Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MH 201 13.08% (mh201-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 201 13.08% (mh201-il)
Reynolds number: 500,000
Max Cl/Cd: 95.88 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh201-il-500000.txt
Download as CSV file: xf-mh201-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 201  13.08%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4542   0.06327   0.06107  -0.0718   0.9938   0.0201
  -9.000  -0.4671   0.05506   0.05263  -0.0820   0.9858   0.0202
  -8.750  -0.4803   0.04804   0.04477  -0.0902   0.9730   0.0213
  -8.500  -0.4780   0.04130   0.03791  -0.0919   0.9659   0.0219
  -8.250  -0.4552   0.03861   0.03518  -0.0940   0.9624   0.0224
  -8.000  -0.4291   0.03626   0.03271  -0.0965   0.9601   0.0233
  -7.750  -0.4082   0.03649   0.03231  -0.0965   0.9522   0.0264
  -7.500  -0.3892   0.03037   0.02615  -0.0987   0.9493   0.0278
  -7.250  -0.3638   0.02094   0.01547  -0.0978   0.9469   0.0130
  -7.000  -0.3302   0.01871   0.01304  -0.0995   0.9455   0.0123
  -6.750  -0.3068   0.01716   0.01132  -0.0987   0.9383   0.0120
  -6.500  -0.2745   0.01581   0.00983  -0.0998   0.9350   0.0117
  -6.250  -0.2405   0.01466   0.00859  -0.1014   0.9322   0.0118
  -6.000  -0.2133   0.01383   0.00770  -0.1016   0.9256   0.0119
  -5.750  -0.1827   0.01306   0.00686  -0.1025   0.9202   0.0123
  -5.500  -0.1492   0.01234   0.00606  -0.1040   0.9160   0.0131
  -5.250  -0.1245   0.01173   0.00539  -0.1036   0.9076   0.0139
  -5.000  -0.0930   0.01120   0.00481  -0.1046   0.9023   0.0165
  -4.750  -0.0673   0.01063   0.00423  -0.1044   0.8947   0.0246
  -4.500  -0.0405   0.00973   0.00366  -0.1048   0.8883   0.0961
  -4.250  -0.0143   0.00907   0.00337  -0.1052   0.8817   0.1863
  -4.000   0.0121   0.00846   0.00312  -0.1055   0.8751   0.2850
  -3.750   0.0406   0.00776   0.00287  -0.1064   0.8697   0.4154
  -3.500   0.0668   0.00731   0.00273  -0.1065   0.8629   0.5100
  -3.250   0.0952   0.00704   0.00270  -0.1067   0.8573   0.5937
  -3.000   0.1231   0.00701   0.00277  -0.1066   0.8515   0.6454
  -2.750   0.1511   0.00705   0.00279  -0.1064   0.8452   0.6695
  -2.500   0.1809   0.00713   0.00279  -0.1067   0.8399   0.6879
  -2.250   0.2080   0.00721   0.00285  -0.1064   0.8333   0.7015
  -2.000   0.2362   0.00728   0.00288  -0.1062   0.8273   0.7122
  -1.750   0.2648   0.00737   0.00290  -0.1063   0.8215   0.7222
  -1.500   0.2920   0.00744   0.00296  -0.1060   0.8147   0.7303
  -1.250   0.3212   0.00753   0.00296  -0.1061   0.8090   0.7381
  -1.000   0.3476   0.00759   0.00303  -0.1057   0.8020   0.7446
  -0.750   0.3764   0.00766   0.00302  -0.1058   0.7956   0.7518
  -0.500   0.4032   0.00771   0.00308  -0.1054   0.7888   0.7568
  -0.250   0.4304   0.00777   0.00312  -0.1051   0.7816   0.7632
   0.000   0.4582   0.00784   0.00315  -0.1050   0.7747   0.7696
   0.250   0.4844   0.00789   0.00321  -0.1044   0.7667   0.7747
   0.500   0.5123   0.00795   0.00322  -0.1044   0.7593   0.7800
   0.750   0.5396   0.00797   0.00322  -0.1042   0.7508   0.7843
   1.000   0.5662   0.00800   0.00325  -0.1038   0.7425   0.7878
   1.250   0.5930   0.00804   0.00327  -0.1035   0.7334   0.7916
   1.500   0.6200   0.00808   0.00330  -0.1033   0.7235   0.7958
   1.750   0.6474   0.00812   0.00330  -0.1032   0.7136   0.7996
   2.000   0.6729   0.00814   0.00333  -0.1026   0.7023   0.8029
   2.250   0.6988   0.00819   0.00339  -0.1022   0.6901   0.8067
   2.500   0.7250   0.00825   0.00342  -0.1018   0.6762   0.8107
   2.750   0.7514   0.00832   0.00345  -0.1015   0.6607   0.8144
   3.000   0.7759   0.00838   0.00349  -0.1008   0.6431   0.8171
   3.250   0.7999   0.00849   0.00355  -0.0999   0.6227   0.8201
   3.500   0.8240   0.00863   0.00363  -0.0992   0.5988   0.8232
   3.750   0.8476   0.00884   0.00373  -0.0984   0.5733   0.8265
   4.000   0.8709   0.00909   0.00386  -0.0976   0.5460   0.8296
   4.250   0.8928   0.00932   0.00401  -0.0965   0.5180   0.8322
   4.500   0.9143   0.00959   0.00419  -0.0953   0.4892   0.8351
   4.750   0.9359   0.00990   0.00440  -0.0942   0.4600   0.8383
   5.000   0.9576   0.01023   0.00462  -0.0932   0.4307   0.8415
   5.250   0.9796   0.01059   0.00486  -0.0923   0.4024   0.8447
   5.500   0.9996   0.01094   0.00511  -0.0909   0.3748   0.8476
   5.750   1.0202   0.01129   0.00538  -0.0897   0.3485   0.8506
   6.000   1.0409   0.01167   0.00567  -0.0885   0.3227   0.8540
   6.250   1.0614   0.01208   0.00598  -0.0874   0.2987   0.8577
   6.500   1.0823   0.01245   0.00628  -0.0864   0.2765   0.8610
   6.750   1.1012   0.01285   0.00662  -0.0849   0.2551   0.8643
   7.000   1.1207   0.01325   0.00696  -0.0836   0.2353   0.8680
   7.250   1.1396   0.01366   0.00731  -0.0822   0.2164   0.8724
   7.500   1.1574   0.01406   0.00767  -0.0805   0.1993   0.8765
   7.750   1.1739   0.01447   0.00805  -0.0787   0.1840   0.8807
   8.000   1.1909   0.01493   0.00847  -0.0770   0.1690   0.8856
   8.250   1.2081   0.01539   0.00891  -0.0753   0.1554   0.8908
   8.500   1.2235   0.01584   0.00936  -0.0733   0.1433   0.8966
   8.750   1.2398   0.01634   0.00985  -0.0716   0.1317   0.9033
   9.000   1.2533   0.01685   0.01036  -0.0694   0.1215   0.9105
   9.250   1.2683   0.01735   0.01087  -0.0674   0.1125   0.9194
   9.500   1.2806   0.01780   0.01138  -0.0650   0.1048   0.9324
   9.750   1.2902   0.01830   0.01193  -0.0621   0.0972   0.9680
  10.000   1.3099   0.01888   0.01254  -0.0615   0.0902   1.0000
  10.250   1.3257   0.01971   0.01334  -0.0603   0.0830   1.0000
  10.500   1.3438   0.02037   0.01402  -0.0594   0.0769   1.0000
  10.750   1.3572   0.02128   0.01493  -0.0580   0.0710   1.0000
  11.000   1.3737   0.02199   0.01569  -0.0569   0.0660   1.0000
  11.250   1.3837   0.02312   0.01680  -0.0551   0.0608   1.0000
  11.500   1.3999   0.02384   0.01760  -0.0540   0.0571   1.0000
  11.750   1.4111   0.02491   0.01867  -0.0525   0.0529   1.0000
  12.000   1.4218   0.02603   0.01985  -0.0510   0.0493   1.0000
  12.250   1.4341   0.02706   0.02094  -0.0497   0.0458   1.0000
  12.500   1.4398   0.02861   0.02249  -0.0479   0.0422   1.0000
  12.750   1.4518   0.02972   0.02370  -0.0468   0.0396   1.0000
  13.000   1.4614   0.03102   0.02504  -0.0456   0.0369   1.0000
  13.250   1.4637   0.03297   0.02702  -0.0439   0.0340   1.0000
  13.500   1.4759   0.03414   0.02829  -0.0431   0.0317   1.0000
  13.750   1.4826   0.03581   0.02999  -0.0420   0.0293   1.0000
  14.000   1.4857   0.03785   0.03208  -0.0409   0.0270   1.0000
  14.250   1.4950   0.03938   0.03371  -0.0401   0.0250   1.0000
  14.500   1.4985   0.04150   0.03587  -0.0393   0.0232   1.0000
  14.750   1.5001   0.04389   0.03834  -0.0386   0.0216   1.0000
  15.000   1.5069   0.04581   0.04035  -0.0382   0.0199   1.0000
  15.250   1.5080   0.04842   0.04304  -0.0377   0.0187   1.0000
  15.500   1.5040   0.05172   0.04641  -0.0375   0.0175   1.0000
  15.750   1.5059   0.05447   0.04929  -0.0375   0.0167   1.0000
  16.000   1.5066   0.05745   0.05239  -0.0376   0.0157   1.0000
  16.250   1.5039   0.06099   0.05603  -0.0381   0.0149   1.0000
  16.500   1.4964   0.06536   0.06049  -0.0390   0.0142   1.0000
  16.750   1.4901   0.06973   0.06500  -0.0400   0.0136   1.0000
  17.000   1.4867   0.07387   0.06929  -0.0413   0.0130   1.0000
  17.250   1.4804   0.07858   0.07414  -0.0429   0.0125   1.0000
  17.500   1.4726   0.08371   0.07939  -0.0448   0.0120   1.0000
  17.750   1.4620   0.08945   0.08525  -0.0473   0.0115   1.0000
  18.000   1.4476   0.09603   0.09197  -0.0502   0.0112   1.0000
  18.250   1.4304   0.10335   0.09942  -0.0538   0.0109   1.0000
<< Back to MH 201 13.08% (mh201-il)

Polar data table (+)

Polar graphs


<< Back to MH 201 13.08% (mh201-il)