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MH33 (mh33-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH33 (mh33-il)
Reynolds number: 50,000
Max Cl/Cd: 32.3 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh33-il-50000.txt
Download as CSV file: xf-mh33-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH33                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5223   0.10041   0.09369   0.0014   1.0000   0.2551
  -8.000  -0.5283   0.09783   0.09122   0.0008   1.0000   0.2665
  -7.500  -0.5320   0.09194   0.08550   0.0013   1.0000   0.2927
  -7.250  -0.5323   0.08889   0.08254   0.0020   1.0000   0.3061
  -6.500  -0.5115   0.07779   0.07161   0.0058   1.0000   0.3507
  -5.750  -0.5189   0.05112   0.04361  -0.0294   1.0000   0.1155
  -5.500  -0.5045   0.04599   0.03789  -0.0292   1.0000   0.1026
  -5.250  -0.4881   0.04175   0.03335  -0.0282   1.0000   0.0968
  -5.000  -0.4690   0.03785   0.02847  -0.0269   1.0000   0.0902
  -4.750  -0.4483   0.03438   0.02462  -0.0256   1.0000   0.0890
  -4.500  -0.4256   0.03136   0.02109  -0.0241   1.0000   0.0894
  -4.250  -0.4030   0.02867   0.01819  -0.0228   1.0000   0.0962
  -4.000  -0.3796   0.02651   0.01582  -0.0215   1.0000   0.1108
  -3.750  -0.3531   0.02404   0.01311  -0.0197   1.0000   0.1310
  -3.500  -0.3291   0.02158   0.01104  -0.0182   1.0000   0.1980
  -3.250  -0.3142   0.01822   0.00941  -0.0153   1.0000   0.4263
  -3.000  -0.1572   0.01671   0.00836  -0.0303   1.0000   1.0000
  -2.750  -0.1522   0.01623   0.00762  -0.0278   1.0000   1.0000
  -2.500  -0.1426   0.01593   0.00703  -0.0255   1.0000   1.0000
  -2.250  -0.1304   0.01574   0.00656  -0.0233   1.0000   1.0000
  -2.000  -0.1167   0.01560   0.00616  -0.0212   1.0000   1.0000
  -1.750  -0.1021   0.01551   0.00583  -0.0192   1.0000   1.0000
  -1.500  -0.0869   0.01546   0.00556  -0.0172   1.0000   1.0000
  -1.250  -0.0709   0.01544   0.00528  -0.0154   1.0000   1.0000
  -1.000  -0.0543   0.01545   0.00512  -0.0136   1.0000   1.0000
  -0.750  -0.0371   0.01549   0.00500  -0.0120   1.0000   1.0000
  -0.500  -0.0194   0.01555   0.00493  -0.0105   1.0000   1.0000
  -0.250  -0.0013   0.01564   0.00490  -0.0090   1.0000   1.0000
   0.000   0.0170   0.01576   0.00493  -0.0077   1.0000   1.0000
   0.250   0.0354   0.01591   0.00496  -0.0064   1.0000   1.0000
   0.500   0.0539   0.01609   0.00508  -0.0053   1.0000   1.0000
   0.750   0.0723   0.01630   0.00526  -0.0042   1.0000   1.0000
   1.000   0.0906   0.01655   0.00549  -0.0031   1.0000   1.0000
   1.250   0.1086   0.01685   0.00579  -0.0021   1.0000   1.0000
   1.500   0.1263   0.01720   0.00616  -0.0012   1.0000   1.0000
   1.750   0.1434   0.01760   0.00660  -0.0004   1.0000   1.0000
   2.000   0.1600   0.01808   0.00712   0.0004   1.0000   1.0000
   2.250   0.1758   0.01864   0.00773   0.0010   1.0000   1.0000
   2.500   0.1908   0.01930   0.00847   0.0015   1.0000   1.0000
   2.750   0.2048   0.02008   0.00933   0.0018   1.0000   1.0000
   3.000   0.2693   0.02152   0.01110  -0.0076   0.9746   1.0000
   3.250   0.3611   0.02248   0.01252  -0.0204   0.9312   1.0000
   3.500   0.4520   0.02229   0.01299  -0.0308   0.8820   1.0000
   3.750   0.5334   0.02102   0.01234  -0.0368   0.8267   1.0000
   4.000   0.5841   0.01983   0.01147  -0.0362   0.7629   1.0000
   4.250   0.6145   0.01937   0.01109  -0.0325   0.6873   1.0000
   4.500   0.6353   0.01967   0.01113  -0.0283   0.6021   1.0000
   4.750   0.6533   0.02047   0.01154  -0.0245   0.5140   1.0000
   5.000   0.6708   0.02164   0.01223  -0.0213   0.4299   1.0000
   5.250   0.6883   0.02307   0.01329  -0.0186   0.3525   1.0000
   5.500   0.7068   0.02469   0.01458  -0.0164   0.2865   1.0000
   5.750   0.7275   0.02665   0.01633  -0.0145   0.2339   1.0000
   6.000   0.7480   0.02868   0.01822  -0.0129   0.1915   1.0000
   6.250   0.7700   0.03110   0.02050  -0.0115   0.1607   1.0000
   6.500   0.7908   0.03362   0.02334  -0.0099   0.1382   1.0000
   6.750   0.8118   0.03707   0.02741  -0.0083   0.1271   1.0000
   7.000   0.8288   0.03987   0.03052  -0.0067   0.1130   1.0000
   7.250   0.8445   0.04354   0.03454  -0.0051   0.1059   1.0000
   7.500   0.8551   0.04802   0.03969  -0.0032   0.1044   1.0000
   7.750   0.8612   0.05294   0.04519  -0.0016   0.1045   1.0000
   8.000   0.8643   0.05813   0.05081  -0.0003   0.1058   1.0000
   8.250   0.8681   0.06350   0.05644   0.0005   0.1075   1.0000
   8.500   0.7802   0.06142   0.05537   0.0033   0.1151   1.0000
   8.750   0.7629   0.06741   0.06146   0.0031   0.1183   1.0000
   9.000   0.7717   0.07355   0.06763   0.0035   0.1217   1.0000
   9.250   0.6979   0.08175   0.07579  -0.0039   0.1294   1.0000
   9.500   0.7034   0.08778   0.08186  -0.0042   0.1353   1.0000
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