Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MH 24 9.01% (mh24-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70.37 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh24-il-1000000-n5.txt
Download as CSV file: xf-mh24-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 24  9.01%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4849   0.10773   0.10606  -0.0272   1.0000   0.0039
 -10.750  -0.4832   0.10499   0.10333  -0.0282   1.0000   0.0042
 -10.500  -0.4828   0.10132   0.09968  -0.0294   1.0000   0.0043
 -10.250  -0.4837   0.09738   0.09575  -0.0307   1.0000   0.0043
 -10.000  -0.4820   0.09463   0.09302  -0.0315   1.0000   0.0046
  -9.500  -0.4800   0.08602   0.08444  -0.0366   0.9920   0.0048
  -9.250  -0.4767   0.08077   0.07919  -0.0412   0.9892   0.0049
  -9.000  -0.4731   0.07488   0.07332  -0.0477   0.9865   0.0050
  -8.750  -0.4719   0.06655   0.06496  -0.0599   0.9834   0.0050
  -8.500  -0.4739   0.06006   0.05837  -0.0658   0.9771   0.0049
  -8.250  -0.4752   0.05409   0.05226  -0.0685   0.9708   0.0049
  -8.000  -0.4742   0.04995   0.04799  -0.0686   0.9656   0.0050
  -7.750  -0.4712   0.04642   0.04432  -0.0675   0.9608   0.0053
  -7.500  -0.4684   0.04240   0.04012  -0.0659   0.9565   0.0054
  -7.250  -0.4619   0.03905   0.03659  -0.0640   0.9529   0.0057
  -7.000  -0.4554   0.03545   0.03278  -0.0616   0.9494   0.0058
  -6.750  -0.4457   0.03231   0.02941  -0.0593   0.9461   0.0060
  -6.500  -0.4351   0.02919   0.02603  -0.0567   0.9434   0.0061
  -6.250  -0.4216   0.02657   0.02316  -0.0545   0.9408   0.0062
  -6.000  -0.4083   0.02375   0.02004  -0.0520   0.9377   0.0061
  -5.500  -0.3767   0.01665   0.01206  -0.0461   0.9321   0.0034
  -5.250  -0.3552   0.01496   0.01012  -0.0448   0.9302   0.0033
  -5.000  -0.3325   0.01340   0.00832  -0.0436   0.9281   0.0032
  -4.750  -0.3092   0.01229   0.00707  -0.0426   0.9254   0.0031
  -4.500  -0.2861   0.01134   0.00600  -0.0415   0.9224   0.0030
  -4.250  -0.2633   0.01050   0.00505  -0.0403   0.9195   0.0029
  -4.000  -0.2399   0.00987   0.00432  -0.0393   0.9170   0.0029
  -3.750  -0.2161   0.00934   0.00370  -0.0384   0.9142   0.0029
  -3.500  -0.1917   0.00890   0.00319  -0.0377   0.9108   0.0028
  -3.250  -0.1667   0.00856   0.00278  -0.0370   0.9073   0.0028
  -3.000  -0.1411   0.00828   0.00240  -0.0365   0.9040   0.0029
  -2.750  -0.1151   0.00807   0.00214  -0.0361   0.9006   0.0029
  -2.500  -0.0890   0.00788   0.00191  -0.0357   0.8964   0.0031
  -2.250  -0.0626   0.00772   0.00171  -0.0354   0.8921   0.0035
  -2.000  -0.0378   0.00737   0.00151  -0.0348   0.8879   0.0469
  -1.750  -0.0140   0.00695   0.00138  -0.0341   0.8820   0.1258
  -1.500   0.0054   0.00612   0.00119  -0.0328   0.8762   0.3192
  -1.250   0.0239   0.00537   0.00107  -0.0313   0.8685   0.5053
  -1.000   0.0464   0.00500   0.00097  -0.0302   0.8601   0.5942
  -0.750   0.0669   0.00457   0.00086  -0.0287   0.8489   0.6981
  -0.500   0.0872   0.00421   0.00082  -0.0270   0.8339   0.7945
  -0.250   0.1106   0.00414   0.00083  -0.0258   0.8122   0.8518
   0.000   0.1350   0.00421   0.00083  -0.0249   0.7838   0.8771
   0.250   0.1587   0.00435   0.00087  -0.0238   0.7508   0.8946
   0.500   0.1821   0.00453   0.00092  -0.0228   0.7146   0.9054
   0.750   0.2053   0.00474   0.00098  -0.0218   0.6758   0.9131
   1.000   0.2290   0.00494   0.00104  -0.0209   0.6381   0.9184
   1.250   0.2523   0.00515   0.00111  -0.0200   0.6005   0.9240
   1.500   0.2753   0.00537   0.00119  -0.0190   0.5616   0.9302
   1.750   0.2978   0.00562   0.00131  -0.0178   0.5225   0.9371
   2.000   0.3199   0.00587   0.00142  -0.0166   0.4845   0.9437
   2.250   0.3436   0.00611   0.00153  -0.0158   0.4470   0.9477
   2.500   0.3673   0.00634   0.00163  -0.0151   0.4108   0.9510
   2.750   0.3905   0.00656   0.00172  -0.0143   0.3764   0.9542
   3.000   0.4146   0.00679   0.00181  -0.0137   0.3409   0.9564
   3.250   0.4394   0.00703   0.00195  -0.0132   0.3060   0.9582
   3.500   0.4644   0.00728   0.00208  -0.0129   0.2730   0.9600
   3.750   0.4890   0.00754   0.00222  -0.0124   0.2406   0.9621
   4.000   0.5133   0.00780   0.00236  -0.0119   0.2089   0.9644
   4.250   0.5368   0.00808   0.00252  -0.0113   0.1783   0.9668
   4.500   0.5600   0.00833   0.00270  -0.0105   0.1536   0.9692
   4.750   0.5861   0.00866   0.00290  -0.0105   0.1228   0.9707
   5.000   0.6117   0.00903   0.00314  -0.0104   0.0911   0.9724
   5.250   0.6380   0.00934   0.00337  -0.0104   0.0718   0.9740
   5.500   0.6639   0.00967   0.00362  -0.0104   0.0529   0.9758
   5.750   0.6883   0.01011   0.00392  -0.0101   0.0295   0.9779
   6.000   0.7131   0.01042   0.00423  -0.0097   0.0205   0.9801
   6.250   0.7381   0.01072   0.00452  -0.0095   0.0152   0.9821
   6.500   0.7671   0.01103   0.00482  -0.0101   0.0112   0.9830
   6.750   0.7956   0.01139   0.00517  -0.0107   0.0080   0.9840
   7.000   0.8240   0.01171   0.00552  -0.0112   0.0057   0.9850
   7.250   0.8507   0.01232   0.00609  -0.0114   0.0014   0.9861
   7.500   0.8782   0.01271   0.00655  -0.0118   0.0013   0.9872
   7.750   0.9051   0.01317   0.00708  -0.0120   0.0012   0.9885
   8.000   0.9311   0.01371   0.00770  -0.0120   0.0011   0.9900
   8.250   0.9562   0.01426   0.00839  -0.0119   0.0011   0.9917
   8.500   0.9803   0.01485   0.00907  -0.0117   0.0010   0.9935
   8.750   1.0051   0.01560   0.00994  -0.0116   0.0010   0.9950
   9.000   1.0295   0.01640   0.01087  -0.0116   0.0010   0.9967
   9.250   1.0525   0.01738   0.01200  -0.0113   0.0010   0.9987
   9.500   1.0712   0.01839   0.01315  -0.0101   0.0010   1.0000
   9.750   1.0771   0.01925   0.01415  -0.0062   0.0010   1.0000
  10.000   1.0854   0.02008   0.01510  -0.0029   0.0010   1.0000
  10.250   1.0925   0.02112   0.01629   0.0005   0.0010   1.0000
  10.500   1.0947   0.02245   0.01780   0.0047   0.0010   1.0000
  10.750   1.1000   0.02349   0.01898   0.0082   0.0010   1.0000
  11.000   1.0996   0.02515   0.02086   0.0123   0.0010   1.0000
  11.250   1.1027   0.02652   0.02242   0.0157   0.0010   1.0000
  11.500   1.0982   0.02860   0.02473   0.0197   0.0010   1.0000
  11.750   1.0987   0.03020   0.02650   0.0227   0.0010   1.0000
  12.000   1.0896   0.03268   0.02922   0.0264   0.0010   1.0000
  12.250   1.0786   0.03538   0.03215   0.0297   0.0010   1.0000
  12.500   1.0696   0.03801   0.03496   0.0321   0.0010   1.0000
  12.750   1.0507   0.04186   0.03905   0.0341   0.0010   1.0000
  13.000   1.0313   0.04626   0.04366   0.0346   0.0010   1.0000
  13.250   1.0173   0.05064   0.04820   0.0338   0.0010   1.0000
  13.500   1.0036   0.05569   0.05339   0.0317   0.0010   1.0000
  13.750   0.9817   0.06316   0.06104   0.0272   0.0010   1.0000
  14.000   0.9715   0.06949   0.06748   0.0230   0.0010   1.0000
  14.250   0.9409   0.08134   0.07950   0.0153   0.0010   1.0000
  14.500   0.9258   0.08983   0.08807   0.0104   0.0010   1.0000
  14.750   0.8963   0.10180   0.10014   0.0043   0.0010   1.0000
  15.000   0.8629   0.11473   0.11310  -0.0017   0.0010   1.0000
  15.250   0.8480   0.12301   0.12141  -0.0056   0.0010   1.0000
<< Back to MH 24 9.01% (mh24-il)

Polar data table (+)

Polar graphs


<< Back to MH 24 9.01% (mh24-il)