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MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 25 9.98% (mh25-il)
Reynolds number: 50,000
Max Cl/Cd: 34.43 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh25-il-50000.txt
Download as CSV file: xf-mh25-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4666   0.11289   0.10613  -0.0232   1.0000   0.2334
  -9.250  -0.4768   0.11105   0.10437  -0.0227   1.0000   0.2438
  -9.000  -0.4672   0.10716   0.10052  -0.0210   1.0000   0.2554
  -8.750  -0.4649   0.10394   0.09735  -0.0196   1.0000   0.2658
  -8.500  -0.4678   0.10101   0.09450  -0.0181   1.0000   0.2787
  -8.250  -0.4716   0.09834   0.09192  -0.0165   1.0000   0.2911
  -8.000  -0.4738   0.09556   0.08921  -0.0144   1.0000   0.3063
  -7.750  -0.4779   0.09297   0.08669  -0.0122   1.0000   0.3216
  -7.500  -0.5002   0.09144   0.08530  -0.0092   1.0000   0.3398
  -5.500  -0.6012   0.05637   0.04931  -0.0121   1.0000   0.1437
  -5.250  -0.5937   0.05147   0.04320  -0.0095   1.0000   0.1082
  -5.000  -0.5787   0.04717   0.03889  -0.0078   1.0000   0.1008
  -4.750  -0.5643   0.04366   0.03470  -0.0051   1.0000   0.0919
  -4.500  -0.5481   0.04036   0.03096  -0.0029   1.0000   0.0875
  -4.250  -0.5288   0.03742   0.02726  -0.0003   1.0000   0.0832
  -4.000  -0.5080   0.03491   0.02444   0.0014   1.0000   0.0848
  -3.750  -0.4862   0.03292   0.02201   0.0030   1.0000   0.0914
  -3.500  -0.1782   0.02388   0.01565  -0.0353   1.0000   1.0000
  -3.250  -0.1710   0.02349   0.01490  -0.0326   1.0000   1.0000
  -3.000  -0.1626   0.02320   0.01428  -0.0300   1.0000   1.0000
  -2.750  -0.1532   0.02296   0.01367  -0.0274   1.0000   1.0000
  -2.500  -0.1432   0.02278   0.01322  -0.0249   1.0000   1.0000
  -2.250  -0.1325   0.02264   0.01282  -0.0223   1.0000   1.0000
  -2.000  -0.1216   0.02254   0.01249  -0.0199   1.0000   1.0000
  -1.750  -0.1103   0.02247   0.01221  -0.0174   1.0000   1.0000
  -1.500  -0.0988   0.02244   0.01199  -0.0150   1.0000   1.0000
  -1.250  -0.0871   0.02243   0.01180  -0.0126   1.0000   1.0000
  -1.000  -0.0753   0.02245   0.01166  -0.0102   1.0000   1.0000
  -0.750  -0.0634   0.02250   0.01153  -0.0079   1.0000   1.0000
  -0.500  -0.0515   0.02258   0.01148  -0.0056   1.0000   1.0000
  -0.250  -0.0394   0.02269   0.01147  -0.0033   1.0000   1.0000
   0.000  -0.0274   0.02283   0.01151  -0.0011   1.0000   1.0000
   0.250  -0.0154   0.02300   0.01158   0.0010   1.0000   1.0000
   0.500  -0.0033   0.02320   0.01168   0.0032   1.0000   1.0000
   0.750   0.0088   0.02344   0.01185   0.0052   1.0000   1.0000
   1.000   0.0208   0.02371   0.01207   0.0072   1.0000   1.0000
   1.250   0.0328   0.02402   0.01234   0.0091   1.0000   1.0000
   1.500   0.0448   0.02438   0.01267   0.0109   1.0000   1.0000
   1.750   0.0567   0.02478   0.01305   0.0127   1.0000   1.0000
   2.000   0.0684   0.02523   0.01349   0.0143   1.0000   1.0000
   2.250   0.0799   0.02574   0.01400   0.0159   1.0000   1.0000
   2.500   0.0913   0.02631   0.01457   0.0174   1.0000   1.0000
   2.750   0.1025   0.02694   0.01522   0.0187   1.0000   1.0000
   3.000   0.1136   0.02764   0.01595   0.0199   1.0000   1.0000
   3.250   0.1244   0.02841   0.01677   0.0210   1.0000   1.0000
   3.500   0.1919   0.03051   0.01908   0.0109   0.9752   1.0000
   3.750   0.2564   0.03217   0.02095   0.0021   0.9468   1.0000
   4.000   0.3164   0.03334   0.02236  -0.0052   0.9185   1.0000
   4.250   0.3772   0.03405   0.02343  -0.0118   0.8899   1.0000
   4.500   0.4266   0.03420   0.02387  -0.0158   0.8591   1.0000
   4.750   0.4855   0.03382   0.02387  -0.0205   0.8275   1.0000
   5.000   0.5555   0.03255   0.02316  -0.0257   0.7942   1.0000
   5.250   0.6550   0.02915   0.02052  -0.0329   0.7554   1.0000
   5.500   0.7578   0.02465   0.01682  -0.0384   0.6873   1.0000
   5.750   0.8061   0.02341   0.01544  -0.0373   0.5848   1.0000
   6.000   0.8233   0.02406   0.01558  -0.0331   0.4888   1.0000
   6.250   0.8328   0.02531   0.01627  -0.0285   0.4035   1.0000
   6.500   0.8406   0.02687   0.01732  -0.0243   0.3282   1.0000
   6.750   0.8516   0.02871   0.01864  -0.0208   0.2636   1.0000
   7.000   0.8630   0.03057   0.02021  -0.0176   0.2125   1.0000
   7.250   0.8852   0.03311   0.02260  -0.0161   0.1736   1.0000
   7.500   0.8999   0.03513   0.02470  -0.0137   0.1467   1.0000
   7.750   0.9275   0.03845   0.02803  -0.0132   0.1299   1.0000
   8.000   0.9416   0.04120   0.03129  -0.0102   0.1203   1.0000
   8.250   0.9491   0.04380   0.03424  -0.0068   0.1106   1.0000
   8.500   0.9637   0.04718   0.03768  -0.0048   0.1032   1.0000
   8.750   0.9638   0.05052   0.04161  -0.0004   0.1017   1.0000
   9.000   0.9606   0.05415   0.04574   0.0041   0.1009   1.0000
   9.250   0.9543   0.05778   0.04977   0.0085   0.1008   1.0000
   9.500   0.9452   0.06152   0.05385   0.0127   0.1013   1.0000
   9.750   0.9336   0.06532   0.05793   0.0167   0.1019   1.0000
  10.000   0.9184   0.06902   0.06185   0.0205   0.1022   1.0000
  10.250   0.9016   0.07274   0.06574   0.0240   0.1026   1.0000
  10.500   0.8867   0.07651   0.06961   0.0270   0.1032   1.0000
  10.750   0.8706   0.08055   0.07373   0.0294   0.1036   1.0000
  11.000   0.7116   0.07872   0.07243   0.0330   0.1146   1.0000
  11.250   0.6355   0.09473   0.08825   0.0221   0.1406   1.0000
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