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NACA M25 AIRFOIL (m25-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA M25 AIRFOIL (m25-il)
Reynolds number: 200,000
Max Cl/Cd: 78.46 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m25-il-200000-n5.txt
Download as CSV file: xf-m25-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3955   0.14486   0.14097   0.0320   0.6703   0.0111
 -10.500  -0.3887   0.14139   0.13748   0.0310   0.6652   0.0113
 -10.250  -0.3815   0.13823   0.13428   0.0298   0.6608   0.0115
 -10.000  -0.3740   0.13513   0.13118   0.0285   0.6562   0.0117
  -9.750  -0.3664   0.13208   0.12811   0.0272   0.6515   0.0120
  -9.500  -0.3587   0.12905   0.12505   0.0258   0.6474   0.0122
  -9.250  -0.3510   0.12604   0.12202   0.0244   0.6432   0.0125
  -9.000  -0.3431   0.12302   0.11900   0.0229   0.6385   0.0128
  -8.750  -0.3352   0.12003   0.11598   0.0214   0.6343   0.0132
  -8.250  -0.3188   0.11409   0.11001   0.0183   0.6263   0.0139
  -8.000  -0.3101   0.11118   0.10710   0.0165   0.6222   0.0143
  -7.750  -0.3012   0.10838   0.10428   0.0145   0.6185   0.0145
  -7.500  -0.2922   0.10572   0.10160   0.0122   0.6150   0.0147
  -7.250  -0.2829   0.10321   0.09909   0.0096   0.6108   0.0148
  -7.000  -0.2694   0.10049   0.09634   0.0062   0.6068   0.0149
  -6.750  -0.2543   0.09772   0.09350   0.0027   0.6033   0.0150
  -6.500  -0.2362   0.09517   0.09090  -0.0016   0.5998   0.0151
  -6.250  -0.2144   0.09282   0.08852  -0.0068   0.5958   0.0151
  -6.000  -0.2066   0.08736   0.08306  -0.0063   0.5923   0.0154
  -5.750  -0.1944   0.08345   0.07911  -0.0073   0.5889   0.0157
  -5.500  -0.1771   0.08020   0.07580  -0.0096   0.5856   0.0161
  -5.250  -0.1573   0.07707   0.07263  -0.0124   0.5815   0.0165
  -5.000  -0.1357   0.07400   0.06951  -0.0154   0.5777   0.0171
  -4.750  -0.1127   0.07098   0.06641  -0.0183   0.5745   0.0178
  -4.500  -0.0876   0.06805   0.06337  -0.0214   0.5714   0.0190
  -4.250  -0.0569   0.06543   0.06066  -0.0252   0.5674   0.0201
  -4.000  -0.0234   0.06305   0.05816  -0.0292   0.5635   0.0205
  -3.750   0.0140   0.06111   0.05602  -0.0335   0.5601   0.0207
  -3.500   0.0437   0.05826   0.05301  -0.0360   0.5573   0.0208
  -3.250   0.0738   0.05534   0.04998  -0.0384   0.5535   0.0208
  -3.000   0.1037   0.05245   0.04696  -0.0404   0.5498   0.0209
  -2.500   0.1377   0.04559   0.03999  -0.0413   0.5436   0.0246
  -2.250   0.1769   0.04443   0.03863  -0.0436   0.5400   0.0280
  -2.000   0.2131   0.04276   0.03675  -0.0453   0.5363   0.0284
  -1.750   0.2470   0.04102   0.03479  -0.0465   0.5328   0.0287
  -1.500   0.2741   0.03779   0.03138  -0.0474   0.5299   0.0291
  -1.250   0.2943   0.03489   0.02839  -0.0479   0.5269   0.0302
  -1.000   0.3207   0.03315   0.02657  -0.0486   0.5231   0.0321
  -0.750   0.3604   0.03332   0.02644  -0.0493   0.5193   0.0387
  -0.500   0.3912   0.03200   0.02488  -0.0496   0.5161   0.0389
   0.000   0.4396   0.02751   0.02022  -0.0507   0.5097   0.0428
   0.250   0.4769   0.02814   0.02052  -0.0507   0.5059   0.0507
   0.500   0.4999   0.02547   0.01782  -0.0514   0.5026   0.0526
   0.750   0.5267   0.02441   0.01662  -0.0516   0.4997   0.0549
   1.000   0.5556   0.02359   0.01568  -0.0519   0.4963   0.0586
   1.250   0.5882   0.02313   0.01494  -0.0518   0.4927   0.0637
   1.500   0.6147   0.02188   0.01365  -0.0522   0.4893   0.0653
   1.750   0.6432   0.02103   0.01262  -0.0523   0.4862   0.0659
   2.000   0.6738   0.01952   0.01081  -0.0519   0.4833   0.0444
   2.250   0.7027   0.01895   0.01014  -0.0520   0.4795   0.0475
   2.500   0.7314   0.01818   0.00924  -0.0521   0.4760   0.0445
   2.750   0.7605   0.01733   0.00815  -0.0520   0.4730   0.0410
   3.000   0.7886   0.01697   0.00763  -0.0519   0.4702   0.0395
   3.250   0.8164   0.01676   0.00739  -0.0521   0.4665   0.0389
   3.500   0.8439   0.01636   0.00698  -0.0522   0.4626   0.0385
   3.750   0.8708   0.01606   0.00666  -0.0522   0.4592   0.0383
   4.000   0.8975   0.01586   0.00641  -0.0521   0.4564   0.0383
   4.250   0.9242   0.01574   0.00631  -0.0522   0.4533   0.0384
   4.500   0.9507   0.01568   0.00632  -0.0522   0.4495   0.0388
   4.750   0.9770   0.01561   0.00626  -0.0521   0.4459   0.0399
   5.000   1.0039   0.01564   0.00624  -0.0522   0.4427   0.0425
   5.250   1.0311   0.01575   0.00633  -0.0524   0.4396   0.0466
   5.750   1.0852   0.01601   0.00692  -0.0528   0.4321   0.1353
   6.750   1.2216   0.01557   0.00767  -0.0607   0.3662   1.0000
   7.000   1.2421   0.01645   0.00824  -0.0607   0.3088   1.0000
   7.250   1.2310   0.02157   0.01202  -0.0599   0.0901   1.0000
   7.500   1.2324   0.02409   0.01436  -0.0585   0.0252   1.0000
   7.750   1.2433   0.02545   0.01585  -0.0576   0.0214   1.0000
   8.000   1.2483   0.02732   0.01788  -0.0569   0.0193   1.0000
   8.250   1.2450   0.02963   0.02037  -0.0553   0.0177   1.0000
   8.500   1.2488   0.03161   0.02247  -0.0544   0.0167   1.0000
   8.750   1.2506   0.03393   0.02494  -0.0537   0.0156   1.0000
   9.000   1.2499   0.03661   0.02777  -0.0531   0.0150   1.0000
   9.250   1.2474   0.03956   0.03086  -0.0526   0.0144   1.0000
   9.500   1.2433   0.04273   0.03418  -0.0521   0.0140   1.0000
   9.750   1.2378   0.04612   0.03770  -0.0517   0.0136   1.0000
  10.000   1.2314   0.04963   0.04137  -0.0513   0.0133   1.0000
  10.250   1.2247   0.05322   0.04507  -0.0510   0.0128   1.0000
  10.500   1.2181   0.05683   0.04877  -0.0507   0.0123   1.0000
  10.750   1.2118   0.06054   0.05256  -0.0505   0.0117   1.0000
  11.000   1.2048   0.06437   0.05646  -0.0504   0.0111   1.0000
  11.250   1.1976   0.06817   0.06031  -0.0501   0.0106   1.0000
  11.500   1.1927   0.07143   0.06359  -0.0493   0.0103   1.0000
  11.750   1.1942   0.07346   0.06559  -0.0477   0.0100   1.0000
  12.000   1.2021   0.07511   0.06729  -0.0466   0.0097   1.0000
  12.250   1.2122   0.07631   0.06852  -0.0452   0.0095   1.0000
  12.500   1.2255   0.07692   0.06916  -0.0431   0.0093   1.0000
  12.750   1.2397   0.07756   0.06990  -0.0412   0.0090   1.0000
  13.000   1.2512   0.07890   0.07134  -0.0400   0.0083   1.0000
  13.250   1.2613   0.08045   0.07297  -0.0391   0.0076   1.0000
  13.500   1.2737   0.08160   0.07419  -0.0377   0.0072   1.0000
  13.750   1.2885   0.08248   0.07515  -0.0357   0.0070   1.0000
  14.000   1.3033   0.08358   0.07634  -0.0338   0.0068   1.0000
  14.250   1.3162   0.08519   0.07809  -0.0321   0.0067   1.0000
  14.500   1.3267   0.08735   0.08041  -0.0307   0.0066   1.0000
  14.750   1.3335   0.09012   0.08337  -0.0298   0.0066   1.0000
  15.000   1.3360   0.09343   0.08694  -0.0293   0.0066   1.0000
  15.250   1.3337   0.09734   0.09109  -0.0293   0.0067   1.0000
  15.500   1.3257   0.10211   0.09615  -0.0300   0.0069   1.0000
  15.750   1.3163   0.10724   0.10157  -0.0309   0.0070   1.0000
  16.000   1.3055   0.11265   0.10724  -0.0322   0.0072   1.0000
  16.250   1.2938   0.11829   0.11312  -0.0340   0.0074   1.0000
  16.500   1.2816   0.12418   0.11924  -0.0361   0.0076   1.0000
  16.750   1.2692   0.13030   0.12555  -0.0386   0.0078   1.0000
  17.000   1.2564   0.13664   0.13209  -0.0416   0.0079   1.0000
  17.250   1.2435   0.14323   0.13886  -0.0449   0.0080   1.0000
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