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MH 102 16.99% (mh102-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 102 16.99% (mh102-il)
Reynolds number: 50,000
Max Cl/Cd: 23.64 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh102-il-50000-n5.txt
Download as CSV file: xf-mh102-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 102  16.99%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.4751   0.10254   0.09504  -0.0453   1.0000   0.0787
 -12.750  -0.4588   0.10274   0.09526  -0.0444   1.0000   0.0831
 -12.500  -0.4945   0.09174   0.08435  -0.0497   1.0000   0.0863
 -12.000  -0.5464   0.07594   0.06863  -0.0572   1.0000   0.0930
 -11.750  -0.5875   0.06625   0.05886  -0.0623   1.0000   0.0947
 -11.500  -0.6186   0.05895   0.05141  -0.0660   1.0000   0.0969
 -11.250  -0.6290   0.05539   0.04792  -0.0671   1.0000   0.1014
 -11.000  -0.6457   0.05148   0.04399  -0.0681   1.0000   0.1054
 -10.750  -0.6716   0.04738   0.03974  -0.0681   1.0000   0.1088
 -10.500  -0.6827   0.04586   0.03839  -0.0658   1.0000   0.1134
 -10.250  -0.7026   0.04379   0.03630  -0.0625   1.0000   0.1182
 -10.000  -0.7121   0.04245   0.03505  -0.0594   1.0000   0.1248
  -9.750  -0.7257   0.04072   0.03321  -0.0560   1.0000   0.1326
  -9.500  -0.7284   0.04028   0.03291  -0.0526   1.0000   0.1409
  -9.250  -0.7348   0.03940   0.03201  -0.0490   1.0000   0.1496
  -9.000  -0.7421   0.03837   0.03081  -0.0455   1.0000   0.1591
  -8.750  -0.7399   0.03843   0.03095  -0.0422   1.0000   0.1681
  -8.500  -0.7130   0.03811   0.03048  -0.0438   0.9903   0.1844
  -8.250  -0.6782   0.03788   0.03007  -0.0465   0.9775   0.2011
  -8.000  -0.6427   0.03777   0.02983  -0.0487   0.9649   0.2158
  -7.750  -0.6068   0.03746   0.02937  -0.0509   0.9531   0.2293
  -7.500  -0.5763   0.03660   0.02825  -0.0526   0.9398   0.2416
  -7.250  -0.5442   0.03593   0.02735  -0.0541   0.9272   0.2529
  -7.000  -0.5066   0.03538   0.02670  -0.0561   0.9169   0.2624
  -6.750  -0.4747   0.03412   0.02503  -0.0582   0.9054   0.2736
  -6.500  -0.4403   0.03375   0.02466  -0.0592   0.8936   0.2806
  -6.250  -0.4075   0.03258   0.02308  -0.0610   0.8832   0.2911
  -6.000  -0.3752   0.03215   0.02266  -0.0616   0.8709   0.2974
  -5.750  -0.3465   0.03139   0.02166  -0.0621   0.8585   0.3063
  -5.500  -0.3116   0.03070   0.02083  -0.0633   0.8486   0.3138
  -5.250  -0.2860   0.03020   0.02018  -0.0630   0.8350   0.3216
  -5.000  -0.2578   0.02957   0.01934  -0.0632   0.8233   0.3298
  -4.750  -0.2273   0.02911   0.01880  -0.0634   0.8124   0.3374
  -4.500  -0.2033   0.02862   0.01806  -0.0630   0.7995   0.3464
  -4.250  -0.1725   0.02822   0.01763  -0.0631   0.7895   0.3540
  -4.000  -0.1482   0.02784   0.01705  -0.0625   0.7771   0.3634
  -3.750  -0.1218   0.02754   0.01673  -0.0621   0.7659   0.3713
  -3.500  -0.0938   0.02717   0.01618  -0.0619   0.7557   0.3820
  -3.250  -0.0694   0.02698   0.01598  -0.0612   0.7440   0.3907
  -3.000  -0.0396   0.02663   0.01544  -0.0613   0.7352   0.4027
  -2.750  -0.0164   0.02651   0.01537  -0.0604   0.7232   0.4124
  -2.500   0.0130   0.02623   0.01497  -0.0604   0.7148   0.4251
  -2.250   0.0366   0.02616   0.01486  -0.0597   0.7034   0.4377
  -2.000   0.0651   0.02595   0.01463  -0.0595   0.6952   0.4512
  -1.750   0.0885   0.02591   0.01459  -0.0587   0.6845   0.4656
  -1.500   0.1163   0.02575   0.01437  -0.0584   0.6766   0.4822
  -1.250   0.1390   0.02578   0.01442  -0.0575   0.6664   0.4994
  -1.000   0.1678   0.02558   0.01422  -0.0572   0.6596   0.5193
  -0.750   0.1880   0.02572   0.01445  -0.0560   0.6491   0.5389
  -0.500   0.2156   0.02557   0.01434  -0.0554   0.6423   0.5625
  -0.250   0.2357   0.02574   0.01463  -0.0541   0.6328   0.5873
   0.000   0.2611   0.02568   0.01463  -0.0532   0.6257   0.6168
   0.250   0.2827   0.02579   0.01487  -0.0518   0.6177   0.6488
   0.500   0.3048   0.02587   0.01509  -0.0504   0.6098   0.6851
   0.750   0.3327   0.02576   0.01505  -0.0494   0.6043   0.7283
   1.000   0.3509   0.02615   0.01565  -0.0476   0.5949   0.7726
   1.250   0.3839   0.02617   0.01572  -0.0476   0.5885   0.8252
   1.500   0.4219   0.02649   0.01611  -0.0492   0.5803   0.8780
   1.750   0.4724   0.02672   0.01631  -0.0533   0.5724   0.9276
   2.000   0.5291   0.02687   0.01634  -0.0587   0.5652   0.9704
   2.250   0.5679   0.02734   0.01676  -0.0618   0.5563   1.0000
   2.500   0.5874   0.02749   0.01675  -0.0605   0.5509   1.0000
   2.750   0.5959   0.02819   0.01741  -0.0581   0.5431   1.0000
   3.000   0.6126   0.02862   0.01775  -0.0565   0.5364   1.0000
   3.250   0.6390   0.02872   0.01770  -0.0560   0.5316   1.0000
   3.500   0.6446   0.02975   0.01876  -0.0534   0.5227   1.0000
   3.750   0.6670   0.03006   0.01900  -0.0524   0.5167   1.0000
   4.000   0.6872   0.03055   0.01942  -0.0513   0.5107   1.0000
   4.250   0.6980   0.03146   0.02035  -0.0493   0.5025   1.0000
   4.500   0.7253   0.03161   0.02042  -0.0489   0.4972   1.0000
   4.750   0.7350   0.03266   0.02151  -0.0469   0.4895   1.0000
   5.000   0.7528   0.03329   0.02212  -0.0456   0.4826   1.0000
   5.250   0.7853   0.03322   0.02197  -0.0457   0.4779   1.0000
   5.500   0.7824   0.03493   0.02380  -0.0426   0.4686   1.0000
   5.750   0.8079   0.03519   0.02402  -0.0421   0.4628   1.0000
   6.000   0.8227   0.03603   0.02487  -0.0406   0.4560   1.0000
   6.250   0.8287   0.03732   0.02623  -0.0384   0.4480   1.0000
   6.500   0.8630   0.03713   0.02598  -0.0386   0.4433   1.0000
   6.750   0.8497   0.03945   0.02842  -0.0349   0.4337   1.0000
   7.000   0.8742   0.03975   0.02872  -0.0343   0.4279   1.0000
   7.250   0.8886   0.04062   0.02962  -0.0329   0.4215   1.0000
   7.500   0.8738   0.04295   0.03201  -0.0292   0.4124   1.0000
   7.750   0.9179   0.04217   0.03121  -0.0300   0.4081   1.0000
   8.000   0.8635   0.04730   0.03645  -0.0247   0.3962   1.0000
   8.250   0.9019   0.04649   0.03564  -0.0245   0.3920   1.0000
   8.500   0.8513   0.05277   0.04201  -0.0222   0.3787   1.0000
   8.750   0.8860   0.05196   0.04121  -0.0214   0.3749   1.0000
   9.000   0.9364   0.04994   0.03920  -0.0211   0.3724   1.0000
   9.250   0.8747   0.05800   0.04735  -0.0200   0.3575   1.0000
   9.750   0.8657   0.06457   0.05400  -0.0196   0.3403   1.0000
  10.750   0.8548   0.07825   0.06787  -0.0203   0.3072   1.0000
  11.250   0.8486   0.08569   0.07541  -0.0214   0.2914   1.0000
  11.750   0.8420   0.09344   0.08326  -0.0228   0.2761   1.0000
  12.250   0.8332   0.10183   0.09176  -0.0248   0.2614   1.0000
  12.500   0.8601   0.10120   0.09119  -0.0236   0.2587   1.0000
  13.000   0.8475   0.11055   0.10064  -0.0263   0.2441   1.0000
  13.500   0.8352   0.12014   0.11035  -0.0295   0.2303   1.0000
  13.750   0.8595   0.11991   0.11019  -0.0285   0.2276   1.0000
  14.250   0.8442   0.13033   0.12072  -0.0325   0.2141   1.0000
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