.00477  -0.0472   0.4195   1.0000
   6.500   1.0417   0.01063   0.00492  -0.0467   0.4143   1.0000
   6.750   1.0660   0.01079   0.00508  -0.0462   0.4096   1.0000
   7.000   1.0901   0.01094   0.00526  -0.0457   0.4038   1.0000
   7.250   1.1140   0.01104   0.00540  -0.0451   0.3961   1.0000
   7.500   1.1374   0.01118   0.00556  -0.0445   0.3866   1.0000
   7.750   1.1600   0.01136   0.00570  -0.0437   0.3748   1.0000
   8.000   1.1833   0.01148   0.00587  -0.0430   0.3633   1.0000
   8.250   1.2061   0.01165   0.00607  -0.0423   0.3516   1.0000
   8.500   1.2282   0.01187   0.00629  -0.0415   0.3378   1.0000
   8.750   1.2491   0.01216   0.00655  -0.0405   0.3193   1.0000
   9.000   1.2682   0.01258   0.00689  -0.0393   0.2958   1.0000
   9.250   1.2843   0.01319   0.00736  -0.0376   0.2662   1.0000
   9.500   1.2978   0.01394   0.00796  -0.0355   0.2366   1.0000
   9.750   1.3088   0.01479   0.00866  -0.0331   0.2064   1.0000
  10.000   1.3132   0.01596   0.00958  -0.0298   0.1606   1.0000
  10.250   1.3071   0.01755   0.01084  -0.0250   0.1148   1.0000
  10.500   1.2995   0.01891   0.01203  -0.0198   0.0832   1.0000
  10.750   1.2825   0.02063   0.01356  -0.0138   0.0546   1.0000
  11.000   1.2761   0.02253   0.01539  -0.0106   0.0408   1.0000
  11.250   1.2770   0.02431   0.01717  -0.0086   0.0347   1.0000
  11.500   1.2817   0.02598   0.01890  -0.0073   0.0314   1.0000
  11.750   1.2840   0.02799   0.02095  -0.0062   0.0291   1.0000
  12.000   1.2864   0.03012   0.02316  -0.0053   0.0275   1.0000
  12.250   1.2912   0.03210   0.02523  -0.0047   0.0263   1.0000
  12.500   1.2940   0.03435   0.02755  -0.0041   0.0252   1.0000
  12.750   1.2932   0.03700   0.03026  -0.0036   0.0242   1.0000
  13.000   1.2858   0.04040   0.03374  -0.0032   0.0233   1.0000
  13.250   1.2890   0.04273   0.03617  -0.0029   0.0227   1.0000
  13.500   1.2896   0.04537   0.03889  -0.0027   0.0221   1.0000
  13.750   1.2887   0.04819   0.04180  -0.0025   0.0215   1.0000
  14.000   1.2870   0.05115   0.04484  -0.0024   0.0210   1.0000
  14.250   1.2848   0.05428   0.04804  -0.0024   0.0205   1.0000
  14.500   1.2815   0.05759   0.05142  -0.0026   0.0201   1.0000
  14.750   1.2761   0.06120   0.05509  -0.0028   0.0197   1.0000
  15.000   1.2684   0.06511   0.05906  -0.0030   0.0193   1.0000
  15.250   1.2650   0.06853   0.06255  -0.0033   0.0190   1.0000
  15.500   1.2660   0.07152   0.06564  -0.0036   0.0187   1.0000
  15.750   1.2667   0.07455   0.06875  -0.0039   0.0184   1.0000
  16.000   1.2674   0.07761   0.07190  -0.0043   0.0180   1.0000
  16.250   1.2680   0.08070   0.07506  -0.0048   0.0176   1.0000
  16.500   1.2687   0.08376   0.07817  -0.0052   0.0173   1.0000
  16.750   1.2694   0.08688   0.08135  -0.0058   0.0169   1.0000
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