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MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH 121 8.76% (mh121-il)
Reynolds number: 1,000,000
Max Cl/Cd: 139.08 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh121-il-1000000.txt
Download as CSV file: xf-mh121-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 121  8.76%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4302   0.11709   0.11544  -0.0307   1.0000   0.0034
 -10.250  -0.4300   0.11409   0.11246  -0.0308   1.0000   0.0034
 -10.000  -0.4314   0.11100   0.10940  -0.0307   1.0000   0.0035
  -9.750  -0.4234   0.10676   0.10516  -0.0337   0.9994   0.0036
  -9.500  -0.4133   0.10231   0.10071  -0.0374   0.9984   0.0038
  -9.250  -0.4037   0.09751   0.09592  -0.0414   0.9972   0.0038
  -9.000  -0.3933   0.09276   0.09118  -0.0458   0.9959   0.0040
  -8.750  -0.3821   0.08793   0.08635  -0.0505   0.9947   0.0041
  -8.500  -0.3713   0.08293   0.08135  -0.0556   0.9933   0.0042
  -8.250  -0.3628   0.07795   0.07638  -0.0604   0.9902   0.0042
  -8.000  -0.3517   0.07261   0.07105  -0.0665   0.9868   0.0044
  -7.750  -0.3383   0.06634   0.06479  -0.0750   0.9836   0.0045
  -7.500  -0.3231   0.05583   0.05425  -0.0930   0.9753   0.0043
  -7.250  -0.3027   0.04783   0.04607  -0.1045   0.9709   0.0044
  -7.000  -0.2859   0.04192   0.03997  -0.1101   0.9648   0.0046
  -6.750  -0.2633   0.03687   0.03468  -0.1142   0.9603   0.0049
  -6.500  -0.2295   0.03534   0.03305  -0.1158   0.9586   0.0060
  -5.500  -0.1279   0.01419   0.00997  -0.1238   0.9376   0.0037
  -5.250  -0.0979   0.01265   0.00816  -0.1245   0.9335   0.0043
  -5.000  -0.0683   0.01174   0.00712  -0.1250   0.9295   0.0051
  -4.750  -0.0415   0.01103   0.00631  -0.1249   0.9243   0.0056
  -4.500  -0.0130   0.01021   0.00537  -0.1252   0.9201   0.0059
  -4.250   0.0135   0.00910   0.00411  -0.1253   0.9156   0.0072
  -4.000   0.0400   0.00839   0.00328  -0.1252   0.9109   0.0076
  -3.750   0.0686   0.00791   0.00268  -0.1254   0.9071   0.0073
  -3.500   0.0972   0.00750   0.00213  -0.1256   0.9036   0.0073
  -3.250   0.1249   0.00701   0.00159  -0.1255   0.8995   0.0348
  -3.000   0.1504   0.00558   0.00124  -0.1263   0.8957   0.3609
  -2.750   0.1789   0.00534   0.00120  -0.1268   0.8926   0.4496
  -2.500   0.2067   0.00528   0.00116  -0.1269   0.8893   0.4709
  -2.250   0.2346   0.00524   0.00113  -0.1270   0.8858   0.4926
  -2.000   0.2627   0.00521   0.00110  -0.1272   0.8827   0.5092
  -1.750   0.2915   0.00519   0.00106  -0.1274   0.8798   0.5282
  -1.500   0.3194   0.00517   0.00107  -0.1276   0.8767   0.5470
  -1.250   0.3471   0.00514   0.00107  -0.1276   0.8733   0.5625
  -1.000   0.3752   0.00513   0.00107  -0.1278   0.8699   0.5757
  -0.750   0.4037   0.00513   0.00107  -0.1280   0.8664   0.5869
  -0.500   0.4311   0.00512   0.00108  -0.1280   0.8620   0.5973
  -0.250   0.4585   0.00510   0.00109  -0.1279   0.8569   0.6079
   0.000   0.4867   0.00511   0.00110  -0.1280   0.8519   0.6189
   0.250   0.5134   0.00508   0.00112  -0.1278   0.8459   0.6305
   0.500   0.5412   0.00508   0.00113  -0.1278   0.8399   0.6429
   0.750   0.5678   0.00505   0.00116  -0.1276   0.8328   0.6562
   1.000   0.5950   0.00505   0.00119  -0.1275   0.8254   0.6704
   1.250   0.6212   0.00502   0.00121  -0.1271   0.8160   0.6858
   1.500   0.6474   0.00501   0.00124  -0.1267   0.8047   0.7023
   1.750   0.6736   0.00500   0.00128  -0.1264   0.7931   0.7200
   2.000   0.6982   0.00502   0.00130  -0.1256   0.7708   0.7397
   2.250   0.7073   0.00566   0.00138  -0.1214   0.6253   0.7606
   2.500   0.7245   0.00621   0.00168  -0.1193   0.5392   0.7846
   2.750   0.7278   0.00785   0.00230  -0.1148   0.2968   0.8127
   3.000   0.7428   0.00869   0.00269  -0.1125   0.1738   0.8482
   3.250   0.7574   0.00931   0.00304  -0.1099   0.0828   0.8999
   3.500   0.7744   0.00988   0.00338  -0.1078   0.0144   1.0000
   3.750   0.7986   0.01027   0.00372  -0.1071   0.0028   1.0000
   4.000   0.8238   0.01057   0.00412  -0.1065   0.0024   1.0000
   4.250   0.8478   0.01099   0.00465  -0.1057   0.0024   1.0000
   4.500   0.8709   0.01152   0.00527  -0.1047   0.0024   1.0000
   4.750   0.8933   0.01214   0.00602  -0.1035   0.0025   1.0000
   5.000   0.9153   0.01282   0.00679  -0.1022   0.0027   1.0000
   5.250   0.9356   0.01374   0.00785  -0.1006   0.0031   1.0000
   5.500   0.9518   0.01634   0.01073  -0.0975   0.0042   1.0000
   7.250   1.0596   0.04387   0.04046  -0.0807   0.0059   1.0000
   7.500   1.0641   0.04739   0.04425  -0.0774   0.0059   1.0000
   7.750   1.0659   0.05098   0.04809  -0.0740   0.0059   1.0000
   8.000   1.0653   0.05461   0.05195  -0.0705   0.0059   1.0000
   8.250   1.0616   0.05828   0.05582  -0.0670   0.0059   1.0000
   8.500   1.0549   0.06188   0.05960  -0.0635   0.0059   1.0000
   8.750   1.0422   0.06498   0.06285  -0.0592   0.0058   1.0000
   9.000   1.0262   0.06802   0.06602  -0.0551   0.0058   1.0000
   9.250   1.0087   0.07151   0.06963  -0.0521   0.0058   1.0000
   9.500   0.9902   0.07553   0.07377  -0.0503   0.0058   1.0000
   9.750   0.9715   0.08011   0.07847  -0.0499   0.0058   1.0000
  10.000   0.9518   0.08556   0.08401  -0.0510   0.0058   1.0000
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