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MH 78 14.47% (mh78-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 78 14.47% (mh78-il)
Reynolds number: 100,000
Max Cl/Cd: 33.65 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh78-il-100000-n5.txt
Download as CSV file: xf-mh78-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 78  14.47%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6339   0.07744   0.07274   0.0053   1.0000   0.0260
 -10.000  -0.6505   0.07072   0.06594  -0.0002   1.0000   0.0257
  -9.750  -0.6775   0.06435   0.05940  -0.0038   1.0000   0.0255
  -9.500  -0.6994   0.05972   0.05459  -0.0043   1.0000   0.0253
  -9.250  -0.7207   0.05565   0.05028  -0.0027   1.0000   0.0253
  -9.000  -0.7317   0.05179   0.04612  -0.0011   1.0000   0.0253
  -8.750  -0.7389   0.04778   0.04168   0.0007   1.0000   0.0257
  -8.500  -0.7407   0.04393   0.03729   0.0026   1.0000   0.0260
  -8.250  -0.7280   0.04162   0.03482   0.0036   1.0000   0.0265
  -7.750  -0.6937   0.03789   0.03061   0.0055   0.8473   0.0274
  -7.250  -0.6664   0.03433   0.02624   0.0103   0.7683   0.0280
  -7.000  -0.6485   0.03264   0.02418   0.0121   0.7397   0.0285
  -6.750  -0.6283   0.03106   0.02224   0.0137   0.7139   0.0290
  -6.500  -0.6065   0.02959   0.02043   0.0151   0.6907   0.0296
  -6.250  -0.5835   0.02827   0.01886   0.0163   0.6690   0.0303
  -6.000  -0.5603   0.02724   0.01772   0.0172   0.6486   0.0310
  -5.750  -0.5365   0.02627   0.01661   0.0182   0.6292   0.0321
  -5.500  -0.5122   0.02537   0.01550   0.0192   0.6107   0.0340
  -5.250  -0.4886   0.02456   0.01466   0.0201   0.5934   0.0358
  -5.000  -0.4646   0.02381   0.01376   0.0211   0.5770   0.0382
  -4.750  -0.4413   0.02304   0.01291   0.0221   0.5617   0.0404
  -4.500  -0.4177   0.02234   0.01209   0.0232   0.5473   0.0431
  -4.250  -0.3938   0.02168   0.01138   0.0241   0.5325   0.0473
  -4.000  -0.3698   0.02107   0.01069   0.0250   0.5190   0.0532
  -3.750  -0.3459   0.02045   0.01000   0.0260   0.5063   0.0617
  -3.500  -0.3217   0.01979   0.00940   0.0269   0.4934   0.0761
  -3.250  -0.2984   0.01905   0.00883   0.0279   0.4821   0.1090
  -3.000  -0.2752   0.01830   0.00843   0.0287   0.4701   0.1784
  -2.750  -0.2518   0.01768   0.00813   0.0295   0.4594   0.2559
  -2.500  -0.2289   0.01708   0.00786   0.0305   0.4487   0.3409
  -2.250  -0.2075   0.01639   0.00766   0.0319   0.4388   0.4534
  -2.000  -0.1858   0.01564   0.00763   0.0339   0.4292   0.6119
  -1.750  -0.1373   0.01579   0.00832   0.0327   0.4170   0.7797
  -1.500  -0.1037   0.01618   0.00854   0.0330   0.4073   0.8338
  -1.250  -0.0709   0.01651   0.00871   0.0331   0.3973   0.8633
  -1.000  -0.0406   0.01681   0.00879   0.0335   0.3889   0.8859
  -0.750  -0.0042   0.01712   0.00892   0.0326   0.3799   0.9025
  -0.500   0.0361   0.01739   0.00898   0.0310   0.3710   0.9161
  -0.250   0.0753   0.01764   0.00904   0.0294   0.3628   0.9295
   0.000   0.1156   0.01786   0.00910   0.0275   0.3545   0.9431
   0.250   0.1617   0.01808   0.00909   0.0244   0.3474   0.9557
   0.500   0.2094   0.01820   0.00910   0.0209   0.3388   0.9663
   0.750   0.2520   0.01828   0.00898   0.0181   0.3323   0.9756
   1.000   0.2920   0.01838   0.00899   0.0158   0.3256   0.9838
   1.250   0.3326   0.01841   0.00891   0.0132   0.3191   0.9901
   1.500   0.3705   0.01846   0.00878   0.0111   0.3140   0.9960
   1.750   0.4049   0.01856   0.00884   0.0097   0.3083   1.0000
   2.000   0.4286   0.01872   0.00896   0.0102   0.3035   1.0000
   2.250   0.4523   0.01888   0.00903   0.0109   0.2993   1.0000
   2.500   0.4758   0.01908   0.00909   0.0115   0.2958   1.0000
   2.750   0.4997   0.01932   0.00935   0.0121   0.2914   1.0000
   3.000   0.5234   0.01957   0.00960   0.0126   0.2870   1.0000
   3.250   0.5468   0.01981   0.00978   0.0133   0.2831   1.0000
   3.500   0.5699   0.02005   0.00992   0.0141   0.2798   1.0000
   3.750   0.5931   0.02038   0.01021   0.0147   0.2767   1.0000
   4.000   0.6162   0.02075   0.01066   0.0153   0.2727   1.0000
   4.250   0.6391   0.02110   0.01101   0.0160   0.2689   1.0000
   4.500   0.6618   0.02141   0.01128   0.0168   0.2656   1.0000
   4.750   0.6843   0.02172   0.01150   0.0176   0.2628   1.0000
   5.000   0.7065   0.02216   0.01195   0.0184   0.2599   1.0000
   5.250   0.7284   0.02268   0.01257   0.0191   0.2564   1.0000
   5.500   0.7500   0.02315   0.01309   0.0199   0.2531   1.0000
   5.750   0.7716   0.02356   0.01351   0.0208   0.2501   1.0000
   6.000   0.7931   0.02393   0.01382   0.0217   0.2475   1.0000
   6.250   0.8147   0.02434   0.01414   0.0227   0.2453   1.0000
   6.500   0.8341   0.02506   0.01504   0.0235   0.2422   1.0000
   6.750   0.8534   0.02576   0.01586   0.0245   0.2391   1.0000
   7.000   0.8728   0.02636   0.01652   0.0255   0.2363   1.0000
   7.250   0.8925   0.02686   0.01703   0.0265   0.2337   1.0000
   7.500   0.9127   0.02729   0.01743   0.0276   0.2315   1.0000
   7.750   0.9334   0.02774   0.01780   0.0287   0.2296   1.0000
   8.000   0.9477   0.02881   0.01911   0.0298   0.2267   1.0000
   8.250   0.9622   0.02982   0.02028   0.0310   0.2240   1.0000
   8.500   0.9774   0.03069   0.02126   0.0323   0.2214   1.0000
   8.750   0.9938   0.03139   0.02200   0.0335   0.2191   1.0000
   9.000   1.0121   0.03193   0.02253   0.0346   0.2171   1.0000
   9.250   1.0320   0.03238   0.02293   0.0356   0.2153   1.0000
   9.500   1.0435   0.03355   0.02422   0.0369   0.2131   1.0000
   9.750   1.0458   0.03537   0.02631   0.0385   0.2105   1.0000
  10.000   1.0484   0.03711   0.02823   0.0398   0.2081   1.0000
  10.250   1.0528   0.03863   0.02987   0.0411   0.2058   1.0000
  10.500   1.0610   0.03980   0.03110   0.0422   0.2038   1.0000
  10.750   1.0763   0.04051   0.03180   0.0431   0.2021   1.0000
  11.000   1.0998   0.04075   0.03198   0.0438   0.2006   1.0000
  12.500   0.6996   0.11405   0.10622   0.0092   0.1627   1.0000
  12.750   0.7152   0.11512   0.10730   0.0093   0.1616   1.0000
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