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MH 104 15.28% (mh104-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 104 15.28% (mh104-il)
Reynolds number: 50,000
Max Cl/Cd: 11.99 at α=0°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh104-il-50000.txt
Download as CSV file: xf-mh104-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 104  15.28%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5367   0.10157   0.09528  -0.0194   1.0000   0.1145
 -10.750  -0.5375   0.09586   0.08963  -0.0213   1.0000   0.1135
 -10.500  -0.6081   0.07918   0.07297  -0.0354   1.0000   0.1002
 -10.250  -0.6269   0.07331   0.06709  -0.0380   1.0000   0.0989
 -10.000  -0.6498   0.06831   0.06203  -0.0392   1.0000   0.0975
  -9.750  -0.6753   0.06395   0.05755  -0.0383   1.0000   0.0962
  -9.500  -0.6946   0.05967   0.05307  -0.0371   1.0000   0.0950
  -9.250  -0.7085   0.05550   0.04860  -0.0354   1.0000   0.0942
  -9.000  -0.7151   0.05162   0.04438  -0.0335   1.0000   0.0940
  -8.750  -0.7150   0.04818   0.04060  -0.0315   1.0000   0.0954
  -8.500  -0.7118   0.04506   0.03709  -0.0293   1.0000   0.0979
  -8.250  -0.7072   0.04222   0.03372  -0.0268   1.0000   0.1006
  -8.000  -0.6903   0.03943   0.03101  -0.0257   1.0000   0.1060
  -7.750  -0.6773   0.03716   0.02852  -0.0237   1.0000   0.1120
  -7.500  -0.6659   0.03519   0.02662  -0.0216   1.0000   0.1208
  -7.250  -0.6608   0.03357   0.02490  -0.0183   1.0000   0.1304
  -7.000  -0.6611   0.03256   0.02395  -0.0146   1.0000   0.1407
  -6.750  -0.6629   0.03161   0.02314  -0.0107   1.0000   0.1533
  -6.500  -0.6648   0.03062   0.02221  -0.0069   1.0000   0.1724
  -6.250  -0.6664   0.02973   0.02154  -0.0032   1.0000   0.2005
  -6.000  -0.6702   0.02896   0.02113   0.0010   1.0000   0.2464
  -5.750  -0.6575   0.02895   0.02170   0.0028   0.9917   0.3291
  -5.500  -0.6149   0.02996   0.02293   0.0004   0.9724   0.4054
  -5.250  -0.5672   0.03076   0.02382  -0.0023   0.9553   0.4616
  -5.000  -0.5201   0.03095   0.02399  -0.0049   0.9393   0.5020
  -4.750  -0.4723   0.03076   0.02368  -0.0079   0.9240   0.5357
  -4.500  -0.4239   0.03045   0.02323  -0.0111   0.9095   0.5661
  -4.250  -0.3846   0.03011   0.02272  -0.0129   0.8949   0.5938
  -4.000  -0.3473   0.02992   0.02243  -0.0141   0.8804   0.6201
  -3.750  -0.3116   0.02983   0.02227  -0.0147   0.8663   0.6458
  -3.500  -0.2826   0.02973   0.02205  -0.0146   0.8529   0.6724
  -3.250  -0.2481   0.02982   0.02206  -0.0149   0.8402   0.6995
  -3.000  -0.2068   0.03000   0.02215  -0.0158   0.8287   0.7282
  -2.750  -0.1656   0.03027   0.02231  -0.0168   0.8174   0.7572
  -2.500  -0.1294   0.03072   0.02266  -0.0174   0.8052   0.7860
  -2.250  -0.0802   0.03126   0.02305  -0.0198   0.7940   0.8158
  -2.000  -0.0135   0.03168   0.02325  -0.0247   0.7844   0.8457
  -1.750   0.0659   0.03225   0.02359  -0.0327   0.7721   0.8718
  -1.500   0.1343   0.03257   0.02372  -0.0399   0.7608   0.9001
  -1.250   0.2020   0.03257   0.02353  -0.0472   0.7511   0.9296
  -1.000   0.2705   0.03241   0.02320  -0.0556   0.7404   0.9597
  -0.750   0.3437   0.03202   0.02269  -0.0660   0.7295   0.9896
  -0.500   0.3786   0.03173   0.02226  -0.0692   0.7222   1.0000
  -0.250   0.3851   0.03258   0.02310  -0.0694   0.7134   1.0000
   0.000   0.3947   0.03293   0.02336  -0.0680   0.7072   1.0000
   0.250   0.3973   0.03413   0.02456  -0.0674   0.6993   1.0000
   0.500   0.4055   0.03482   0.02517  -0.0659   0.6930   1.0000
   0.750   0.4060   0.03613   0.02645  -0.0643   0.6865   1.0000
   1.000   0.4051   0.03746   0.02775  -0.0623   0.6800   1.0000
   1.250   0.4200   0.03805   0.02823  -0.0605   0.6749   1.0000
   1.500   0.3946   0.04058   0.03076  -0.0569   0.6690   1.0000
   1.750   0.3890   0.04214   0.03226  -0.0539   0.6637   1.0000
   2.000   0.4066   0.04298   0.03302  -0.0526   0.6585   1.0000
   2.250   0.3696   0.04572   0.03568  -0.0472   0.6551   1.0000
   2.500   0.3455   0.04782   0.03769  -0.0425   0.6521   1.0000
   2.750   0.3306   0.04959   0.03936  -0.0384   0.6495   1.0000
   3.000   0.3692   0.05058   0.04032  -0.0398   0.6429   1.0000
   3.250   0.3448   0.05272   0.04237  -0.0352   0.6421   1.0000
   3.500   0.3329   0.05474   0.04432  -0.0322   0.6416   1.0000
   3.750   0.3305   0.05678   0.04630  -0.0304   0.6421   1.0000
   4.000   0.3310   0.05889   0.04838  -0.0292   0.6439   1.0000
   4.250   0.1733   0.06280   0.05226  -0.0213   0.8061   1.0000
   4.500   0.1918   0.06460   0.05404  -0.0215   0.7913   1.0000
   4.750   0.2103   0.06646   0.05587  -0.0217   0.7763   1.0000
   5.000   0.2277   0.06838   0.05776  -0.0218   0.7627   1.0000
   5.250   0.2468   0.07047   0.05984  -0.0221   0.7493   1.0000
   5.500   0.2709   0.07299   0.06236  -0.0231   0.7364   1.0000
   5.750   0.2967   0.07562   0.06501  -0.0242   0.7224   1.0000
   6.250   0.3165   0.07859   0.06797  -0.0225   0.6934   1.0000
   6.500   0.3259   0.08031   0.06969  -0.0218   0.6800   1.0000
   6.750   0.3378   0.08235   0.07174  -0.0215   0.6678   1.0000
   7.000   0.3573   0.08500   0.07442  -0.0220   0.6564   1.0000
   7.250   0.3878   0.08839   0.07787  -0.0234   0.6435   1.0000
   7.500   0.3880   0.08942   0.07891  -0.0219   0.6298   1.0000
   7.750   0.3942   0.09121   0.08072  -0.0211   0.6166   1.0000
   8.000   0.4036   0.09343   0.08297  -0.0208   0.6050   1.0000
   8.250   0.4297   0.09699   0.08660  -0.0219   0.5951   1.0000
   8.500   0.4447   0.09933   0.08898  -0.0219   0.5813   1.0000
   8.750   0.4436   0.10074   0.09041  -0.0208   0.5685   1.0000
   9.000   0.4489   0.10304   0.09277  -0.0205   0.5581   1.0000
   9.250   0.4737   0.10675   0.09655  -0.0214   0.5481   1.0000
   9.500   0.4863   0.10912   0.09898  -0.0213   0.5347   1.0000
   9.750   0.4808   0.11066   0.10053  -0.0206   0.5238   1.0000
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