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MH 61 10.26% (mh61-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 61 10.26% (mh61-il)
Reynolds number: 100,000
Max Cl/Cd: 47.62 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh61-il-100000.txt
Download as CSV file: xf-mh61-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5672   0.12556   0.12116   0.0205   1.0000   0.0860
 -10.250  -0.5784   0.12197   0.11765   0.0148   1.0000   0.0894
 -10.000  -0.5995   0.11816   0.11401   0.0066   1.0000   0.0902
  -9.750  -0.5603   0.11295   0.10868   0.0138   1.0000   0.0942
  -9.500  -0.5549   0.10919   0.10494   0.0123   1.0000   0.0983
  -9.250  -0.5775   0.10505   0.10092   0.0037   1.0000   0.1030
  -9.000  -0.5666   0.10000   0.09591   0.0041   1.0000   0.1052
  -8.750  -0.5513   0.09653   0.09244   0.0052   1.0000   0.1092
  -8.250  -0.4817   0.08065   0.07702  -0.0077   1.0000   0.1292
  -6.750  -0.5741   0.04469   0.03910  -0.0282   1.0000   0.0495
  -6.500  -0.5619   0.03999   0.03413  -0.0278   1.0000   0.0450
  -6.250  -0.5538   0.03783   0.03104  -0.0244   1.0000   0.0391
  -6.000  -0.5503   0.03481   0.02787  -0.0215   1.0000   0.0378
  -5.750  -0.5463   0.03236   0.02513  -0.0183   1.0000   0.0370
  -5.500  -0.5384   0.03025   0.02273  -0.0155   1.0000   0.0363
  -5.250  -0.5275   0.02862   0.02074  -0.0129   1.0000   0.0372
  -5.000  -0.4951   0.02643   0.01807  -0.0139   0.9945   0.0395
  -4.750  -0.4585   0.02358   0.01510  -0.0159   0.9880   0.0423
  -4.500  -0.4174   0.02156   0.01298  -0.0181   0.9822   0.0466
  -4.250  -0.3829   0.01990   0.01126  -0.0193   0.9744   0.0534
  -4.000  -0.3496   0.01766   0.00937  -0.0206   0.9675   0.1065
  -3.750  -0.3299   0.01551   0.00902  -0.0200   0.9586   0.4472
  -3.500  -0.3005   0.01530   0.00905  -0.0201   0.9500   0.5431
  -3.250  -0.2651   0.01506   0.00898  -0.0210   0.9430   0.6196
  -3.000  -0.2370   0.01486   0.00892  -0.0205   0.9339   0.6835
  -2.750  -0.2001   0.01470   0.00887  -0.0212   0.9272   0.7538
  -2.500  -0.1590   0.01467   0.00885  -0.0226   0.9199   0.8236
  -2.250  -0.0980   0.01482   0.00887  -0.0274   0.9158   0.8841
  -2.000  -0.0352   0.01507   0.00890  -0.0331   0.9096   0.9236
  -1.750   0.0327   0.01520   0.00875  -0.0400   0.9041   0.9519
  -1.500   0.0980   0.01517   0.00852  -0.0471   0.8968   0.9784
  -1.250   0.1571   0.01487   0.00805  -0.0536   0.8890   1.0000
  -1.000   0.1700   0.01494   0.00799  -0.0518   0.8759   1.0000
  -0.750   0.1850   0.01506   0.00801  -0.0501   0.8634   1.0000
  -0.500   0.2014   0.01521   0.00806  -0.0484   0.8513   1.0000
  -0.250   0.2185   0.01539   0.00816  -0.0468   0.8397   1.0000
   0.000   0.2363   0.01557   0.00827  -0.0450   0.8284   1.0000
   0.250   0.2542   0.01575   0.00837  -0.0431   0.8178   1.0000
   0.500   0.2721   0.01590   0.00844  -0.0410   0.8076   1.0000
   0.750   0.2923   0.01611   0.00860  -0.0397   0.7958   1.0000
   1.000   0.3127   0.01631   0.00876  -0.0383   0.7844   1.0000
   1.250   0.3331   0.01649   0.00893  -0.0367   0.7733   1.0000
   1.500   0.3534   0.01663   0.00903  -0.0350   0.7628   1.0000
   1.750   0.3734   0.01671   0.00906  -0.0329   0.7530   1.0000
   2.000   0.3952   0.01687   0.00922  -0.0317   0.7409   1.0000
   2.250   0.4172   0.01702   0.00937  -0.0304   0.7290   1.0000
   2.500   0.4392   0.01715   0.00954  -0.0290   0.7171   1.0000
   2.750   0.4613   0.01724   0.00964  -0.0275   0.7055   1.0000
   3.000   0.4835   0.01728   0.00970  -0.0259   0.6941   1.0000
   3.250   0.5057   0.01725   0.00967  -0.0241   0.6832   1.0000
   3.500   0.5285   0.01724   0.00972  -0.0226   0.6711   1.0000
   3.750   0.5518   0.01727   0.00979  -0.0213   0.6579   1.0000
   4.000   0.5752   0.01726   0.00983  -0.0199   0.6444   1.0000
   4.250   0.5987   0.01723   0.00983  -0.0185   0.6305   1.0000
   4.500   0.6225   0.01720   0.00986  -0.0171   0.6152   1.0000
   4.750   0.6464   0.01721   0.01001  -0.0160   0.5978   1.0000
   5.000   0.6704   0.01713   0.00998  -0.0146   0.5804   1.0000
   5.250   0.6944   0.01699   0.00985  -0.0130   0.5628   1.0000
   5.500   0.7184   0.01701   0.00996  -0.0119   0.5409   1.0000
   5.750   0.7425   0.01696   0.00993  -0.0105   0.5191   1.0000
   6.000   0.7663   0.01697   0.00996  -0.0092   0.4942   1.0000
   6.250   0.7897   0.01707   0.01012  -0.0081   0.4652   1.0000
   6.500   0.8125   0.01725   0.01043  -0.0070   0.4311   1.0000
   6.750   0.8343   0.01752   0.01071  -0.0058   0.3912   1.0000
   7.000   0.8544   0.01798   0.01111  -0.0046   0.3417   1.0000
   7.250   0.8715   0.01885   0.01179  -0.0034   0.2745   1.0000
   7.500   0.8811   0.02072   0.01307  -0.0019   0.1794   1.0000
   7.750   0.8862   0.02335   0.01507   0.0003   0.1162   1.0000
   8.000   0.8949   0.02555   0.01705   0.0024   0.0834   1.0000
   8.250   0.9058   0.02774   0.01907   0.0044   0.0664   1.0000
   8.500   0.9193   0.02991   0.02116   0.0061   0.0536   1.0000
   8.750   0.9390   0.03246   0.02386   0.0077   0.0460   1.0000
   9.000   0.9556   0.03538   0.02677   0.0088   0.0391   1.0000
   9.250   0.9745   0.03826   0.03003   0.0103   0.0368   1.0000
   9.500   0.9891   0.04158   0.03384   0.0118   0.0356   1.0000
   9.750   0.9974   0.04502   0.03769   0.0135   0.0345   1.0000
  10.000   1.0020   0.04810   0.04109   0.0152   0.0333   1.0000
  10.250   1.0061   0.05087   0.04403   0.0165   0.0316   1.0000
  10.500   1.0035   0.05410   0.04751   0.0180   0.0311   1.0000
  10.750   0.9943   0.05729   0.05095   0.0199   0.0308   1.0000
  11.000   0.9828   0.06105   0.05484   0.0210   0.0299   1.0000
  11.250   0.9676   0.06435   0.05842   0.0217   0.0304   1.0000
  11.500   0.9462   0.06863   0.06301   0.0211   0.0312   1.0000
  11.750   0.8992   0.07712   0.07196   0.0170   0.0354   1.0000
  12.000   0.8769   0.08364   0.07863   0.0134   0.0365   1.0000
  12.250   0.8545   0.09090   0.08600   0.0087   0.0371   1.0000
  12.500   0.8342   0.09880   0.09396   0.0036   0.0380   1.0000
  12.750   0.8173   0.10692   0.10202  -0.0011   0.0390   1.0000
  13.000   0.8060   0.11439   0.10949  -0.0047   0.0398   1.0000
  13.250   0.7666   0.13473   0.12980  -0.0177   0.0496   1.0000
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