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MH 80 12.72% (mh80-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 80 12.72% (mh80-il)
Reynolds number: 50,000
Max Cl/Cd: 22.65 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh80-il-50000-n5.txt
Download as CSV file: xf-mh80-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 80  12.72%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4718   0.09657   0.09069   0.0063   1.0000   0.0444
  -8.750  -0.4718   0.09168   0.08587   0.0032   1.0000   0.0435
  -8.500  -0.4743   0.08617   0.08045  -0.0010   1.0000   0.0426
  -8.250  -0.4843   0.07913   0.07348  -0.0074   1.0000   0.0413
  -8.000  -0.5112   0.07070   0.06487  -0.0132   1.0000   0.0394
  -7.750  -0.5118   0.06645   0.06056  -0.0147   1.0000   0.0391
  -7.500  -0.5112   0.06213   0.05613  -0.0159   1.0000   0.0389
  -7.250  -0.5080   0.05788   0.05170  -0.0168   1.0000   0.0386
  -7.000  -0.5025   0.05361   0.04718  -0.0175   1.0000   0.0385
  -6.750  -0.4934   0.04964   0.04291  -0.0179   1.0000   0.0384
  -6.500  -0.4824   0.04573   0.03857  -0.0181   1.0000   0.0389
  -6.250  -0.4546   0.04190   0.03415  -0.0204   0.9208   0.0399
  -6.000  -0.4287   0.03983   0.03185  -0.0210   0.8795   0.0418
  -5.750  -0.4091   0.03765   0.02920  -0.0198   0.8479   0.0433
  -5.500  -0.3897   0.03553   0.02657  -0.0181   0.8208   0.0446
  -5.250  -0.3690   0.03354   0.02403  -0.0161   0.7978   0.0458
  -5.000  -0.3469   0.03189   0.02210  -0.0146   0.7755   0.0476
  -4.750  -0.3246   0.03069   0.02070  -0.0132   0.7548   0.0510
  -4.500  -0.3005   0.02938   0.01907  -0.0117   0.7359   0.0553
  -4.250  -0.2767   0.02825   0.01781  -0.0104   0.7178   0.0600
  -4.000  -0.2521   0.02719   0.01660  -0.0092   0.7006   0.0674
  -3.750  -0.2271   0.02619   0.01549  -0.0081   0.6840   0.0789
  -3.500  -0.2017   0.02523   0.01441  -0.0071   0.6680   0.0996
  -3.250  -0.1773   0.02406   0.01349  -0.0063   0.6528   0.1449
  -3.000  -0.1558   0.02278   0.01273  -0.0053   0.6386   0.2406
  -2.750  -0.1387   0.02157   0.01227  -0.0035   0.6256   0.3844
  -2.500  -0.1219   0.02031   0.01223   0.0003   0.6134   0.6274
  -2.250  -0.0649   0.02053   0.01260  -0.0007   0.5965   0.8460
  -2.000  -0.0202   0.02090   0.01253  -0.0021   0.5811   0.9127
  -1.750   0.0395   0.02106   0.01218  -0.0070   0.5647   0.9576
  -1.500   0.1120   0.02089   0.01148  -0.0151   0.5476   0.9947
  -1.250   0.1423   0.02088   0.01117  -0.0160   0.5354   1.0000
  -1.000   0.1639   0.02093   0.01092  -0.0151   0.5255   1.0000
  -0.750   0.1866   0.02105   0.01084  -0.0145   0.5143   1.0000
  -0.500   0.2091   0.02120   0.01078  -0.0138   0.5046   1.0000
  -0.250   0.2315   0.02135   0.01070  -0.0129   0.4952   1.0000
   0.000   0.2546   0.02158   0.01077  -0.0123   0.4853   1.0000
   0.250   0.2770   0.02176   0.01073  -0.0114   0.4773   1.0000
   0.500   0.3005   0.02207   0.01093  -0.0109   0.4677   1.0000
   0.750   0.3230   0.02229   0.01094  -0.0099   0.4604   1.0000
   1.000   0.3463   0.02267   0.01124  -0.0095   0.4514   1.0000
   1.250   0.3690   0.02294   0.01133  -0.0086   0.4444   1.0000
   1.500   0.3922   0.02337   0.01170  -0.0080   0.4364   1.0000
   1.750   0.4150   0.02372   0.01192  -0.0072   0.4293   1.0000
   2.000   0.4378   0.02413   0.01223  -0.0065   0.4227   1.0000
   2.250   0.4606   0.02462   0.01268  -0.0059   0.4151   1.0000
   2.500   0.4833   0.02495   0.01284  -0.0049   0.4100   1.0000
   2.750   0.5058   0.02563   0.01357  -0.0046   0.4024   1.0000
   3.000   0.5284   0.02608   0.01395  -0.0038   0.3964   1.0000
   3.250   0.5509   0.02653   0.01430  -0.0029   0.3913   1.0000
   3.500   0.5726   0.02735   0.01520  -0.0026   0.3843   1.0000
   3.750   0.5949   0.02783   0.01562  -0.0017   0.3792   1.0000
   4.000   0.6169   0.02845   0.01620  -0.0010   0.3741   1.0000
   4.250   0.6373   0.02939   0.01723  -0.0006   0.3675   1.0000
   4.500   0.6594   0.02991   0.01770   0.0003   0.3629   1.0000
   4.750   0.6811   0.03058   0.01835   0.0010   0.3585   1.0000
   5.000   0.6993   0.03186   0.01979   0.0013   0.3521   1.0000
   5.250   0.7208   0.03251   0.02042   0.0021   0.3475   1.0000
   5.500   0.7444   0.03287   0.02067   0.0031   0.3441   1.0000
   5.750   0.7578   0.03480   0.02290   0.0031   0.3373   1.0000
   6.000   0.7769   0.03581   0.02396   0.0038   0.3327   1.0000
   6.250   0.8000   0.03625   0.02435   0.0046   0.3292   1.0000
   6.500   0.8113   0.03830   0.02659   0.0048   0.3234   1.0000
   6.750   0.8240   0.04005   0.02850   0.0052   0.3181   1.0000
   7.000   0.8447   0.04081   0.02927   0.0059   0.3146   1.0000
   7.250   0.8658   0.04157   0.03002   0.0067   0.3114   1.0000
   7.500   0.8504   0.04639   0.03519   0.0061   0.3036   1.0000
   7.750   0.8657   0.04764   0.03650   0.0067   0.2997   1.0000
   8.000   0.8916   0.04779   0.03664   0.0077   0.2971   1.0000
   8.250   0.7951   0.06143   0.05052   0.0028   0.2853   1.0000
   8.500   0.8177   0.06161   0.05074   0.0041   0.2827   1.0000
   8.750   0.8506   0.06065   0.04980   0.0060   0.2810   1.0000
   9.750   0.7453   0.08887   0.07811  -0.0064   0.2537   1.0000
  10.000   0.7636   0.09000   0.07928  -0.0058   0.2513   1.0000
  10.250   0.7383   0.09725   0.08656  -0.0093   0.2456   1.0000
  10.500   0.7372   0.10104   0.09039  -0.0105   0.2409   1.0000
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