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MH 42 8.94% (mh42-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 42 8.94% (mh42-il)
Reynolds number: 100,000
Max Cl/Cd: 49.63 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh42-il-100000-n5.txt
Download as CSV file: xf-mh42-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 42  8.94%                                    
  
 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  -0.5079   0.09121   0.08645  -0.0097   1.0000   0.0143
  -8.750  -0.5085   0.08665   0.08195  -0.0122   1.0000   0.0141
  -8.500  -0.5094   0.08223   0.07758  -0.0148   1.0000   0.0139
  -8.250  -0.5135   0.07706   0.07249  -0.0183   1.0000   0.0138
  -8.000  -0.5193   0.07181   0.06731  -0.0226   1.0000   0.0135
  -7.750  -0.5233   0.06570   0.06120  -0.0277   1.0000   0.0133
  -7.500  -0.5255   0.05937   0.05478  -0.0317   1.0000   0.0131
  -7.250  -0.5249   0.05373   0.04897  -0.0341   1.0000   0.0128
  -7.000  -0.5223   0.04823   0.04320  -0.0357   1.0000   0.0126
  -6.750  -0.5162   0.04316   0.03775  -0.0362   1.0000   0.0125
  -6.500  -0.5063   0.03875   0.03289  -0.0361   1.0000   0.0127
  -6.250  -0.4931   0.03500   0.02864  -0.0354   1.0000   0.0134
  -6.000  -0.4770   0.03192   0.02497  -0.0343   1.0000   0.0145
  -5.750  -0.4592   0.02954   0.02210  -0.0330   1.0000   0.0152
  -5.500  -0.4429   0.02687   0.01904  -0.0315   1.0000   0.0163
  -5.250  -0.4261   0.02483   0.01677  -0.0300   1.0000   0.0171
  -5.000  -0.4087   0.02315   0.01489  -0.0283   1.0000   0.0182
  -4.750  -0.3917   0.02174   0.01331  -0.0265   1.0000   0.0195
  -4.500  -0.3561   0.02005   0.01137  -0.0281   0.9893   0.0223
  -4.250  -0.3203   0.01864   0.00986  -0.0300   0.9795   0.0304
  -4.000  -0.2845   0.01733   0.00844  -0.0318   0.9694   0.0437
  -3.750  -0.2512   0.01606   0.00727  -0.0331   0.9580   0.0791
  -3.500  -0.2183   0.01508   0.00657  -0.0344   0.9464   0.1532
  -3.250  -0.1865   0.01435   0.00617  -0.0356   0.9345   0.2409
  -3.000  -0.1563   0.01369   0.00584  -0.0363   0.9223   0.3362
  -2.750  -0.1279   0.01309   0.00558  -0.0364   0.9098   0.4408
  -2.500  -0.1010   0.01258   0.00536  -0.0358   0.8974   0.5511
  -2.250  -0.0750   0.01218   0.00524  -0.0347   0.8852   0.6566
  -2.000  -0.0487   0.01193   0.00515  -0.0334   0.8732   0.7493
  -1.750  -0.0183   0.01179   0.00506  -0.0328   0.8612   0.8281
  -1.500   0.0213   0.01172   0.00492  -0.0343   0.8500   0.8912
  -1.250   0.0659   0.01167   0.00470  -0.0371   0.8389   0.9380
  -1.000   0.1131   0.01163   0.00447  -0.0407   0.8277   0.9722
  -0.750   0.1604   0.01157   0.00423  -0.0446   0.8160   1.0000
  -0.500   0.1825   0.01160   0.00410  -0.0435   0.8022   1.0000
  -0.250   0.2053   0.01165   0.00402  -0.0425   0.7889   1.0000
   0.000   0.2285   0.01172   0.00395  -0.0415   0.7760   1.0000
   0.250   0.2518   0.01179   0.00391  -0.0406   0.7633   1.0000
   0.500   0.2754   0.01188   0.00389  -0.0396   0.7504   1.0000
   0.750   0.2992   0.01198   0.00390  -0.0388   0.7375   1.0000
   1.000   0.3232   0.01208   0.00393  -0.0379   0.7246   1.0000
   1.250   0.3474   0.01219   0.00397  -0.0371   0.7118   1.0000
   1.500   0.3717   0.01231   0.00404  -0.0363   0.6988   1.0000
   1.750   0.3963   0.01243   0.00411  -0.0355   0.6857   1.0000
   2.000   0.4209   0.01256   0.00419  -0.0348   0.6723   1.0000
   2.250   0.4458   0.01269   0.00429  -0.0340   0.6586   1.0000
   2.500   0.4707   0.01283   0.00440  -0.0333   0.6446   1.0000
   2.750   0.4957   0.01298   0.00457  -0.0326   0.6301   1.0000
   3.000   0.5207   0.01313   0.00471  -0.0319   0.6150   1.0000
   3.250   0.5457   0.01328   0.00485  -0.0312   0.5995   1.0000
   3.500   0.5708   0.01345   0.00503  -0.0306   0.5825   1.0000
   3.750   0.5958   0.01362   0.00527  -0.0299   0.5643   1.0000
   4.000   0.6207   0.01380   0.00545  -0.0292   0.5456   1.0000
   4.250   0.6455   0.01400   0.00568  -0.0285   0.5247   1.0000
   4.500   0.6701   0.01422   0.00590  -0.0278   0.5032   1.0000
   4.750   0.6947   0.01447   0.00622  -0.0271   0.4788   1.0000
   5.000   0.7189   0.01475   0.00652  -0.0263   0.4525   1.0000
   5.250   0.7427   0.01507   0.00684  -0.0256   0.4239   1.0000
   5.500   0.7661   0.01546   0.00719  -0.0248   0.3924   1.0000
   5.750   0.7891   0.01590   0.00761  -0.0240   0.3578   1.0000
   6.000   0.8114   0.01644   0.00809  -0.0232   0.3209   1.0000
   6.250   0.8330   0.01707   0.00863  -0.0223   0.2818   1.0000
   6.500   0.8540   0.01780   0.00934  -0.0215   0.2428   1.0000
   6.750   0.8743   0.01864   0.01007  -0.0206   0.2041   1.0000
   7.000   0.8941   0.01956   0.01089  -0.0197   0.1669   1.0000
   7.250   0.9131   0.02058   0.01181  -0.0188   0.1345   1.0000
   7.500   0.9316   0.02167   0.01282  -0.0179   0.1058   1.0000
   7.750   0.9489   0.02287   0.01394  -0.0168   0.0833   1.0000
   8.000   0.9661   0.02409   0.01519  -0.0156   0.0655   1.0000
   8.250   0.9813   0.02551   0.01666  -0.0142   0.0542   1.0000
   8.500   0.9957   0.02696   0.01815  -0.0128   0.0446   1.0000
   8.750   1.0092   0.02845   0.01981  -0.0114   0.0378   1.0000
   9.000   1.0207   0.03027   0.02178  -0.0095   0.0338   1.0000
   9.250   1.0335   0.03180   0.02348  -0.0080   0.0288   1.0000
   9.500   1.0414   0.03386   0.02559  -0.0063   0.0252   1.0000
   9.750   1.0528   0.03593   0.02794  -0.0046   0.0229   1.0000
  10.000   1.0607   0.03766   0.02985  -0.0030   0.0197   1.0000
  10.250   1.0627   0.03959   0.03187  -0.0010   0.0177   1.0000
  10.500   1.0633   0.04258   0.03503   0.0008   0.0165   1.0000
  10.750   1.0653   0.04541   0.03820   0.0024   0.0156   1.0000
  11.000   1.0639   0.04854   0.04163   0.0037   0.0151   1.0000
  11.250   1.0589   0.05194   0.04533   0.0045   0.0144   1.0000
  11.500   1.0517   0.05554   0.04919   0.0046   0.0140   1.0000
  11.750   1.0417   0.05966   0.05357   0.0041   0.0137   1.0000
  12.000   1.0305   0.06405   0.05819   0.0027   0.0132   1.0000
  12.250   1.0159   0.06941   0.06380   0.0005   0.0133   1.0000
  12.500   1.0005   0.07522   0.06982  -0.0025   0.0132   1.0000
  12.750   0.9812   0.08233   0.07713  -0.0066   0.0135   1.0000
  13.000   0.9620   0.09001   0.08499  -0.0116   0.0135   1.0000
  13.250   0.9386   0.09945   0.09460  -0.0177   0.0141   1.0000
  13.500   0.9191   0.10882   0.10407  -0.0236   0.0149   1.0000
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