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MH 23 8% (mh23-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH 23 8% (mh23-il)
Reynolds number: 1,000,000
Max Cl/Cd: 83.86 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh23-il-1000000.txt
Download as CSV file: xf-mh23-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 23  8%                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4589   0.04719   0.04572  -0.0462   0.9941   0.0045
  -7.500  -0.4713   0.03791   0.03625  -0.0501   0.9900   0.0048
  -7.250  -0.4673   0.03212   0.03028  -0.0520   0.9873   0.0051
  -7.000  -0.4534   0.02824   0.02625  -0.0535   0.9855   0.0054
  -6.750  -0.4375   0.02465   0.02246  -0.0545   0.9838   0.0058
  -6.500  -0.4202   0.02106   0.01867  -0.0550   0.9818   0.0065
  -6.250  -0.4066   0.01829   0.01571  -0.0536   0.9781   0.0074
  -6.000  -0.3744   0.01882   0.01620  -0.0535   0.9766   0.0093
  -5.750  -0.3576   0.01640   0.01355  -0.0524   0.9734   0.0094
  -5.500  -0.3414   0.01393   0.01081  -0.0511   0.9701   0.0095
  -3.500  -0.1962   0.01089   0.00574  -0.0388   0.9471   0.0085
  -3.250  -0.1762   0.00968   0.00440  -0.0367   0.9437   0.0074
  -3.000  -0.1546   0.00897   0.00355  -0.0350   0.9399   0.0067
  -2.750  -0.1313   0.00851   0.00298  -0.0337   0.9359   0.0064
  -2.500  -0.1068   0.00820   0.00257  -0.0327   0.9324   0.0062
  -2.250  -0.0820   0.00799   0.00228  -0.0318   0.9292   0.0063
  -2.000  -0.0564   0.00781   0.00203  -0.0312   0.9247   0.0072
  -1.750  -0.0350   0.00710   0.00174  -0.0299   0.9203   0.1322
  -1.500  -0.0168   0.00615   0.00156  -0.0282   0.9163   0.3608
  -1.250  -0.0008   0.00522   0.00145  -0.0261   0.9107   0.5982
  -1.000   0.0097   0.00420   0.00149  -0.0218   0.9054   0.8925
  -0.750   0.0416   0.00423   0.00156  -0.0223   0.9016   0.9302
  -0.500   0.0705   0.00427   0.00159  -0.0223   0.8958   0.9444
  -0.250   0.0960   0.00431   0.00157  -0.0215   0.8906   0.9553
   0.000   0.1319   0.00438   0.00162  -0.0231   0.8841   0.9597
   0.250   0.1636   0.00446   0.00167  -0.0237   0.8771   0.9674
   0.500   0.2062   0.00453   0.00173  -0.0269   0.8681   0.9704
   0.750   0.2466   0.00457   0.00174  -0.0296   0.8562   0.9724
   1.000   0.2817   0.00459   0.00171  -0.0311   0.8380   0.9747
   1.250   0.3135   0.00467   0.00168  -0.0319   0.8071   0.9779
   1.500   0.3400   0.00487   0.00169  -0.0315   0.7615   0.9818
   1.750   0.3753   0.00509   0.00170  -0.0332   0.7073   0.9833
   2.000   0.4108   0.00536   0.00175  -0.0351   0.6516   0.9854
   2.250   0.4456   0.00566   0.00182  -0.0369   0.5909   0.9881
   2.500   0.4779   0.00598   0.00190  -0.0381   0.5280   0.9910
   2.750   0.5076   0.00634   0.00202  -0.0388   0.4653   0.9938
   3.000   0.5415   0.00663   0.00210  -0.0405   0.4027   0.9953
   3.250   0.5738   0.00695   0.00218  -0.0420   0.3423   0.9969
   3.500   0.6055   0.00722   0.00228  -0.0432   0.2944   0.9986
   3.750   0.6360   0.00759   0.00241  -0.0442   0.2364   0.9999
   4.000   0.6583   0.00797   0.00260  -0.0434   0.1866   1.0000
   4.250   0.6779   0.00855   0.00283  -0.0421   0.1168   1.0000
   4.500   0.6996   0.00886   0.00303  -0.0411   0.0902   1.0000
   4.750   0.7210   0.00922   0.00326  -0.0401   0.0616   1.0000
   5.000   0.7426   0.00954   0.00349  -0.0390   0.0433   1.0000
   5.250   0.7640   0.00988   0.00375  -0.0379   0.0278   1.0000
   5.500   0.7850   0.01026   0.00406  -0.0368   0.0148   1.0000
   5.750   0.8055   0.01069   0.00445  -0.0355   0.0056   1.0000
   6.000   0.8261   0.01113   0.00493  -0.0341   0.0029   1.0000
   6.250   0.8465   0.01159   0.00552  -0.0326   0.0025   1.0000
   6.500   0.8665   0.01207   0.00611  -0.0311   0.0023   1.0000
   6.750   0.8851   0.01272   0.00688  -0.0293   0.0022   1.0000
   7.000   0.9027   0.01345   0.00774  -0.0273   0.0022   1.0000
   7.250   0.9187   0.01434   0.00879  -0.0249   0.0022   1.0000
   7.500   0.9327   0.01545   0.01007  -0.0223   0.0023   1.0000
   7.750   0.9430   0.01715   0.01202  -0.0188   0.0024   1.0000
   8.000   0.9512   0.01947   0.01464  -0.0150   0.0026   1.0000
   8.250   0.9573   0.02241   0.01794  -0.0109   0.0028   1.0000
   8.500   0.9581   0.02596   0.02190  -0.0062   0.0032   1.0000
   8.750   0.9468   0.03066   0.02708  -0.0001   0.0035   1.0000
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