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

MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 43 8.5% (mh43-il)
Reynolds number: 50,000
Max Cl/Cd: 33.44 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh43-il-50000.txt
Download as CSV file: xf-mh43-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 43  8.5%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5244   0.11739   0.11092   0.0084   1.0000   0.2028
  -9.000  -0.5071   0.11208   0.10561   0.0090   1.0000   0.2098
  -8.750  -0.5275   0.11137   0.10505   0.0053   1.0000   0.2171
  -8.500  -0.5014   0.10537   0.09902   0.0071   1.0000   0.2272
  -8.250  -0.4988   0.10178   0.09551   0.0061   1.0000   0.2344
  -8.000  -0.5161   0.10055   0.09443   0.0033   1.0000   0.2443
  -7.750  -0.4998   0.09576   0.08966   0.0042   1.0000   0.2567
  -7.500  -0.4910   0.09189   0.08584   0.0045   1.0000   0.2692
  -7.250  -0.4931   0.08899   0.08304   0.0041   1.0000   0.2839
  -7.000  -0.4990   0.08637   0.08046   0.0035   1.0000   0.2985
  -6.250  -0.4916   0.06108   0.05490  -0.0286   1.0000   0.1306
  -6.000  -0.4812   0.05334   0.04663  -0.0333   1.0000   0.1058
  -5.750  -0.4675   0.04727   0.03987  -0.0351   1.0000   0.0945
  -5.500  -0.4504   0.04307   0.03537  -0.0351   1.0000   0.0929
  -5.250  -0.4325   0.03923   0.03099  -0.0348   1.0000   0.0938
  -5.000  -0.4128   0.03586   0.02691  -0.0340   1.0000   0.0956
  -4.750  -0.3927   0.03254   0.02336  -0.0330   1.0000   0.0991
  -4.500  -0.3710   0.02976   0.02022  -0.0317   1.0000   0.1034
  -4.250  -0.3508   0.02765   0.01785  -0.0303   1.0000   0.1188
  -4.000  -0.3293   0.02536   0.01535  -0.0286   1.0000   0.1378
  -3.750  -0.3099   0.02352   0.01360  -0.0268   1.0000   0.1775
  -3.500  -0.2894   0.02131   0.01177  -0.0249   1.0000   0.2464
  -3.250  -0.2749   0.01943   0.01067  -0.0224   1.0000   0.3792
  -3.000  -0.2646   0.01788   0.01012  -0.0185   1.0000   0.5360
  -2.750  -0.0973   0.01644   0.00877  -0.0338   1.0000   1.0000
  -2.500  -0.1126   0.01615   0.00839  -0.0293   1.0000   1.0000
  -2.250  -0.1208   0.01611   0.00814  -0.0251   1.0000   1.0000
  -2.000  -0.1199   0.01618   0.00793  -0.0220   1.0000   1.0000
  -1.750  -0.1124   0.01632   0.00777  -0.0198   1.0000   1.0000
  -1.500  -0.1011   0.01650   0.00767  -0.0181   1.0000   1.0000
  -1.250  -0.0877   0.01672   0.00763  -0.0168   1.0000   1.0000
  -1.000  -0.0729   0.01699   0.00766  -0.0157   1.0000   1.0000
  -0.750  -0.0573   0.01729   0.00770  -0.0148   1.0000   1.0000
  -0.500  -0.0410   0.01764   0.00785  -0.0140   1.0000   1.0000
  -0.250  -0.0243   0.01802   0.00805  -0.0134   1.0000   1.0000
   0.000  -0.0075   0.01845   0.00832  -0.0129   1.0000   1.0000
   0.250   0.0096   0.01891   0.00864  -0.0125   1.0000   1.0000
   0.500   0.0268   0.01942   0.00902  -0.0121   1.0000   1.0000
   0.750   0.0656   0.02026   0.00972  -0.0160   0.9905   1.0000
   1.000   0.1148   0.02125   0.01063  -0.0216   0.9755   1.0000
   1.250   0.1628   0.02220   0.01153  -0.0268   0.9600   1.0000
   1.500   0.2105   0.02311   0.01242  -0.0317   0.9442   1.0000
   1.750   0.2596   0.02399   0.01332  -0.0367   0.9282   1.0000
   2.000   0.3003   0.02476   0.01414  -0.0399   0.9108   1.0000
   2.250   0.3419   0.02550   0.01499  -0.0432   0.8929   1.0000
   2.500   0.3914   0.02616   0.01577  -0.0474   0.8752   1.0000
   2.750   0.4318   0.02681   0.01653  -0.0499   0.8561   1.0000
   3.000   0.4725   0.02734   0.01722  -0.0520   0.8366   1.0000
   3.250   0.5118   0.02780   0.01792  -0.0534   0.8170   1.0000
   3.500   0.5449   0.02823   0.01851  -0.0536   0.7957   1.0000
   3.750   0.5759   0.02860   0.01906  -0.0531   0.7741   1.0000
   4.000   0.6106   0.02863   0.01936  -0.0523   0.7527   1.0000
   4.250   0.6356   0.02888   0.01980  -0.0504   0.7284   1.0000
   4.500   0.6620   0.02889   0.02000  -0.0482   0.7036   1.0000
   4.750   0.6884   0.02867   0.01997  -0.0454   0.6778   1.0000
   5.000   0.7140   0.02827   0.01976  -0.0423   0.6501   1.0000
   5.250   0.7395   0.02764   0.01929  -0.0387   0.6203   1.0000
   5.500   0.7646   0.02682   0.01869  -0.0348   0.5873   1.0000
   5.750   0.7887   0.02595   0.01789  -0.0308   0.5488   1.0000
   6.000   0.8097   0.02544   0.01741  -0.0271   0.5002   1.0000
   6.250   0.8302   0.02501   0.01681  -0.0233   0.4427   1.0000
   6.500   0.8476   0.02535   0.01679  -0.0199   0.3741   1.0000
   6.750   0.8624   0.02661   0.01759  -0.0170   0.3024   1.0000
   7.000   0.8777   0.02856   0.01910  -0.0147   0.2402   1.0000
   7.250   0.8950   0.03096   0.02125  -0.0129   0.1923   1.0000
   7.500   0.9130   0.03336   0.02338  -0.0114   0.1561   1.0000
   7.750   0.9351   0.03644   0.02669  -0.0100   0.1336   1.0000
   8.000   0.9546   0.03967   0.03005  -0.0088   0.1167   1.0000
   8.250   0.9721   0.04300   0.03362  -0.0076   0.1041   1.0000
   8.500   0.9844   0.04727   0.03864  -0.0060   0.0996   1.0000
   8.750   0.9942   0.05175   0.04363  -0.0046   0.0966   1.0000
   9.000   1.0049   0.05623   0.04822  -0.0037   0.0914   1.0000
   9.250   0.9994   0.06071   0.05331  -0.0024   0.0896   1.0000
   9.500   0.9902   0.06538   0.05842  -0.0015   0.0888   1.0000
   9.750   0.9769   0.07021   0.06354  -0.0010   0.0889   1.0000
  10.000   0.9613   0.07500   0.06853  -0.0010   0.0898   1.0000
  10.250   0.9436   0.07970   0.07333  -0.0012   0.0906   1.0000
  10.500   0.9288   0.08500   0.07869  -0.0026   0.0915   1.0000
  10.750   0.9179   0.09065   0.08441  -0.0045   0.0926   1.0000
  11.000   0.8803   0.10147   0.09525  -0.0123   0.1052   1.0000
<< Back to MH 43 8.5% (mh43-il)

Polar data table (+)

Polar graphs


<< Back to MH 43 8.5% (mh43-il)