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

MH 61 10.26% (mh61-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 61 10.26% (mh61-il)
Reynolds number: 100,000
Max Cl/Cd: 47.15 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh61-il-100000-n5.txt
Download as CSV file: xf-mh61-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 61  10.26%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5795   0.08827   0.08405   0.0013   1.0000   0.0143
  -9.000  -0.5835   0.08206   0.07791  -0.0030   1.0000   0.0140
  -8.750  -0.5902   0.07439   0.07028  -0.0092   1.0000   0.0137
  -8.500  -0.6021   0.06643   0.06230  -0.0172   1.0000   0.0134
  -8.250  -0.6154   0.06094   0.05668  -0.0205   1.0000   0.0132
  -8.000  -0.6223   0.05564   0.05117  -0.0228   1.0000   0.0130
  -7.750  -0.6235   0.05065   0.04588  -0.0242   1.0000   0.0128
  -7.500  -0.6195   0.04590   0.04074  -0.0250   1.0000   0.0125
  -7.250  -0.6103   0.04159   0.03599  -0.0252   1.0000   0.0123
  -7.000  -0.5972   0.03775   0.03166  -0.0251   1.0000   0.0122
  -6.750  -0.5774   0.03422   0.02760  -0.0255   0.9760   0.0121
  -6.500  -0.5512   0.03108   0.02391  -0.0263   0.9567   0.0123
  -6.000  -0.5018   0.02666   0.01863  -0.0257   0.9295   0.0131
  -5.750  -0.4784   0.02531   0.01699  -0.0249   0.9177   0.0152
  -5.500  -0.4552   0.02410   0.01552  -0.0239   0.9069   0.0166
  -5.250  -0.4343   0.02248   0.01374  -0.0225   0.8970   0.0181
  -5.000  -0.4148   0.02114   0.01225  -0.0209   0.8878   0.0199
  -4.750  -0.3933   0.02012   0.01107  -0.0197   0.8784   0.0224
  -4.500  -0.3713   0.01923   0.00998  -0.0184   0.8697   0.0286
  -4.250  -0.3505   0.01812   0.00882  -0.0169   0.8619   0.0436
  -4.000  -0.3328   0.01623   0.00784  -0.0157   0.8532   0.1857
  -3.750  -0.3133   0.01535   0.00750  -0.0145   0.8458   0.3240
  -3.500  -0.2913   0.01489   0.00728  -0.0133   0.8377   0.4075
  -3.250  -0.2680   0.01457   0.00704  -0.0122   0.8304   0.4641
  -3.000  -0.2442   0.01430   0.00679  -0.0111   0.8230   0.5118
  -2.750  -0.2196   0.01405   0.00658  -0.0102   0.8156   0.5576
  -2.500  -0.1952   0.01381   0.00638  -0.0091   0.8087   0.6043
  -2.250  -0.1692   0.01359   0.00618  -0.0084   0.8012   0.6545
  -2.000  -0.1431   0.01338   0.00603  -0.0075   0.7947   0.7083
  -1.750  -0.1137   0.01321   0.00595  -0.0072   0.7871   0.7662
  -1.500  -0.0797   0.01309   0.00585  -0.0076   0.7809   0.8244
  -1.250  -0.0373   0.01307   0.00576  -0.0100   0.7733   0.8754
  -1.000   0.0049   0.01307   0.00564  -0.0123   0.7669   0.9145
  -0.750   0.0486   0.01310   0.00556  -0.0153   0.7586   0.9438
  -0.500   0.0887   0.01311   0.00540  -0.0176   0.7517   0.9687
  -0.250   0.1317   0.01310   0.00529  -0.0208   0.7429   0.9894
   0.000   0.1670   0.01308   0.00516  -0.0225   0.7346   1.0000
   0.250   0.1896   0.01309   0.00507  -0.0216   0.7265   1.0000
   0.500   0.2138   0.01313   0.00504  -0.0211   0.7170   1.0000
   0.750   0.2374   0.01316   0.00500  -0.0203   0.7085   1.0000
   1.000   0.2613   0.01320   0.00497  -0.0196   0.6996   1.0000
   1.250   0.2860   0.01327   0.00500  -0.0191   0.6897   1.0000
   1.500   0.3103   0.01332   0.00502  -0.0184   0.6805   1.0000
   1.750   0.3345   0.01337   0.00502  -0.0176   0.6714   1.0000
   2.000   0.3596   0.01345   0.00510  -0.0171   0.6605   1.0000
   2.250   0.3846   0.01352   0.00517  -0.0165   0.6499   1.0000
   2.500   0.4094   0.01359   0.00527  -0.0159   0.6393   1.0000
   2.750   0.4342   0.01366   0.00532  -0.0151   0.6287   1.0000
   3.000   0.4593   0.01374   0.00543  -0.0145   0.6170   1.0000
   3.250   0.4845   0.01385   0.00556  -0.0140   0.6044   1.0000
   3.500   0.5097   0.01395   0.00570  -0.0134   0.5914   1.0000
   3.750   0.5349   0.01407   0.00589  -0.0128   0.5778   1.0000
   4.000   0.5600   0.01419   0.00605  -0.0122   0.5636   1.0000
   4.250   0.5850   0.01433   0.00622  -0.0115   0.5486   1.0000
   4.500   0.6102   0.01449   0.00645  -0.0110   0.5315   1.0000
   4.750   0.6352   0.01467   0.00674  -0.0104   0.5131   1.0000
   5.000   0.6598   0.01486   0.00694  -0.0097   0.4938   1.0000
   5.250   0.6845   0.01510   0.00724  -0.0091   0.4712   1.0000
   5.500   0.7089   0.01537   0.00755  -0.0085   0.4474   1.0000
   5.750   0.7329   0.01569   0.00789  -0.0078   0.4211   1.0000
   6.000   0.7565   0.01607   0.00829  -0.0071   0.3920   1.0000
   6.250   0.7794   0.01653   0.00874  -0.0065   0.3595   1.0000
   6.500   0.8016   0.01709   0.00934  -0.0058   0.3217   1.0000
   6.750   0.8224   0.01780   0.00995  -0.0051   0.2773   1.0000
   7.000   0.8416   0.01871   0.01069  -0.0043   0.2238   1.0000
   7.250   0.8588   0.01988   0.01161  -0.0034   0.1673   1.0000
   7.500   0.8739   0.02131   0.01274  -0.0025   0.1159   1.0000
   7.750   0.8878   0.02284   0.01406  -0.0013   0.0787   1.0000
   8.000   0.9008   0.02440   0.01550   0.0000   0.0547   1.0000
   8.250   0.9122   0.02603   0.01713   0.0016   0.0418   1.0000
   8.500   0.9233   0.02760   0.01878   0.0032   0.0327   1.0000
   8.750   0.9310   0.02938   0.02063   0.0050   0.0271   1.0000
   9.000   0.9391   0.03112   0.02252   0.0069   0.0233   1.0000
   9.250   0.9444   0.03291   0.02437   0.0087   0.0202   1.0000
   9.500   0.9489   0.03478   0.02645   0.0107   0.0181   1.0000
   9.750   0.9557   0.03675   0.02862   0.0125   0.0162   1.0000
  10.000   0.9632   0.03894   0.03099   0.0142   0.0151   1.0000
  10.250   0.9700   0.04125   0.03348   0.0155   0.0142   1.0000
  10.500   0.9752   0.04361   0.03602   0.0167   0.0135   1.0000
  10.750   0.9770   0.04612   0.03869   0.0175   0.0127   1.0000
  11.000   0.9732   0.04931   0.04201   0.0181   0.0117   1.0000
  11.250   0.9680   0.05322   0.04615   0.0185   0.0113   1.0000
  11.500   0.9643   0.05639   0.04958   0.0184   0.0110   1.0000
  11.750   0.9577   0.06018   0.05362   0.0179   0.0109   1.0000
  12.000   0.9488   0.06435   0.05805   0.0167   0.0107   1.0000
  12.250   0.9375   0.06905   0.06299   0.0149   0.0104   1.0000
  12.500   0.9244   0.07436   0.06852   0.0124   0.0102   1.0000
  12.750   0.9091   0.08042   0.07478   0.0092   0.0102   1.0000
  13.000   0.8934   0.08700   0.08154   0.0053   0.0102   1.0000
  13.250   0.8775   0.09411   0.08878   0.0012   0.0106   1.0000
  13.500   0.8605   0.10210   0.09690  -0.0037   0.0108   1.0000
  13.750   0.8441   0.11050   0.10538  -0.0085   0.0112   1.0000
  14.000   0.8276   0.11967   0.11462  -0.0139   0.0113   1.0000
  14.250   0.6591   0.13003   0.12550  -0.0145   0.0162   1.0000
<< Back to MH 61 10.26% (mh61-il)

Polar data table (+)

Polar graphs


<< Back to MH 61 10.26% (mh61-il)