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MH 44 9.66% (mh44-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 44 9.66% (mh44-il)
Reynolds number: 100,000
Max Cl/Cd: 44.91 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh44-il-100000.txt
Download as CSV file: xf-mh44-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 44  9.66%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5170   0.10340   0.09874  -0.0007   1.0000   0.1080
  -9.000  -0.5220   0.09980   0.09521  -0.0039   1.0000   0.1137
  -8.750  -0.5621   0.09592   0.09154  -0.0151   1.0000   0.1157
  -8.500  -0.5189   0.09169   0.08721  -0.0068   1.0000   0.1199
  -8.250  -0.5164   0.08825   0.08381  -0.0081   1.0000   0.1248
  -8.000  -0.5754   0.08334   0.07897  -0.0225   1.0000   0.1296
  -7.750  -0.5320   0.07984   0.07557  -0.0141   1.0000   0.1330
  -7.500  -0.5286   0.07628   0.07205  -0.0153   1.0000   0.1380
  -7.250  -0.5405   0.07124   0.06701  -0.0205   1.0000   0.1457
  -7.000  -0.5292   0.06782   0.06361  -0.0200   1.0000   0.1499
  -6.750  -0.5265   0.03767   0.03265  -0.0317   1.0000   0.0748
  -6.500  -0.5497   0.04298   0.03719  -0.0298   1.0000   0.0588
  -6.250  -0.5405   0.03814   0.03146  -0.0273   1.0000   0.0491
  -6.000  -0.5288   0.03450   0.02753  -0.0254   1.0000   0.0470
  -5.750  -0.5173   0.03150   0.02415  -0.0228   1.0000   0.0451
  -5.500  -0.5048   0.02895   0.02117  -0.0201   1.0000   0.0435
  -5.250  -0.4905   0.02678   0.01861  -0.0174   1.0000   0.0430
  -5.000  -0.4751   0.02519   0.01680  -0.0151   1.0000   0.0450
  -4.750  -0.4584   0.02382   0.01518  -0.0129   1.0000   0.0475
  -4.500  -0.4404   0.02262   0.01371  -0.0107   1.0000   0.0498
  -4.250  -0.4229   0.02061   0.01174  -0.0087   1.0000   0.0527
  -4.000  -0.4066   0.01938   0.01054  -0.0065   1.0000   0.0587
  -3.750  -0.3914   0.01827   0.00943  -0.0043   1.0000   0.0724
  -3.500  -0.3778   0.01660   0.00815  -0.0017   1.0000   0.1214
  -3.250  -0.3681   0.01492   0.00778   0.0010   1.0000   0.3548
  -3.000  -0.3531   0.01458   0.00770   0.0030   1.0000   0.4323
  -2.750  -0.3388   0.01422   0.00769   0.0054   1.0000   0.5195
  -2.500  -0.3238   0.01380   0.00769   0.0078   1.0000   0.6173
  -2.250  -0.2776   0.01330   0.00781   0.0055   0.9938   0.7965
  -2.000  -0.1296   0.01351   0.00776  -0.0162   1.0000   1.0000
  -1.750  -0.0949   0.01363   0.00758  -0.0191   0.9929   1.0000
  -1.500  -0.0380   0.01380   0.00748  -0.0257   0.9821   1.0000
  -1.250   0.0179   0.01389   0.00736  -0.0318   0.9709   1.0000
  -1.000   0.0735   0.01393   0.00722  -0.0377   0.9595   1.0000
  -0.750   0.1298   0.01390   0.00707  -0.0435   0.9482   1.0000
  -0.500   0.1809   0.01384   0.00689  -0.0481   0.9352   1.0000
  -0.250   0.2242   0.01377   0.00675  -0.0510   0.9203   1.0000
   0.000   0.2591   0.01374   0.00665  -0.0520   0.9036   1.0000
   0.250   0.2867   0.01374   0.00658  -0.0513   0.8865   1.0000
   0.500   0.3066   0.01385   0.00664  -0.0493   0.8666   1.0000
   0.750   0.3263   0.01392   0.00664  -0.0471   0.8481   1.0000
   1.000   0.3456   0.01396   0.00662  -0.0446   0.8307   1.0000
   1.250   0.3646   0.01404   0.00665  -0.0423   0.8115   1.0000
   1.500   0.3843   0.01407   0.00664  -0.0401   0.7928   1.0000
   1.750   0.4046   0.01407   0.00658  -0.0378   0.7751   1.0000
   2.000   0.4254   0.01408   0.00654  -0.0357   0.7562   1.0000
   2.250   0.4467   0.01409   0.00653  -0.0338   0.7364   1.0000
   2.500   0.4685   0.01407   0.00644  -0.0319   0.7179   1.0000
   2.750   0.4908   0.01413   0.00646  -0.0303   0.6970   1.0000
   3.000   0.5134   0.01418   0.00644  -0.0286   0.6767   1.0000
   3.250   0.5364   0.01429   0.00653  -0.0271   0.6550   1.0000
   3.500   0.5595   0.01441   0.00658  -0.0256   0.6334   1.0000
   3.750   0.5828   0.01460   0.00673  -0.0244   0.6100   1.0000
   4.000   0.6061   0.01479   0.00684  -0.0230   0.5875   1.0000
   4.250   0.6294   0.01502   0.00706  -0.0218   0.5631   1.0000
   4.500   0.6527   0.01528   0.00729  -0.0206   0.5379   1.0000
   4.750   0.6759   0.01557   0.00753  -0.0194   0.5125   1.0000
   5.000   0.6990   0.01589   0.00779  -0.0183   0.4867   1.0000
   5.250   0.7218   0.01625   0.00811  -0.0171   0.4600   1.0000
   5.500   0.7444   0.01665   0.00845  -0.0160   0.4325   1.0000
   5.750   0.7667   0.01708   0.00883  -0.0148   0.4041   1.0000
   6.000   0.7886   0.01756   0.00927  -0.0137   0.3747   1.0000
   6.250   0.8102   0.01809   0.00977  -0.0126   0.3455   1.0000
   6.500   0.8313   0.01869   0.01035  -0.0114   0.3161   1.0000
   6.750   0.8520   0.01937   0.01098  -0.0103   0.2876   1.0000
   7.000   0.8722   0.02012   0.01166  -0.0091   0.2597   1.0000
   7.250   0.8919   0.02097   0.01244  -0.0079   0.2333   1.0000
   7.500   0.9111   0.02193   0.01326  -0.0067   0.2084   1.0000
   7.750   0.9298   0.02293   0.01430  -0.0054   0.1843   1.0000
   8.000   0.9479   0.02407   0.01547  -0.0041   0.1625   1.0000
   8.250   0.9658   0.02526   0.01662  -0.0028   0.1430   1.0000
   8.500   0.9833   0.02669   0.01795  -0.0016   0.1258   1.0000
   8.750   1.0008   0.02822   0.01958  -0.0002   0.1109   1.0000
   9.000   1.0173   0.02978   0.02120   0.0012   0.0976   1.0000
   9.250   1.0354   0.03176   0.02312   0.0023   0.0869   1.0000
   9.500   1.0496   0.03321   0.02485   0.0039   0.0776   1.0000
   9.750   1.0659   0.03588   0.02774   0.0053   0.0714   1.0000
  10.000   1.0800   0.03807   0.03020   0.0068   0.0658   1.0000
  10.250   1.0918   0.04107   0.03334   0.0081   0.0612   1.0000
  10.500   1.0962   0.04373   0.03651   0.0104   0.0579   1.0000
  10.750   1.1002   0.04683   0.03995   0.0124   0.0555   1.0000
  11.000   1.1032   0.04979   0.04314   0.0142   0.0535   1.0000
  11.250   1.1054   0.05411   0.04751   0.0152   0.0510   1.0000
  11.500   1.0892   0.05730   0.05104   0.0180   0.0503   1.0000
  11.750   1.0697   0.06035   0.05437   0.0204   0.0500   1.0000
  12.000   1.0495   0.06407   0.05834   0.0214   0.0499   1.0000
  12.250   1.0279   0.06848   0.06297   0.0210   0.0499   1.0000
  12.500   1.0077   0.07361   0.06828   0.0195   0.0502   1.0000
  12.750   0.9853   0.07968   0.07449   0.0169   0.0505   1.0000
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