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MH 46 9.1% (mh46-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 46 9.1% (mh46-il)
Reynolds number: 100,000
Max Cl/Cd: 46.34 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh46-il-100000-n5.txt
Download as CSV file: xf-mh46-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 46  9.1%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5651   0.08044   0.07577  -0.0104   1.0000   0.0133
  -8.750  -0.5708   0.07433   0.06972  -0.0144   1.0000   0.0132
  -8.500  -0.5783   0.06735   0.06276  -0.0205   1.0000   0.0130
  -8.250  -0.5909   0.06150   0.05684  -0.0247   1.0000   0.0129
  -8.000  -0.5979   0.05645   0.05163  -0.0270   1.0000   0.0127
  -7.750  -0.6027   0.05124   0.04616  -0.0284   1.0000   0.0126
  -7.500  -0.6020   0.04654   0.04112  -0.0289   1.0000   0.0125
  -7.250  -0.5967   0.04219   0.03637  -0.0287   1.0000   0.0125
  -7.000  -0.5876   0.03817   0.03187  -0.0280   1.0000   0.0126
  -6.750  -0.5744   0.03478   0.02799  -0.0270   1.0000   0.0127
  -6.500  -0.5576   0.03209   0.02479  -0.0259   1.0000   0.0134
  -6.250  -0.5422   0.02927   0.02169  -0.0250   1.0000   0.0146
  -6.000  -0.5228   0.02766   0.01986  -0.0241   1.0000   0.0162
  -5.750  -0.5025   0.02581   0.01772  -0.0230   1.0000   0.0176
  -5.500  -0.4821   0.02391   0.01554  -0.0216   1.0000   0.0186
  -5.250  -0.4624   0.02228   0.01370  -0.0200   1.0000   0.0198
  -5.000  -0.4440   0.02100   0.01224  -0.0182   1.0000   0.0211
  -4.750  -0.4292   0.01967   0.01083  -0.0162   1.0000   0.0243
  -4.500  -0.4130   0.01889   0.00994  -0.0142   1.0000   0.0304
  -4.250  -0.3819   0.01752   0.00851  -0.0152   0.9895   0.0440
  -4.000  -0.3475   0.01617   0.00743  -0.0170   0.9791   0.0915
  -3.750  -0.3124   0.01517   0.00678  -0.0190   0.9691   0.1710
  -3.500  -0.2792   0.01448   0.00638  -0.0205   0.9576   0.2547
  -3.250  -0.2467   0.01393   0.00602  -0.0216   0.9460   0.3341
  -3.000  -0.2152   0.01348   0.00576  -0.0224   0.9342   0.4077
  -2.750  -0.1848   0.01309   0.00554  -0.0228   0.9224   0.4791
  -2.500  -0.1554   0.01274   0.00534  -0.0227   0.9106   0.5497
  -2.250  -0.1266   0.01240   0.00518  -0.0224   0.8989   0.6230
  -2.000  -0.0980   0.01208   0.00502  -0.0219   0.8871   0.7023
  -1.750  -0.0640   0.01181   0.00494  -0.0221   0.8757   0.7922
  -1.500  -0.0117   0.01167   0.00483  -0.0261   0.8661   0.8790
  -1.250   0.0400   0.01164   0.00464  -0.0304   0.8556   0.9340
  -1.000   0.0852   0.01164   0.00448  -0.0336   0.8435   0.9701
  -0.750   0.1300   0.01162   0.00430  -0.0370   0.8308   0.9989
  -0.500   0.1534   0.01164   0.00417  -0.0361   0.8158   1.0000
  -0.250   0.1758   0.01168   0.00408  -0.0349   0.8010   1.0000
   0.000   0.1985   0.01173   0.00402  -0.0338   0.7864   1.0000
   0.250   0.2217   0.01179   0.00398  -0.0327   0.7718   1.0000
   0.500   0.2452   0.01185   0.00395  -0.0317   0.7573   1.0000
   0.750   0.2687   0.01193   0.00393  -0.0307   0.7425   1.0000
   1.000   0.2924   0.01201   0.00394  -0.0297   0.7275   1.0000
   1.250   0.3163   0.01210   0.00395  -0.0288   0.7123   1.0000
   1.500   0.3403   0.01219   0.00400  -0.0278   0.6967   1.0000
   1.750   0.3644   0.01229   0.00403  -0.0269   0.6809   1.0000
   2.000   0.3886   0.01240   0.00408  -0.0259   0.6646   1.0000
   2.250   0.4130   0.01252   0.00417  -0.0251   0.6467   1.0000
   2.500   0.4374   0.01264   0.00426  -0.0242   0.6287   1.0000
   2.750   0.4617   0.01278   0.00438  -0.0233   0.6106   1.0000
   3.000   0.4862   0.01294   0.00452  -0.0225   0.5908   1.0000
   3.250   0.5106   0.01310   0.00466  -0.0217   0.5709   1.0000
   3.500   0.5351   0.01329   0.00486  -0.0209   0.5502   1.0000
   3.750   0.5595   0.01350   0.00504  -0.0201   0.5289   1.0000
   4.000   0.5839   0.01373   0.00526  -0.0193   0.5066   1.0000
   4.250   0.6080   0.01399   0.00549  -0.0185   0.4841   1.0000
   4.500   0.6322   0.01427   0.00576  -0.0177   0.4601   1.0000
   4.750   0.6562   0.01458   0.00611  -0.0169   0.4353   1.0000
   5.000   0.6800   0.01492   0.00644  -0.0162   0.4095   1.0000
   5.250   0.7036   0.01530   0.00681  -0.0154   0.3825   1.0000
   5.500   0.7268   0.01572   0.00721  -0.0146   0.3542   1.0000
   5.750   0.7497   0.01618   0.00765  -0.0138   0.3244   1.0000
   6.000   0.7722   0.01670   0.00819  -0.0130   0.2934   1.0000
   6.250   0.7943   0.01728   0.00874  -0.0122   0.2607   1.0000
   6.500   0.8157   0.01795   0.00935  -0.0114   0.2268   1.0000
   6.750   0.8366   0.01870   0.01003  -0.0105   0.1929   1.0000
   7.000   0.8568   0.01955   0.01080  -0.0097   0.1598   1.0000
   7.250   0.8762   0.02051   0.01167  -0.0087   0.1293   1.0000
   7.500   0.8949   0.02156   0.01265  -0.0078   0.1008   1.0000
   7.750   0.9124   0.02275   0.01378  -0.0067   0.0791   1.0000
   8.000   0.9290   0.02405   0.01513  -0.0054   0.0627   1.0000
   8.250   0.9444   0.02542   0.01652  -0.0041   0.0514   1.0000
   8.500   0.9595   0.02681   0.01805  -0.0026   0.0443   1.0000
   8.750   0.9725   0.02840   0.01974  -0.0010   0.0387   1.0000
   9.000   0.9867   0.02976   0.02124   0.0004   0.0334   1.0000
   9.250   0.9950   0.03185   0.02334   0.0023   0.0305   1.0000
   9.500   1.0083   0.03365   0.02541   0.0040   0.0283   1.0000
   9.750   1.0198   0.03542   0.02740   0.0055   0.0253   1.0000
  10.000   1.0278   0.03708   0.02916   0.0070   0.0227   1.0000
  10.250   1.0315   0.03980   0.03199   0.0089   0.0211   1.0000
  10.500   1.0358   0.04235   0.03483   0.0109   0.0201   1.0000
  10.750   1.0365   0.04494   0.03773   0.0128   0.0191   1.0000
  11.000   1.0339   0.04749   0.04062   0.0142   0.0178   1.0000
  11.250   1.0291   0.05046   0.04385   0.0151   0.0170   1.0000
  11.500   1.0230   0.05347   0.04707   0.0152   0.0161   1.0000
  11.750   1.0153   0.05690   0.05068   0.0147   0.0154   1.0000
  12.000   1.0057   0.06098   0.05497   0.0136   0.0151   1.0000
  12.250   0.9934   0.06572   0.05989   0.0117   0.0148   1.0000
  12.500   0.9789   0.07128   0.06567   0.0090   0.0148   1.0000
  12.750   0.9625   0.07760   0.07219   0.0053   0.0149   1.0000
  13.000   0.9423   0.08522   0.08001   0.0005   0.0149   1.0000
  13.250   0.9123   0.09603   0.09106  -0.0064   0.0160   1.0000
  13.500   0.8758   0.10974   0.10486  -0.0148   0.0179   1.0000
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