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MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH 70 11.08% (mh70-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.4 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh70-il-1000000.txt
Download as CSV file: xf-mh70-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3149   0.09533   0.09387  -0.0216   1.0000   0.0096
 -10.000  -0.3122   0.09142   0.08997  -0.0230   1.0000   0.0097
  -9.750  -0.3107   0.08719   0.08576  -0.0246   1.0000   0.0097
  -9.500  -0.3020   0.08185   0.08040  -0.0286   0.9596   0.0099
  -9.250  -0.2953   0.07652   0.07499  -0.0324   0.9293   0.0101
  -9.000  -0.2980   0.07196   0.07035  -0.0338   0.9025   0.0102
  -8.750  -0.3028   0.06711   0.06543  -0.0354   0.8839   0.0103
  -8.500  -0.3085   0.06211   0.06039  -0.0373   0.8690   0.0104
  -8.250  -0.3178   0.05658   0.05482  -0.0397   0.8559   0.0104
  -8.000  -0.3314   0.05065   0.04886  -0.0428   0.8434   0.0104
  -7.750  -0.3720   0.04071   0.03885  -0.0516   0.8301   0.0100
  -7.500  -0.3953   0.03094   0.02881  -0.0563   0.8204   0.0100
  -7.250  -0.4547   0.02326   0.01946  -0.0603   0.8297   0.0066
  -7.000  -0.4416   0.01929   0.01495  -0.0589   0.8204   0.0061
  -6.750  -0.4221   0.01665   0.01188  -0.0578   0.8122   0.0059
  -6.500  -0.3991   0.01511   0.01005  -0.0570   0.8041   0.0059
  -6.250  -0.3744   0.01401   0.00875  -0.0564   0.7967   0.0060
  -6.000  -0.3490   0.01321   0.00780  -0.0559   0.7891   0.0063
  -5.750  -0.3226   0.01266   0.00712  -0.0555   0.7820   0.0067
  -5.500  -0.2959   0.01220   0.00656  -0.0552   0.7745   0.0068
  -5.250  -0.2714   0.01119   0.00542  -0.0546   0.7678   0.0073
  -5.000  -0.2445   0.01078   0.00497  -0.0544   0.7606   0.0077
  -4.500  -0.1902   0.01006   0.00412  -0.0539   0.7470   0.0084
  -4.250  -0.1630   0.00973   0.00372  -0.0536   0.7399   0.0088
  -4.000  -0.1353   0.00946   0.00339  -0.0535   0.7332   0.0091
  -3.750  -0.1081   0.00904   0.00291  -0.0532   0.7261   0.0101
  -3.500  -0.0803   0.00885   0.00269  -0.0531   0.7193   0.0113
  -3.250  -0.0525   0.00857   0.00238  -0.0529   0.7119   0.0142
  -3.000  -0.0250   0.00824   0.00207  -0.0526   0.7049   0.0268
  -2.750   0.0026   0.00792   0.00186  -0.0525   0.6974   0.0538
  -2.500   0.0298   0.00764   0.00169  -0.0524   0.6901   0.0961
  -2.250   0.0573   0.00730   0.00156  -0.0523   0.6824   0.1554
  -2.000   0.0844   0.00702   0.00145  -0.0522   0.6746   0.2185
  -1.750   0.1120   0.00675   0.00138  -0.0522   0.6665   0.2799
  -1.500   0.1394   0.00655   0.00131  -0.0521   0.6583   0.3391
  -1.250   0.1672   0.00637   0.00126  -0.0520   0.6495   0.3910
  -1.000   0.1944   0.00615   0.00122  -0.0519   0.6407   0.4626
  -0.750   0.2216   0.00595   0.00119  -0.0517   0.6312   0.5324
  -0.500   0.2488   0.00577   0.00118  -0.0515   0.6216   0.6005
  -0.250   0.2753   0.00558   0.00117  -0.0512   0.6114   0.6769
   0.000   0.3014   0.00539   0.00118  -0.0507   0.6005   0.7532
   0.250   0.3268   0.00525   0.00121  -0.0499   0.5895   0.8237
   0.500   0.3515   0.00517   0.00125  -0.0489   0.5782   0.8820
   1.000   0.4069   0.00520   0.00130  -0.0482   0.5526   0.9596
   1.250   0.4435   0.00528   0.00131  -0.0499   0.5382   0.9775
   1.500   0.4819   0.00538   0.00133  -0.0521   0.5224   0.9884
   1.750   0.5200   0.00549   0.00135  -0.0543   0.5063   0.9957
   2.000   0.5556   0.00560   0.00139  -0.0560   0.4904   1.0000
   2.250   0.5806   0.00573   0.00144  -0.0554   0.4753   1.0000
   2.500   0.6058   0.00586   0.00150  -0.0548   0.4602   1.0000
   2.750   0.6312   0.00601   0.00157  -0.0543   0.4449   1.0000
   3.000   0.6566   0.00616   0.00165  -0.0538   0.4294   1.0000
   3.250   0.6823   0.00632   0.00174  -0.0534   0.4143   1.0000
   3.500   0.7081   0.00649   0.00184  -0.0529   0.3982   1.0000
   3.750   0.7340   0.00667   0.00194  -0.0526   0.3821   1.0000
   4.250   0.7860   0.00706   0.00219  -0.0519   0.3497   1.0000
   4.500   0.8121   0.00726   0.00233  -0.0516   0.3347   1.0000
   4.750   0.8382   0.00747   0.00248  -0.0513   0.3191   1.0000
   5.000   0.8642   0.00769   0.00263  -0.0510   0.3036   1.0000
   5.250   0.8902   0.00792   0.00280  -0.0508   0.2892   1.0000
   5.500   0.9161   0.00816   0.00298  -0.0505   0.2741   1.0000
   6.000   0.9679   0.00864   0.00336  -0.0499   0.2476   1.0000
   6.250   0.9936   0.00889   0.00356  -0.0497   0.2346   1.0000
   6.500   1.0193   0.00914   0.00377  -0.0494   0.2230   1.0000
   6.750   1.0447   0.00942   0.00400  -0.0491   0.2109   1.0000
   7.000   1.0699   0.00971   0.00425  -0.0487   0.1997   1.0000
   7.250   1.0950   0.01000   0.00450  -0.0484   0.1887   1.0000
   7.500   1.1203   0.01026   0.00474  -0.0481   0.1794   1.0000
   7.750   1.1450   0.01057   0.00502  -0.0477   0.1696   1.0000
   8.000   1.1693   0.01091   0.00532  -0.0473   0.1594   1.0000
   8.250   1.1941   0.01120   0.00559  -0.0469   0.1511   1.0000
   8.500   1.2181   0.01154   0.00592  -0.0465   0.1426   1.0000
   8.750   1.2418   0.01189   0.00624  -0.0460   0.1341   1.0000
   9.000   1.2657   0.01222   0.00657  -0.0455   0.1267   1.0000
   9.250   1.2882   0.01264   0.00695  -0.0449   0.1179   1.0000
   9.500   1.3116   0.01298   0.00729  -0.0443   0.1113   1.0000
   9.750   1.3337   0.01340   0.00770  -0.0436   0.1038   1.0000
  10.000   1.3557   0.01381   0.00810  -0.0429   0.0972   1.0000
  10.250   1.3771   0.01424   0.00853  -0.0422   0.0910   1.0000
  10.500   1.3974   0.01472   0.00899  -0.0412   0.0842   1.0000
  10.750   1.4177   0.01518   0.00946  -0.0403   0.0782   1.0000
  11.000   1.4356   0.01577   0.01001  -0.0391   0.0709   1.0000
  11.250   1.4546   0.01624   0.01050  -0.0380   0.0661   1.0000
  11.500   1.4703   0.01688   0.01113  -0.0365   0.0601   1.0000
  11.750   1.4853   0.01739   0.01167  -0.0347   0.0561   1.0000
  12.000   1.4947   0.01811   0.01237  -0.0322   0.0511   1.0000
  12.250   1.5066   0.01871   0.01301  -0.0302   0.0476   1.0000
  12.500   1.5146   0.01958   0.01387  -0.0279   0.0434   1.0000
  12.750   1.5251   0.02037   0.01470  -0.0260   0.0399   1.0000
  13.250   1.5419   0.02238   0.01676  -0.0225   0.0337   1.0000
  13.500   1.5486   0.02360   0.01800  -0.0209   0.0309   1.0000
  13.750   1.5556   0.02487   0.01930  -0.0194   0.0278   1.0000
  14.000   1.5625   0.02622   0.02070  -0.0182   0.0262   1.0000
  14.250   1.5666   0.02785   0.02236  -0.0169   0.0238   1.0000
  14.500   1.5730   0.02936   0.02393  -0.0159   0.0219   1.0000
  14.750   1.5756   0.03128   0.02588  -0.0150   0.0201   1.0000
  15.000   1.5799   0.03311   0.02778  -0.0142   0.0186   1.0000
  15.250   1.5829   0.03515   0.02988  -0.0136   0.0174   1.0000
  15.500   1.5835   0.03749   0.03229  -0.0132   0.0164   1.0000
  15.750   1.5839   0.03993   0.03481  -0.0129   0.0154   1.0000
  16.000   1.5849   0.04242   0.03738  -0.0128   0.0146   1.0000
  16.250   1.5831   0.04529   0.04033  -0.0128   0.0138   1.0000
  16.500   1.5790   0.04855   0.04366  -0.0131   0.0130   1.0000
  16.750   1.5748   0.05200   0.04720  -0.0137   0.0124   1.0000
  17.000   1.5720   0.05540   0.05070  -0.0144   0.0119   1.0000
  17.250   1.5668   0.05925   0.05467  -0.0154   0.0114   1.0000
  17.500   1.5587   0.06366   0.05916  -0.0168   0.0106   1.0000
  17.750   1.5501   0.06830   0.06391  -0.0184   0.0104   1.0000
  18.000   1.5376   0.07368   0.06940  -0.0205   0.0099   1.0000
  18.250   1.5276   0.07885   0.07469  -0.0226   0.0097   1.0000
  18.500   1.5167   0.08429   0.08024  -0.0249   0.0094   1.0000
  18.750   1.5033   0.09029   0.08636  -0.0276   0.0091   1.0000
  19.000   1.4887   0.09665   0.09285  -0.0306   0.0088   1.0000
  19.250   1.4728   0.10338   0.09970  -0.0339   0.0087   1.0000
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