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NACA M25 AIRFOIL (m25-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NACA M25 AIRFOIL (m25-il)
Reynolds number: 500,000
Max Cl/Cd: 94.51 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m25-il-500000-n5.txt
Download as CSV file: xf-m25-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M25 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3242   0.10983   0.10648   0.0194   0.5697   0.0076
  -7.750  -0.3161   0.10683   0.10349   0.0175   0.5663   0.0076
  -7.500  -0.3084   0.10388   0.10053   0.0154   0.5628   0.0077
  -7.250  -0.2989   0.10087   0.09751   0.0129   0.5595   0.0077
  -7.000  -0.2863   0.09763   0.09424   0.0100   0.5565   0.0077
  -6.750  -0.2723   0.09432   0.09092   0.0070   0.5533   0.0077
  -6.500  -0.2569   0.09095   0.08752   0.0039   0.5501   0.0077
  -6.250  -0.2402   0.08754   0.08408   0.0007   0.5470   0.0077
  -6.000  -0.2224   0.08410   0.08059  -0.0025   0.5439   0.0077
  -5.750  -0.2035   0.08060   0.07705  -0.0056   0.5410   0.0077
  -5.500  -0.1849   0.07707   0.07350  -0.0084   0.5377   0.0076
  -5.250  -0.1670   0.07397   0.07036  -0.0107   0.5344   0.0073
  -5.000  -0.1441   0.07061   0.06694  -0.0140   0.5314   0.0071
  -4.500  -0.0881   0.06491   0.06111  -0.0212   0.5254   0.0108
  -4.250  -0.0683   0.06168   0.05782  -0.0231   0.5221   0.0102
  -4.000  -0.0412   0.05821   0.05428  -0.0262   0.5190   0.0088
  -3.750  -0.0117   0.05460   0.05056  -0.0293   0.5161   0.0084
  -3.500   0.0172   0.05161   0.04746  -0.0319   0.5133   0.0086
  -3.250   0.0466   0.04880   0.04457  -0.0342   0.5103   0.0090
  -3.000   0.0777   0.04578   0.04144  -0.0365   0.5071   0.0103
  -2.750   0.1115   0.04211   0.03762  -0.0390   0.5042   0.0111
  -2.500   0.1381   0.04057   0.03598  -0.0401   0.5011   0.0116
  -2.250   0.1672   0.03860   0.03389  -0.0415   0.4981   0.0123
  -2.000   0.1988   0.03625   0.03142  -0.0428   0.4951   0.0143
  -1.750   0.2327   0.03335   0.02833  -0.0441   0.4921   0.0155
  -1.500   0.2589   0.03225   0.02716  -0.0448   0.4889   0.0163
  -1.250   0.2876   0.03089   0.02567  -0.0456   0.4858   0.0178
  -1.000   0.3191   0.02907   0.02370  -0.0462   0.4829   0.0195
  -0.750   0.3545   0.02685   0.02124  -0.0467   0.4800   0.0215
  -0.500   0.3783   0.02605   0.02042  -0.0473   0.4767   0.0228
  -0.250   0.4107   0.02596   0.02021  -0.0476   0.4736   0.0281
   0.250   0.4699   0.02307   0.01700  -0.0481   0.4678   0.0284
   0.500   0.4991   0.02178   0.01558  -0.0482   0.4645   0.0284
   0.750   0.5285   0.02077   0.01443  -0.0483   0.4613   0.0286
   1.000   0.5572   0.01956   0.01307  -0.0485   0.4583   0.0286
   1.250   0.5846   0.01781   0.01113  -0.0488   0.4556   0.0271
   1.500   0.6138   0.01663   0.00980  -0.0487   0.4527   0.0267
   1.750   0.6431   0.01553   0.00853  -0.0487   0.4495   0.0273
   2.000   0.6720   0.01485   0.00770  -0.0487   0.4460   0.0283
   2.500   0.7284   0.01340   0.00597  -0.0490   0.4399   0.0312
   2.750   0.7564   0.01314   0.00571  -0.0493   0.4369   0.0328
   3.000   0.7849   0.01247   0.00486  -0.0492   0.4337   0.0301
   3.250   0.8130   0.01232   0.00466  -0.0494   0.4303   0.0294
   3.500   0.8408   0.01225   0.00455  -0.0496   0.4268   0.0290
   3.750   0.8684   0.01197   0.00427  -0.0498   0.4236   0.0285
   4.000   0.8956   0.01171   0.00400  -0.0498   0.4202   0.0283
   4.250   0.9227   0.01155   0.00384  -0.0499   0.4168   0.0282
   4.500   0.9498   0.01147   0.00376  -0.0500   0.4136   0.0282
   4.750   0.9770   0.01143   0.00373  -0.0502   0.4106   0.0283
   5.000   1.0045   0.01140   0.00375  -0.0504   0.4074   0.0286
   5.250   1.0318   0.01139   0.00377  -0.0506   0.4036   0.0293
   5.500   1.0590   0.01144   0.00381  -0.0508   0.3949   0.0320
   5.750   1.0862   0.01158   0.00391  -0.0512   0.3801   0.0347
   6.000   1.1133   0.01178   0.00408  -0.0515   0.3651   0.0368
   6.250   1.1394   0.01217   0.00437  -0.0519   0.3376   0.0451
   6.500   1.1638   0.01294   0.00494  -0.0524   0.2895   0.0759
   7.000   1.2095   0.01734   0.00946  -0.0577   0.0167   0.9953
   7.250   1.2456   0.01807   0.01028  -0.0607   0.0132   1.0000
   7.500   1.2643   0.01889   0.01119  -0.0601   0.0108   1.0000
   7.750   1.2806   0.01989   0.01231  -0.0594   0.0097   1.0000
   8.000   1.2966   0.02079   0.01329  -0.0586   0.0090   1.0000
   8.250   1.3105   0.02182   0.01438  -0.0578   0.0080   1.0000
   8.500   1.3209   0.02329   0.01592  -0.0575   0.0073   1.0000
   8.750   1.3214   0.02527   0.01800  -0.0563   0.0070   1.0000
   9.000   1.3203   0.02770   0.02053  -0.0553   0.0066   1.0000
   9.250   1.3139   0.03099   0.02394  -0.0546   0.0063   1.0000
   9.500   1.3122   0.03387   0.02692  -0.0542   0.0062   1.0000
   9.750   1.3107   0.03675   0.02990  -0.0537   0.0060   1.0000
  10.000   1.3071   0.03990   0.03315  -0.0533   0.0059   1.0000
  10.250   1.3023   0.04318   0.03653  -0.0528   0.0057   1.0000
  10.500   1.2969   0.04655   0.03999  -0.0524   0.0056   1.0000
  10.750   1.2924   0.04980   0.04334  -0.0519   0.0054   1.0000
  11.000   1.2893   0.05295   0.04656  -0.0516   0.0051   1.0000
  11.250   1.2886   0.05592   0.04960  -0.0513   0.0049   1.0000
  11.500   1.2895   0.05877   0.05251  -0.0512   0.0046   1.0000
  11.750   1.2908   0.06159   0.05538  -0.0511   0.0044   1.0000
  12.000   1.2896   0.06472   0.05859  -0.0510   0.0042   1.0000
  12.250   1.2869   0.06801   0.06194  -0.0508   0.0041   1.0000
  12.500   1.2822   0.07136   0.06534  -0.0503   0.0040   1.0000
  12.750   1.2842   0.07391   0.06796  -0.0497   0.0039   1.0000
  13.000   1.2879   0.07615   0.07028  -0.0490   0.0038   1.0000
  13.250   1.2935   0.07791   0.07210  -0.0478   0.0036   1.0000
  13.500   1.3024   0.07892   0.07319  -0.0458   0.0034   1.0000
  13.750   1.3162   0.07901   0.07334  -0.0429   0.0032   1.0000
  14.000   1.3326   0.07887   0.07330  -0.0396   0.0031   1.0000
  14.250   1.3493   0.07911   0.07366  -0.0363   0.0030   1.0000
  14.500   1.3572   0.08103   0.07574  -0.0351   0.0029   1.0000
  14.750   1.3601   0.08374   0.07855  -0.0350   0.0028   1.0000
  15.000   1.3613   0.08672   0.08165  -0.0353   0.0027   1.0000
  15.250   1.3606   0.09002   0.08506  -0.0358   0.0026   1.0000
  15.500   1.3591   0.09349   0.08865  -0.0364   0.0025   1.0000
  15.750   1.3556   0.09728   0.09257  -0.0372   0.0024   1.0000
  16.000   1.3495   0.10155   0.09699  -0.0379   0.0024   1.0000
  16.250   1.3442   0.10589   0.10154  -0.0377   0.0023   1.0000
  16.500   1.3377   0.11062   0.10648  -0.0381   0.0023   1.0000
  16.750   1.3286   0.11586   0.11192  -0.0392   0.0023   1.0000
  17.000   1.3184   0.12146   0.11772  -0.0407   0.0022   1.0000
  17.250   1.3069   0.12743   0.12387  -0.0427   0.0022   1.0000
  17.500   1.2943   0.13381   0.13043  -0.0453   0.0022   1.0000
  17.750   1.2814   0.14047   0.13726  -0.0484   0.0022   1.0000
  18.000   1.2683   0.14736   0.14431  -0.0518   0.0022   1.0000
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