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NACA M25 AIRFOIL (m25-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M25 AIRFOIL (m25-il)
Reynolds number: 100,000
Max Cl/Cd: 54.32 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m25-il-100000-n5.txt
Download as CSV file: xf-m25-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.2458   0.10305   0.09823  -0.0027   0.6572   0.0213
  -6.750  -0.2356   0.09862   0.09376  -0.0033   0.6524   0.0216
  -6.500  -0.2238   0.09510   0.09020  -0.0048   0.6484   0.0219
  -6.250  -0.2105   0.09190   0.08693  -0.0068   0.6449   0.0224
  -6.000  -0.1945   0.08875   0.08377  -0.0095   0.6399   0.0228
  -5.750  -0.1775   0.08569   0.08067  -0.0121   0.6355   0.0234
  -5.500  -0.1595   0.08273   0.07761  -0.0148   0.6319   0.0243
  -5.250  -0.1384   0.07986   0.07469  -0.0179   0.6276   0.0259
  -5.000  -0.1112   0.07758   0.07233  -0.0222   0.6229   0.0276
  -4.750  -0.0792   0.07594   0.07054  -0.0272   0.6190   0.0282
  -4.500  -0.0481   0.07408   0.06848  -0.0314   0.6156   0.0285
  -4.250  -0.0164   0.07190   0.06616  -0.0355   0.6106   0.0286
  -4.000   0.0135   0.06943   0.06353  -0.0385   0.6065   0.0287
  -3.750   0.0245   0.06375   0.05787  -0.0384   0.6034   0.0292
  -3.500   0.0366   0.05950   0.05359  -0.0382   0.6000   0.0308
  -3.250   0.0621   0.05682   0.05083  -0.0403   0.5953   0.0331
  -3.000   0.0913   0.05442   0.04827  -0.0425   0.5913   0.0354
  -2.750   0.1384   0.05442   0.04787  -0.0464   0.5879   0.0386
  -2.500   0.1617   0.05068   0.04406  -0.0477   0.5840   0.0397
  -2.250   0.1791   0.04737   0.04074  -0.0481   0.5797   0.0431
  -2.000   0.2093   0.04553   0.03870  -0.0495   0.5759   0.0477
  -1.750   0.2529   0.04536   0.03809  -0.0516   0.5728   0.0511
  -1.500   0.2686   0.04158   0.03435  -0.0519   0.5686   0.0541
  -1.250   0.3135   0.04291   0.03522  -0.0536   0.5641   0.0630
  -1.000   0.3305   0.03868   0.03102  -0.0539   0.5608   0.0648
  -0.750   0.3553   0.03676   0.02892  -0.0541   0.5579   0.0686
  -0.500   0.3959   0.03755   0.02931  -0.0552   0.5531   0.0757
  -0.250   0.4145   0.03421   0.02604  -0.0557   0.5491   0.0803
   0.000   0.4513   0.03489   0.02628  -0.0559   0.5456   0.0888
   0.250   0.4737   0.03211   0.02343  -0.0562   0.5429   0.0909
   0.500   0.5010   0.03092   0.02217  -0.0568   0.5381   0.0946
   0.750   0.5342   0.03106   0.02199  -0.0570   0.5339   0.1029
   1.000   0.5595   0.02927   0.02011  -0.0572   0.5307   0.1051
   1.250   0.5870   0.02826   0.01891  -0.0572   0.5281   0.1078
   1.500   0.6155   0.02773   0.01832  -0.0578   0.5231   0.1203
   1.750   0.6413   0.02705   0.01759  -0.0581   0.5190   0.1511
   2.000   0.6789   0.02565   0.01557  -0.0571   0.5161   0.0607
   2.250   0.7069   0.02491   0.01464  -0.0569   0.5136   0.0584
   2.500   0.7356   0.02449   0.01416  -0.0573   0.5088   0.0563
   2.750   0.7643   0.02399   0.01353  -0.0575   0.5047   0.0544
   3.000   0.7929   0.02347   0.01281  -0.0575   0.5015   0.0529
   3.250   0.8231   0.02301   0.01217  -0.0577   0.4989   0.0522
   3.500   0.8534   0.02298   0.01217  -0.0587   0.4939   0.0521
   3.750   0.8805   0.02283   0.01198  -0.0587   0.4901   0.0525
   4.000   0.9057   0.02267   0.01173  -0.0583   0.4870   0.0536
   4.250   0.9307   0.02253   0.01146  -0.0578   0.4844   0.0553
   4.500   0.9554   0.02286   0.01189  -0.0579   0.4794   0.0588
   4.750   0.9807   0.02308   0.01215  -0.0579   0.4754   0.0693
   5.000   1.0063   0.02318   0.01223  -0.0577   0.4725   0.0798
   5.250   1.0322   0.02323   0.01225  -0.0574   0.4701   0.1021
   5.750   1.1131   0.02322   0.01374  -0.0646   0.4606   1.0000
   6.000   1.1376   0.02348   0.01400  -0.0642   0.4576   1.0000
   6.250   1.1625   0.02367   0.01421  -0.0638   0.4553   1.0000
   6.500   1.1841   0.02459   0.01536  -0.0639   0.4504   1.0000
   6.750   1.2096   0.02402   0.01475  -0.0630   0.4416   1.0000
   7.000   1.2316   0.02337   0.01416  -0.0622   0.4183   1.0000
   7.250   1.2539   0.02340   0.01432  -0.0616   0.4035   1.0000
   7.500   1.2726   0.02343   0.01425  -0.0608   0.3662   1.0000
   7.750   1.2871   0.02432   0.01500  -0.0600   0.3220   1.0000
   8.000   1.2770   0.02756   0.01747  -0.0584   0.2127   1.0000
   8.250   1.2535   0.03202   0.02154  -0.0568   0.1491   1.0000
   8.500   1.2308   0.03640   0.02575  -0.0553   0.1032   1.0000
   8.750   1.2094   0.04116   0.03036  -0.0543   0.0595   1.0000
   9.000   1.1938   0.04556   0.03469  -0.0537   0.0387   1.0000
   9.250   1.1857   0.04927   0.03845  -0.0532   0.0329   1.0000
   9.500   1.1791   0.05287   0.04217  -0.0528   0.0299   1.0000
   9.750   1.1728   0.05651   0.04596  -0.0525   0.0281   1.0000
  10.000   1.1669   0.06016   0.04975  -0.0522   0.0269   1.0000
  10.250   1.1631   0.06362   0.05339  -0.0520   0.0262   1.0000
  10.500   1.1589   0.06723   0.05716  -0.0518   0.0255   1.0000
  10.750   1.1546   0.07097   0.06108  -0.0518   0.0246   1.0000
  11.000   1.1500   0.07484   0.06515  -0.0519   0.0235   1.0000
  11.250   1.1450   0.07880   0.06927  -0.0521   0.0223   1.0000
  11.500   1.1399   0.08285   0.07346  -0.0523   0.0213   1.0000
  11.750   1.1350   0.08689   0.07764  -0.0526   0.0206   1.0000
  12.000   1.1309   0.09083   0.08170  -0.0528   0.0201   1.0000
  12.250   1.1279   0.09454   0.08553  -0.0529   0.0197   1.0000
  12.500   1.1272   0.09771   0.08879  -0.0528   0.0192   1.0000
  12.750   1.1341   0.09898   0.09008  -0.0514   0.0186   1.0000
  13.000   1.1691   0.09409   0.08503  -0.0458   0.0170   1.0000
  13.250   1.1889   0.09365   0.08466  -0.0436   0.0159   1.0000
  13.500   1.2189   0.09144   0.08253  -0.0393   0.0153   1.0000
  13.750   1.2469   0.09037   0.08155  -0.0356   0.0150   1.0000
  14.000   1.2719   0.09044   0.08178  -0.0326   0.0149   1.0000
  14.250   1.2903   0.09181   0.08336  -0.0305   0.0147   1.0000
  14.500   1.2988   0.09438   0.08617  -0.0296   0.0143   1.0000
  14.750   1.3024   0.09751   0.08954  -0.0293   0.0138   1.0000
  15.000   1.3034   0.10099   0.09325  -0.0293   0.0134   1.0000
  15.250   1.3021   0.10481   0.09730  -0.0297   0.0131   1.0000
  15.500   1.2986   0.10898   0.10171  -0.0303   0.0129   1.0000
  15.750   1.2931   0.11352   0.10656  -0.0312   0.0130   1.0000
  16.000   1.2856   0.11843   0.11171  -0.0326   0.0131   1.0000
  16.250   1.2767   0.12365   0.11718  -0.0344   0.0133   1.0000
  16.500   1.2666   0.12921   0.12297  -0.0366   0.0134   1.0000
  16.750   1.2556   0.13509   0.12907  -0.0393   0.0135   1.0000
  17.000   1.2439   0.14130   0.13548  -0.0424   0.0137   1.0000
  17.250   1.2318   0.14784   0.14222  -0.0459   0.0138   1.0000
  17.500   1.2195   0.15476   0.14933  -0.0498   0.0140   1.0000
  17.750   1.2072   0.16206   0.15681  -0.0542   0.0141   1.0000
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