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MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 70 11.08% (mh70-il)
Reynolds number: 500,000
Max Cl/Cd: 95.05 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh70-il-500000.txt
Download as CSV file: xf-mh70-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 70  11.08%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3766   0.09219   0.09000  -0.0253   1.0000   0.0174
  -9.000  -0.3844   0.08489   0.08275  -0.0307   1.0000   0.0183
  -8.750  -0.3884   0.07907   0.07697  -0.0346   1.0000   0.0184
  -7.750  -0.3959   0.04970   0.04741  -0.0644   0.9477   0.0189
  -7.500  -0.3836   0.04722   0.04481  -0.0659   0.9229   0.0191
  -7.250  -0.3778   0.04424   0.04163  -0.0660   0.9024   0.0194
  -7.000  -0.3699   0.04132   0.03850  -0.0658   0.8869   0.0199
  -6.750  -0.3601   0.03806   0.03498  -0.0656   0.8741   0.0206
  -6.500  -0.3709   0.02412   0.01923  -0.0623   0.8618   0.0119
  -6.250  -0.3523   0.02105   0.01593  -0.0614   0.8525   0.0113
  -6.000  -0.3306   0.01882   0.01331  -0.0604   0.8440   0.0112
  -5.750  -0.3069   0.01723   0.01137  -0.0595   0.8357   0.0114
  -5.500  -0.2818   0.01606   0.00996  -0.0588   0.8277   0.0116
  -5.250  -0.2567   0.01499   0.00868  -0.0581   0.8200   0.0119
  -5.000  -0.2320   0.01391   0.00754  -0.0575   0.8123   0.0124
  -4.750  -0.2062   0.01326   0.00681  -0.0570   0.8047   0.0129
  -4.500  -0.1796   0.01286   0.00634  -0.0567   0.7974   0.0140
  -4.250  -0.1528   0.01246   0.00584  -0.0563   0.7898   0.0148
  -4.000  -0.1275   0.01167   0.00501  -0.0557   0.7829   0.0158
  -3.750  -0.1008   0.01120   0.00449  -0.0554   0.7752   0.0173
  -3.500  -0.0742   0.01072   0.00392  -0.0549   0.7685   0.0194
  -3.250  -0.0470   0.01026   0.00345  -0.0546   0.7606   0.0258
  -3.000  -0.0207   0.00969   0.00297  -0.0542   0.7539   0.0563
  -2.750   0.0054   0.00908   0.00272  -0.0540   0.7460   0.1378
  -2.500   0.0318   0.00869   0.00255  -0.0538   0.7388   0.2122
  -2.250   0.0586   0.00834   0.00243  -0.0537   0.7309   0.2839
  -2.000   0.0853   0.00805   0.00232  -0.0534   0.7234   0.3559
  -1.750   0.1123   0.00778   0.00224  -0.0532   0.7153   0.4210
  -1.500   0.1386   0.00752   0.00216  -0.0529   0.7075   0.4967
  -1.250   0.1644   0.00718   0.00212  -0.0524   0.6991   0.5909
  -1.000   0.1896   0.00691   0.00208  -0.0516   0.6911   0.6784
  -0.750   0.2141   0.00663   0.00209  -0.0506   0.6821   0.7670
  -0.500   0.2376   0.00647   0.00209  -0.0491   0.6738   0.8450
  -0.250   0.2627   0.00637   0.00210  -0.0479   0.6642   0.9069
   0.000   0.2957   0.00637   0.00208  -0.0485   0.6547   0.9484
   0.250   0.3351   0.00641   0.00202  -0.0507   0.6442   0.9727
   0.500   0.3784   0.00644   0.00198  -0.0538   0.6325   0.9867
   0.750   0.4221   0.00647   0.00192  -0.0571   0.6204   0.9970
   1.000   0.4534   0.00652   0.00189  -0.0578   0.6087   1.0000
   1.500   0.5027   0.00667   0.00189  -0.0564   0.5842   1.0000
   1.750   0.5277   0.00676   0.00190  -0.0558   0.5709   1.0000
   2.000   0.5528   0.00686   0.00194  -0.0552   0.5572   1.0000
   2.250   0.5780   0.00698   0.00198  -0.0546   0.5433   1.0000
   2.500   0.6033   0.00710   0.00203  -0.0540   0.5286   1.0000
   2.750   0.6287   0.00724   0.00210  -0.0535   0.5135   1.0000
   3.000   0.6543   0.00740   0.00218  -0.0530   0.4980   1.0000
   3.250   0.6800   0.00756   0.00227  -0.0526   0.4821   1.0000
   3.500   0.7057   0.00773   0.00238  -0.0521   0.4661   1.0000
   3.750   0.7314   0.00792   0.00249  -0.0517   0.4494   1.0000
   4.000   0.7572   0.00812   0.00263  -0.0514   0.4332   1.0000
   4.250   0.7829   0.00833   0.00278  -0.0510   0.4162   1.0000
   4.500   0.8085   0.00856   0.00293  -0.0506   0.3992   1.0000
   4.750   0.8340   0.00881   0.00311  -0.0502   0.3822   1.0000
   5.000   0.8594   0.00906   0.00330  -0.0498   0.3651   1.0000
   5.250   0.8849   0.00931   0.00349  -0.0495   0.3487   1.0000
   5.500   0.9103   0.00958   0.00371  -0.0491   0.3321   1.0000
   5.750   0.9354   0.00987   0.00394  -0.0487   0.3155   1.0000
   6.000   0.9604   0.01016   0.00418  -0.0483   0.2999   1.0000
   6.250   0.9853   0.01047   0.00444  -0.0479   0.2844   1.0000
   6.500   1.0100   0.01079   0.00472  -0.0475   0.2699   1.0000
   6.750   1.0344   0.01113   0.00501  -0.0471   0.2559   1.0000
   7.000   1.0587   0.01148   0.00532  -0.0466   0.2425   1.0000
   7.250   1.0825   0.01185   0.00564  -0.0461   0.2296   1.0000
   7.500   1.1065   0.01221   0.00597  -0.0456   0.2172   1.0000
   7.750   1.1305   0.01256   0.00632  -0.0451   0.2058   1.0000
   8.000   1.1539   0.01294   0.00668  -0.0446   0.1949   1.0000
   8.250   1.1767   0.01336   0.00708  -0.0440   0.1847   1.0000
   8.500   1.1993   0.01378   0.00747  -0.0433   0.1745   1.0000
   8.750   1.2222   0.01416   0.00788  -0.0427   0.1651   1.0000
   9.000   1.2438   0.01463   0.00833  -0.0420   0.1561   1.0000
   9.250   1.2652   0.01509   0.00878  -0.0412   0.1472   1.0000
   9.500   1.2866   0.01553   0.00925  -0.0404   0.1392   1.0000
   9.750   1.3057   0.01611   0.00980  -0.0393   0.1309   1.0000
  10.000   1.3267   0.01653   0.01026  -0.0385   0.1234   1.0000
  10.250   1.3448   0.01711   0.01085  -0.0373   0.1161   1.0000
  10.500   1.3630   0.01765   0.01140  -0.0361   0.1088   1.0000
  10.750   1.3798   0.01824   0.01202  -0.0348   0.1022   1.0000
  11.000   1.3935   0.01886   0.01265  -0.0329   0.0960   1.0000
  11.250   1.4056   0.01952   0.01334  -0.0309   0.0904   1.0000
  11.500   1.4168   0.02025   0.01409  -0.0289   0.0846   1.0000
  11.750   1.4271   0.02108   0.01496  -0.0269   0.0793   1.0000
  12.000   1.4374   0.02196   0.01586  -0.0252   0.0739   1.0000
  12.250   1.4455   0.02303   0.01697  -0.0234   0.0690   1.0000
  12.500   1.4554   0.02406   0.01804  -0.0219   0.0644   1.0000
  12.750   1.4601   0.02550   0.01950  -0.0203   0.0600   1.0000
  13.000   1.4701   0.02663   0.02072  -0.0191   0.0562   1.0000
  13.250   1.4742   0.02828   0.02239  -0.0178   0.0523   1.0000
  13.500   1.4803   0.02984   0.02403  -0.0168   0.0492   1.0000
  13.750   1.4854   0.03155   0.02579  -0.0158   0.0460   1.0000
  14.000   1.4838   0.03394   0.02822  -0.0149   0.0431   1.0000
  14.250   1.4900   0.03570   0.03009  -0.0143   0.0408   1.0000
  14.500   1.4922   0.03791   0.03237  -0.0138   0.0384   1.0000
  14.750   1.4882   0.04083   0.03534  -0.0135   0.0363   1.0000
  15.000   1.4876   0.04354   0.03816  -0.0134   0.0345   1.0000
  15.250   1.4882   0.04620   0.04093  -0.0134   0.0328   1.0000
  15.500   1.4843   0.04947   0.04428  -0.0138   0.0311   1.0000
  15.750   1.4746   0.05362   0.04850  -0.0145   0.0298   1.0000
  16.000   1.4701   0.05731   0.05232  -0.0153   0.0286   1.0000
  16.250   1.4677   0.06088   0.05602  -0.0163   0.0273   1.0000
  16.500   1.4615   0.06509   0.06033  -0.0176   0.0262   1.0000
  16.750   1.4522   0.06990   0.06521  -0.0193   0.0251   1.0000
  17.000   1.4370   0.07580   0.07121  -0.0216   0.0242   1.0000
  17.250   1.4276   0.08093   0.07647  -0.0236   0.0236   1.0000
  17.500   1.4201   0.08592   0.08160  -0.0257   0.0227   1.0000
  17.750   1.4112   0.09126   0.08706  -0.0281   0.0220   1.0000
  18.000   1.4002   0.09707   0.09297  -0.0308   0.0211   1.0000
  18.250   1.3862   0.10350   0.09950  -0.0339   0.0206   1.0000
  18.500   1.3714   0.11020   0.10629  -0.0373   0.0201   1.0000
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