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MH 92 15.49% (mh92-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 92 15.49% (mh92-il)
Reynolds number: 50,000
Max Cl/Cd: 24.85 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh92-il-50000-n5.txt
Download as CSV file: xf-mh92-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 92  15.49%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6227   0.10119   0.09420  -0.0076   1.0000   0.0441
 -12.000  -0.6490   0.09156   0.08449  -0.0142   1.0000   0.0432
 -11.750  -0.6822   0.08262   0.07539  -0.0203   1.0000   0.0424
 -11.500  -0.7111   0.07585   0.06840  -0.0240   1.0000   0.0419
 -11.250  -0.7358   0.07044   0.06276  -0.0257   1.0000   0.0416
 -11.000  -0.7545   0.06615   0.05823  -0.0260   1.0000   0.0414
 -10.750  -0.7677   0.06256   0.05442  -0.0253   1.0000   0.0416
 -10.500  -0.7773   0.05931   0.05094  -0.0239   1.0000   0.0418
 -10.250  -0.7828   0.05635   0.04773  -0.0221   1.0000   0.0421
 -10.000  -0.7840   0.05356   0.04468  -0.0202   1.0000   0.0424
  -9.750  -0.7794   0.05081   0.04165  -0.0186   1.0000   0.0430
  -9.500  -0.7699   0.04815   0.03870  -0.0173   1.0000   0.0436
  -9.250  -0.7568   0.04561   0.03582  -0.0161   1.0000   0.0447
  -9.000  -0.7398   0.04336   0.03334  -0.0153   1.0000   0.0464
  -8.750  -0.7201   0.04158   0.03154  -0.0148   1.0000   0.0487
  -8.500  -0.6976   0.03967   0.02942  -0.0143   1.0000   0.0516
  -8.250  -0.6716   0.03788   0.02757  -0.0141   1.0000   0.0540
  -8.000  -0.6472   0.03631   0.02598  -0.0138   1.0000   0.0576
  -7.750  -0.6244   0.03484   0.02448  -0.0133   1.0000   0.0624
  -7.500  -0.6035   0.03351   0.02309  -0.0125   1.0000   0.0682
  -7.250  -0.5864   0.03220   0.02186  -0.0115   1.0000   0.0745
  -7.000  -0.5721   0.03091   0.02063  -0.0101   1.0000   0.0837
  -6.750  -0.5614   0.02973   0.01956  -0.0082   1.0000   0.0950
  -6.500  -0.5574   0.02866   0.01866  -0.0054   1.0000   0.1099
  -6.250  -0.5541   0.02752   0.01780  -0.0028   0.9911   0.1345
  -6.000  -0.5300   0.02530   0.01640  -0.0045   0.9658   0.2322
  -5.750  -0.5060   0.02395   0.01574  -0.0052   0.9441   0.3598
  -5.500  -0.4811   0.02337   0.01556  -0.0048   0.9237   0.4508
  -5.250  -0.4559   0.02326   0.01566  -0.0035   0.9044   0.5225
  -5.000  -0.4279   0.02349   0.01598  -0.0020   0.8864   0.5780
  -4.750  -0.3976   0.02385   0.01629  -0.0007   0.8692   0.6172
  -4.500  -0.3693   0.02416   0.01645   0.0006   0.8522   0.6465
  -4.250  -0.3385   0.02455   0.01667   0.0017   0.8358   0.6701
  -4.000  -0.3115   0.02484   0.01677   0.0032   0.8196   0.6920
  -3.750  -0.2864   0.02507   0.01681   0.0048   0.8039   0.7125
  -3.500  -0.2599   0.02531   0.01685   0.0063   0.7889   0.7309
  -3.250  -0.2299   0.02559   0.01693   0.0071   0.7738   0.7465
  -3.000  -0.1991   0.02584   0.01700   0.0077   0.7582   0.7609
  -2.750  -0.1696   0.02603   0.01701   0.0083   0.7430   0.7752
  -2.500  -0.1419   0.02615   0.01694   0.0091   0.7284   0.7896
  -2.250  -0.1158   0.02622   0.01683   0.0101   0.7147   0.8045
  -2.000  -0.0898   0.02627   0.01670   0.0110   0.7010   0.8190
  -1.750  -0.0520   0.02642   0.01669   0.0100   0.6857   0.8291
  -1.250   0.0031   0.02646   0.01642   0.0108   0.6583   0.8561
  -1.000   0.0436   0.02645   0.01622   0.0091   0.6448   0.8653
  -0.750   0.0745   0.02646   0.01611   0.0086   0.6301   0.8774
  -0.500   0.1052   0.02646   0.01600   0.0081   0.6162   0.8895
  -0.250   0.1430   0.02639   0.01579   0.0065   0.6027   0.8987
   0.000   0.1714   0.02633   0.01558   0.0064   0.5908   0.9103
   0.250   0.2090   0.02628   0.01545   0.0044   0.5762   0.9193
   0.500   0.2411   0.02626   0.01533   0.0034   0.5631   0.9291
   0.750   0.2747   0.02618   0.01512   0.0022   0.5511   0.9385
   1.000   0.3095   0.02611   0.01496   0.0006   0.5384   0.9469
   1.250   0.3404   0.02616   0.01496  -0.0005   0.5256   0.9564
   1.500   0.3777   0.02606   0.01478  -0.0026   0.5134   0.9638
   1.750   0.4106   0.02602   0.01464  -0.0039   0.5023   0.9720
   2.000   0.4461   0.02605   0.01466  -0.0060   0.4895   0.9797
   2.250   0.4810   0.02603   0.01457  -0.0078   0.4783   0.9869
   2.500   0.5157   0.02602   0.01450  -0.0096   0.4675   0.9942
   2.750   0.5486   0.02615   0.01464  -0.0114   0.4559   1.0000
   3.000   0.5679   0.02624   0.01462  -0.0102   0.4482   1.0000
   3.250   0.5869   0.02663   0.01510  -0.0095   0.4379   1.0000
   3.500   0.6063   0.02676   0.01512  -0.0082   0.4308   1.0000
   3.750   0.6245   0.02725   0.01569  -0.0074   0.4208   1.0000
   4.000   0.6436   0.02743   0.01578  -0.0061   0.4138   1.0000
   4.250   0.6609   0.02801   0.01648  -0.0052   0.4047   1.0000
   4.500   0.6795   0.02827   0.01669  -0.0038   0.3977   1.0000
   4.750   0.6960   0.02887   0.01737  -0.0027   0.3895   1.0000
   5.000   0.7135   0.02928   0.01779  -0.0013   0.3823   1.0000
   5.250   0.7304   0.02979   0.01831   0.0000   0.3756   1.0000
   5.500   0.7453   0.03047   0.01908   0.0014   0.3679   1.0000
   5.750   0.7639   0.03074   0.01927   0.0029   0.3623   1.0000
   6.000   0.7752   0.03173   0.02045   0.0045   0.3546   1.0000
   6.250   0.7907   0.03228   0.02101   0.0061   0.3485   1.0000
   6.500   0.8067   0.03280   0.02152   0.0078   0.3430   1.0000
   6.750   0.8145   0.03393   0.02284   0.0098   0.3358   1.0000
   7.000   0.8305   0.03441   0.02330   0.0115   0.3304   1.0000
   7.250   0.8411   0.03532   0.02428   0.0135   0.3249   1.0000
   7.500   0.8455   0.03656   0.02568   0.0158   0.3184   1.0000
   7.750   0.8618   0.03702   0.02613   0.0175   0.3135   1.0000
   8.000   0.8679   0.03818   0.02738   0.0198   0.3081   1.0000
   8.250   0.8654   0.03984   0.02920   0.0226   0.3022   1.0000
   8.500   0.8808   0.04040   0.02975   0.0242   0.2973   1.0000
   8.750   0.8883   0.04150   0.03089   0.0263   0.2926   1.0000
   9.000   0.8667   0.04433   0.03392   0.0297   0.2866   1.0000
   9.250   0.8770   0.04528   0.03490   0.0314   0.2818   1.0000
   9.500   0.9027   0.04542   0.03500   0.0322   0.2777   1.0000
   9.750   0.7792   0.05632   0.04608   0.0355   0.2700   1.0000
  10.000   0.7895   0.05767   0.04748   0.0362   0.2653   1.0000
  10.250   0.8526   0.05399   0.04379   0.0382   0.2627   1.0000
  10.500   0.7127   0.07328   0.06312   0.0311   0.2488   1.0000
  10.750   0.7449   0.07175   0.06165   0.0331   0.2467   1.0000
  11.250   0.7014   0.08491   0.07484   0.0281   0.2316   1.0000
  11.750   0.6688   0.09684   0.08681   0.0235   0.2179   1.0000
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