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MH 78 14.47% (mh78-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 78 14.47% (mh78-il)
Reynolds number: 200,000
Max Cl/Cd: 51.27 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh78-il-200000-n5.txt
Download as CSV file: xf-mh78-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7103   0.07247   0.06888   0.0076   1.0000   0.0156
 -10.750  -0.7570   0.06020   0.05631  -0.0030   1.0000   0.0154
 -10.500  -0.7876   0.05417   0.05001  -0.0052   1.0000   0.0153
 -10.250  -0.8131   0.04963   0.04520  -0.0043   1.0000   0.0152
 -10.000  -0.8301   0.04620   0.04152  -0.0017   1.0000   0.0151
  -9.750  -0.8408   0.04286   0.03785   0.0010   1.0000   0.0152
  -9.500  -0.8421   0.03974   0.03441   0.0032   1.0000   0.0152
  -9.250  -0.8376   0.03689   0.03123   0.0052   1.0000   0.0153
  -9.000  -0.8253   0.03444   0.02842   0.0064   0.9102   0.0154
  -8.750  -0.8165   0.03266   0.02619   0.0093   0.8288   0.0156
  -8.500  -0.8043   0.03097   0.02408   0.0118   0.7859   0.0158
  -8.250  -0.7887   0.02940   0.02215   0.0138   0.7526   0.0160
  -8.000  -0.7708   0.02798   0.02035   0.0155   0.7243   0.0162
  -7.750  -0.7507   0.02681   0.01896   0.0169   0.6989   0.0164
  -7.500  -0.7295   0.02584   0.01784   0.0180   0.6751   0.0167
  -7.250  -0.7075   0.02496   0.01681   0.0191   0.6532   0.0169
  -7.000  -0.6847   0.02411   0.01580   0.0201   0.6332   0.0173
  -6.750  -0.6614   0.02332   0.01485   0.0210   0.6139   0.0177
  -6.500  -0.6375   0.02259   0.01396   0.0219   0.5959   0.0184
  -6.250  -0.6132   0.02187   0.01301   0.0228   0.5790   0.0193
  -6.000  -0.5893   0.02122   0.01232   0.0236   0.5627   0.0200
  -5.750  -0.5649   0.02062   0.01162   0.0244   0.5471   0.0206
  -5.500  -0.5403   0.02000   0.01090   0.0252   0.5321   0.0214
  -5.250  -0.5157   0.01939   0.01016   0.0260   0.5181   0.0222
  -5.000  -0.4912   0.01881   0.00949   0.0269   0.5046   0.0230
  -4.750  -0.4662   0.01830   0.00893   0.0276   0.4911   0.0241
  -4.500  -0.4408   0.01784   0.00837   0.0283   0.4789   0.0254
  -4.250  -0.4155   0.01739   0.00783   0.0290   0.4667   0.0271
  -4.000  -0.3895   0.01701   0.00738   0.0296   0.4548   0.0298
  -3.750  -0.3637   0.01664   0.00694   0.0302   0.4437   0.0338
  -3.500  -0.3376   0.01626   0.00654   0.0308   0.4326   0.0391
  -3.250  -0.3118   0.01588   0.00614   0.0315   0.4230   0.0475
  -3.000  -0.2860   0.01547   0.00579   0.0321   0.4126   0.0641
  -2.750  -0.2610   0.01500   0.00546   0.0327   0.4033   0.0988
  -2.500  -0.2362   0.01450   0.00521   0.0333   0.3936   0.1565
  -2.250  -0.2116   0.01407   0.00500   0.0339   0.3852   0.2178
  -2.000  -0.1871   0.01364   0.00482   0.0346   0.3769   0.2842
  -1.750  -0.1636   0.01320   0.00464   0.0355   0.3691   0.3607
  -1.000  -0.0990   0.01155   0.00467   0.0408   0.3472   0.7636
  -0.500  -0.0350   0.01200   0.00509   0.0412   0.3327   0.8600
  -0.250  -0.0054   0.01219   0.00519   0.0415   0.3262   0.8783
   0.000   0.0233   0.01236   0.00526   0.0419   0.3195   0.8930
   0.250   0.0508   0.01256   0.00532   0.0425   0.3137   0.9061
   0.500   0.0857   0.01276   0.00545   0.0417   0.3078   0.9144
   0.750   0.1127   0.01294   0.00553   0.0423   0.3024   0.9256
   1.000   0.1543   0.01322   0.00567   0.0402   0.2966   0.9328
   1.250   0.1897   0.01346   0.00584   0.0392   0.2911   0.9435
   1.500   0.2380   0.01368   0.00597   0.0356   0.2849   0.9493
   1.750   0.2704   0.01388   0.00606   0.0350   0.2805   0.9575
   2.000   0.3123   0.01404   0.00612   0.0324   0.2760   0.9608
   2.250   0.3491   0.01416   0.00620   0.0308   0.2710   0.9649
   2.500   0.3798   0.01430   0.00627   0.0304   0.2668   0.9700
   2.750   0.4150   0.01444   0.00631   0.0289   0.2628   0.9728
   3.000   0.4498   0.01458   0.00640   0.0276   0.2593   0.9755
   3.250   0.4825   0.01470   0.00651   0.0266   0.2555   0.9786
   3.500   0.5129   0.01484   0.00662   0.0261   0.2516   0.9820
   3.750   0.5455   0.01499   0.00669   0.0251   0.2481   0.9843
   4.000   0.5784   0.01518   0.00679   0.0240   0.2450   0.9865
   4.250   0.6106   0.01533   0.00697   0.0231   0.2419   0.9889
   4.500   0.6418   0.01549   0.00715   0.0223   0.2386   0.9913
   4.750   0.6723   0.01568   0.00732   0.0217   0.2354   0.9936
   5.000   0.7041   0.01585   0.00745   0.0207   0.2323   0.9955
   5.250   0.7350   0.01611   0.00762   0.0199   0.2295   0.9975
   5.500   0.7665   0.01631   0.00788   0.0190   0.2268   0.9995
   5.750   0.7920   0.01655   0.00817   0.0193   0.2242   1.0000
   6.000   0.8150   0.01680   0.00843   0.0200   0.2216   1.0000
   6.250   0.8377   0.01705   0.00868   0.0208   0.2190   1.0000
   6.500   0.8600   0.01733   0.00894   0.0216   0.2166   1.0000
   6.750   0.8819   0.01768   0.00922   0.0225   0.2144   1.0000
   7.000   0.9040   0.01799   0.00962   0.0233   0.2122   1.0000
   7.250   0.9257   0.01831   0.01001   0.0242   0.2099   1.0000
   7.500   0.9471   0.01865   0.01039   0.0252   0.2077   1.0000
   7.750   0.9681   0.01897   0.01074   0.0261   0.2054   1.0000
   8.000   0.9887   0.01931   0.01108   0.0271   0.2033   1.0000
   8.250   1.0089   0.01968   0.01143   0.0282   0.2012   1.0000
   8.500   1.0287   0.02010   0.01187   0.0293   0.1993   1.0000
   8.750   1.0481   0.02052   0.01239   0.0305   0.1973   1.0000
   9.000   1.0671   0.02096   0.01291   0.0316   0.1953   1.0000
   9.250   1.0857   0.02139   0.01340   0.0329   0.1932   1.0000
   9.500   1.1041   0.02181   0.01387   0.0341   0.1912   1.0000
   9.750   1.1222   0.02223   0.01431   0.0353   0.1893   1.0000
  10.000   1.1402   0.02268   0.01474   0.0366   0.1876   1.0000
  10.250   1.1578   0.02321   0.01528   0.0378   0.1859   1.0000
  10.500   1.1742   0.02380   0.01601   0.0390   0.1841   1.0000
  10.750   1.1903   0.02441   0.01672   0.0402   0.1822   1.0000
  11.000   1.2062   0.02501   0.01740   0.0414   0.1802   1.0000
  11.250   1.2220   0.02560   0.01806   0.0425   0.1783   1.0000
  11.500   1.2376   0.02620   0.01870   0.0436   0.1765   1.0000
  11.750   1.2532   0.02682   0.01933   0.0446   0.1750   1.0000
  12.000   1.2693   0.02748   0.01997   0.0456   0.1735   1.0000
  12.250   1.2780   0.02846   0.02111   0.0468   0.1719   1.0000
  12.500   1.2810   0.02956   0.02234   0.0485   0.1701   1.0000
  12.750   1.2838   0.03085   0.02375   0.0496   0.1683   1.0000
  13.000   1.2878   0.03229   0.02529   0.0501   0.1666   1.0000
  13.250   1.2924   0.03383   0.02691   0.0503   0.1650   1.0000
  13.500   1.2983   0.03539   0.02852   0.0503   0.1635   1.0000
  13.750   1.3076   0.03672   0.02984   0.0503   0.1619   1.0000
  14.000   1.3097   0.03881   0.03201   0.0498   0.1603   1.0000
  14.250   1.2987   0.04237   0.03578   0.0484   0.1585   1.0000
  14.500   1.2869   0.04624   0.03982   0.0467   0.1566   1.0000
  14.750   1.2753   0.05024   0.04396   0.0448   0.1546   1.0000
  15.000   1.2673   0.05392   0.04772   0.0430   0.1527   1.0000
  15.250   1.2665   0.05676   0.05060   0.0418   0.1511   1.0000
  15.500   1.2822   0.05749   0.05129   0.0420   0.1495   1.0000
  16.000   1.0355   0.10069   0.09517   0.0177   0.1376   1.0000
  16.250   1.0773   0.09717   0.09164   0.0199   0.1379   1.0000
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