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MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 25 9.98% (mh25-il)
Reynolds number: 200,000
Max Cl/Cd: 58.81 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh25-il-200000-n5.txt
Download as CSV file: xf-mh25-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 25  9.98%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4969   0.08976   0.08633  -0.0340   1.0000   0.0106
  -9.000  -0.5078   0.08594   0.08256  -0.0345   1.0000   0.0105
  -8.750  -0.5206   0.08208   0.07875  -0.0354   1.0000   0.0103
  -8.500  -0.5401   0.07785   0.07455  -0.0366   1.0000   0.0102
  -8.250  -0.5578   0.07457   0.07125  -0.0359   0.9994   0.0102
  -8.000  -0.5650   0.06986   0.06646  -0.0376   0.9956   0.0100
  -7.750  -0.5659   0.06480   0.06127  -0.0393   0.9920   0.0097
  -7.500  -0.5667   0.05982   0.05613  -0.0398   0.9879   0.0093
  -7.250  -0.5623   0.05515   0.05125  -0.0401   0.9846   0.0090
  -7.000  -0.5559   0.05001   0.04583  -0.0400   0.9817   0.0085
  -6.750  -0.5532   0.04598   0.04153  -0.0376   0.9773   0.0081
  -6.500  -0.5455   0.04112   0.03626  -0.0355   0.9736   0.0076
  -6.250  -0.5334   0.03589   0.03048  -0.0335   0.9709   0.0071
  -6.000  -0.5198   0.03208   0.02613  -0.0310   0.9679   0.0067
  -5.750  -0.5065   0.02932   0.02291  -0.0281   0.9641   0.0064
  -5.500  -0.4859   0.02708   0.02026  -0.0268   0.9614   0.0063
  -5.250  -0.4614   0.02517   0.01797  -0.0261   0.9594   0.0063
  -5.000  -0.4340   0.02360   0.01609  -0.0261   0.9578   0.0062
  -4.750  -0.4056   0.02183   0.01403  -0.0261   0.9566   0.0063
  -4.500  -0.3879   0.02060   0.01263  -0.0240   0.9526   0.0064
  -4.250  -0.3651   0.01943   0.01133  -0.0230   0.9495   0.0066
  -4.000  -0.3391   0.01848   0.01021  -0.0227   0.9471   0.0069
  -3.750  -0.3106   0.01768   0.00929  -0.0229   0.9450   0.0077
  -3.500  -0.2798   0.01707   0.00854  -0.0236   0.9434   0.0084
  -3.250  -0.2630   0.01663   0.00800  -0.0212   0.9380   0.0109
  -3.000  -0.2374   0.01603   0.00740  -0.0208   0.9346   0.0224
  -2.750  -0.2145   0.01471   0.00693  -0.0205   0.9319   0.1777
  -2.500  -0.1905   0.01358   0.00663  -0.0205   0.9298   0.3798
  -2.250  -0.1883   0.01258   0.00643  -0.0153   0.9219   0.5749
  -2.000  -0.1364   0.01248   0.00733  -0.0187   0.9239   0.8591
  -1.750  -0.1017   0.01273   0.00746  -0.0196   0.9212   0.8938
  -1.500  -0.0667   0.01291   0.00752  -0.0206   0.9188   0.9149
  -1.250  -0.0168   0.01326   0.00773  -0.0248   0.9182   0.9306
  -1.000   0.0409   0.01358   0.00794  -0.0307   0.9183   0.9435
  -0.750   0.0953   0.01363   0.00789  -0.0363   0.9177   0.9480
  -0.500   0.1253   0.01364   0.00784  -0.0367   0.9124   0.9560
  -0.250   0.1737   0.01356   0.00771  -0.0411   0.9096   0.9591
   0.000   0.2202   0.01341   0.00752  -0.0451   0.9067   0.9624
   0.250   0.2640   0.01320   0.00729  -0.0484   0.9039   0.9654
   0.500   0.2916   0.01309   0.00718  -0.0484   0.8957   0.9705
   0.750   0.3333   0.01280   0.00689  -0.0513   0.8911   0.9720
   1.000   0.3651   0.01260   0.00671  -0.0522   0.8819   0.9752
   1.250   0.3983   0.01235   0.00650  -0.0533   0.8735   0.9779
   1.500   0.4279   0.01214   0.00630  -0.0536   0.8632   0.9810
   1.750   0.4563   0.01194   0.00614  -0.0537   0.8479   0.9837
   2.000   0.4881   0.01168   0.00592  -0.0545   0.8303   0.9857
   2.250   0.5246   0.01133   0.00563  -0.0561   0.8093   0.9868
   2.500   0.5640   0.01096   0.00521  -0.0582   0.7765   0.9871
   2.750   0.6013   0.01074   0.00483  -0.0598   0.7290   0.9873
   3.000   0.6308   0.01084   0.00468  -0.0599   0.6688   0.9888
   3.250   0.6551   0.01114   0.00473  -0.0592   0.6081   0.9910
   3.500   0.6768   0.01153   0.00487  -0.0581   0.5482   0.9935
   3.750   0.6998   0.01192   0.00503  -0.0574   0.4891   0.9956
   4.000   0.7223   0.01238   0.00524  -0.0568   0.4291   0.9980
   4.250   0.7447   0.01287   0.00550  -0.0561   0.3727   1.0000
   4.500   0.7594   0.01332   0.00584  -0.0538   0.3278   1.0000
   4.750   0.7738   0.01380   0.00616  -0.0514   0.2837   1.0000
   5.000   0.7882   0.01429   0.00650  -0.0491   0.2425   1.0000
   5.250   0.8026   0.01479   0.00687  -0.0468   0.2042   1.0000
   5.500   0.8165   0.01533   0.00726  -0.0444   0.1671   1.0000
   5.750   0.8303   0.01587   0.00767  -0.0420   0.1341   1.0000
   6.250   0.8573   0.01697   0.00859  -0.0370   0.0833   1.0000
   6.500   0.8699   0.01756   0.00912  -0.0344   0.0641   1.0000
   6.750   0.8823   0.01815   0.00967  -0.0317   0.0491   1.0000
   7.000   0.8938   0.01877   0.01036  -0.0288   0.0392   1.0000
   7.250   0.9050   0.01937   0.01103  -0.0258   0.0332   1.0000
   7.500   0.9136   0.02012   0.01185  -0.0223   0.0289   1.0000
   7.750   0.9228   0.02077   0.01264  -0.0189   0.0262   1.0000
   8.000   0.9319   0.02141   0.01335  -0.0156   0.0227   1.0000
   8.250   0.9342   0.02247   0.01446  -0.0111   0.0198   1.0000
   8.500   0.9409   0.02314   0.01527  -0.0073   0.0184   1.0000
   8.750   0.9488   0.02369   0.01593  -0.0038   0.0157   1.0000
   9.000   0.9547   0.02441   0.01673  -0.0002   0.0134   1.0000
   9.250   0.9597   0.02536   0.01778   0.0035   0.0107   1.0000
   9.500   0.9668   0.02628   0.01883   0.0068   0.0093   1.0000
   9.750   0.9743   0.02722   0.01989   0.0099   0.0081   1.0000
  10.000   0.9796   0.02843   0.02121   0.0130   0.0072   1.0000
  10.250   0.9785   0.03055   0.02351   0.0170   0.0063   1.0000
  10.500   0.9834   0.03221   0.02544   0.0199   0.0061   1.0000
  10.750   0.9865   0.03417   0.02766   0.0229   0.0058   1.0000
  11.000   0.9877   0.03630   0.03005   0.0259   0.0055   1.0000
  11.250   0.9862   0.03864   0.03267   0.0289   0.0053   1.0000
  11.500   0.9816   0.04122   0.03552   0.0318   0.0052   1.0000
  11.750   0.9745   0.04399   0.03856   0.0344   0.0051   1.0000
  12.000   0.9632   0.04721   0.04206   0.0367   0.0050   1.0000
  12.250   0.9489   0.05088   0.04600   0.0384   0.0049   1.0000
  12.500   0.9351   0.05470   0.05005   0.0391   0.0049   1.0000
  12.750   0.9179   0.05933   0.05492   0.0388   0.0049   1.0000
  13.000   0.9014   0.06438   0.06017   0.0373   0.0050   1.0000
  13.250   0.8818   0.07068   0.06667   0.0343   0.0049   1.0000
  13.500   0.8639   0.07755   0.07371   0.0303   0.0051   1.0000
  13.750   0.8432   0.08605   0.08237   0.0249   0.0052   1.0000
  14.000   0.8237   0.09524   0.09168   0.0191   0.0053   1.0000
  14.250   0.8016   0.10588   0.10241   0.0129   0.0054   1.0000
  14.500   0.7779   0.11723   0.11375   0.0071   0.0057   1.0000
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