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MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MH 121 8.76% (mh121-il)
Reynolds number: 500,000
Max Cl/Cd: 107.77 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh121-il-500000-n5.txt
Download as CSV file: xf-mh121-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.4433   0.14787   0.14536  -0.0274   1.0000   0.0047
 -12.500  -0.4393   0.14456   0.14206  -0.0281   1.0000   0.0048
 -12.250  -0.4357   0.14116   0.13867  -0.0289   1.0000   0.0050
  -7.750  -0.3486   0.06393   0.06172  -0.0749   0.9715   0.0022
  -7.500  -0.3390   0.05365   0.05137  -0.0907   0.9599   0.0021
  -7.250  -0.3280   0.04613   0.04363  -0.0993   0.9522   0.0020
  -7.000  -0.3107   0.03916   0.03636  -0.1055   0.9465   0.0020
  -6.750  -0.2868   0.03248   0.02927  -0.1105   0.9427   0.0020
  -6.500  -0.2645   0.02663   0.02294  -0.1128   0.9369   0.0020
  -6.250  -0.2368   0.02173   0.01747  -0.1148   0.9335   0.0020
  -6.000  -0.2057   0.01899   0.01429  -0.1165   0.9311   0.0022
  -5.750  -0.1801   0.01627   0.01112  -0.1167   0.9260   0.0024
  -5.500  -0.1516   0.01426   0.00880  -0.1175   0.9222   0.0029
  -5.250  -0.1207   0.01358   0.00795  -0.1187   0.9193   0.0035
  -5.000  -0.0915   0.01320   0.00752  -0.1194   0.9158   0.0046
  -4.750  -0.0634   0.01278   0.00701  -0.1197   0.9118   0.0056
  -4.500  -0.0349   0.01166   0.00573  -0.1200   0.9080   0.0057
  -4.250  -0.0054   0.01070   0.00462  -0.1206   0.9050   0.0057
  -4.000   0.0212   0.01001   0.00380  -0.1206   0.9006   0.0058
  -3.750   0.0496   0.00948   0.00312  -0.1208   0.8969   0.0060
  -3.500   0.0792   0.00907   0.00251  -0.1212   0.8938   0.0070
  -3.250   0.1080   0.00850   0.00210  -0.1217   0.8906   0.0625
  -3.000   0.1335   0.00725   0.00176  -0.1225   0.8867   0.3239
  -2.750   0.1615   0.00701   0.00166  -0.1228   0.8834   0.3920
  -2.500   0.1903   0.00687   0.00159  -0.1232   0.8805   0.4382
  -2.250   0.2190   0.00680   0.00154  -0.1235   0.8777   0.4683
  -2.000   0.2463   0.00674   0.00153  -0.1235   0.8742   0.4994
  -1.750   0.2741   0.00668   0.00152  -0.1236   0.8710   0.5272
  -1.500   0.3027   0.00666   0.00145  -0.1239   0.8681   0.5438
  -1.000   0.3589   0.00663   0.00143  -0.1242   0.8622   0.5643
  -0.750   0.3866   0.00663   0.00144  -0.1243   0.8588   0.5733
  -0.250   0.4437   0.00663   0.00147  -0.1247   0.8528   0.5926
   0.000   0.4706   0.00662   0.00151  -0.1246   0.8484   0.6026
   0.250   0.4980   0.00662   0.00154  -0.1246   0.8435   0.6129
   0.500   0.5263   0.00662   0.00156  -0.1247   0.8385   0.6240
   0.750   0.5526   0.00661   0.00161  -0.1244   0.8314   0.6358
   1.000   0.5800   0.00661   0.00167  -0.1243   0.8242   0.6478
   1.250   0.6065   0.00660   0.00171  -0.1240   0.8150   0.6609
   1.500   0.6326   0.00659   0.00175  -0.1236   0.8039   0.6746
   1.750   0.6583   0.00659   0.00179  -0.1231   0.7892   0.6894
   2.000   0.6830   0.00660   0.00182  -0.1223   0.7677   0.7052
   2.250   0.7071   0.00664   0.00187  -0.1214   0.7391   0.7224
   2.500   0.7296   0.00677   0.00199  -0.1201   0.6973   0.7413
   2.750   0.7445   0.00728   0.00215  -0.1173   0.6044   0.7617
   3.000   0.7491   0.00852   0.00265  -0.1127   0.4357   0.7852
   3.250   0.7494   0.01046   0.00341  -0.1080   0.1779   0.8129
   3.500   0.7612   0.01157   0.00395  -0.1052   0.0473   0.8489
   3.750   0.7778   0.01178   0.00421  -0.1028   0.0262   0.9077
   4.000   0.8007   0.01224   0.00459  -0.1019   0.0031   1.0000
   4.250   0.8250   0.01260   0.00501  -0.1012   0.0020   1.0000
   4.500   0.8489   0.01301   0.00552  -0.1004   0.0018   1.0000
   4.750   0.8721   0.01351   0.00619  -0.0995   0.0017   1.0000
   5.000   0.8942   0.01414   0.00694  -0.0984   0.0017   1.0000
   5.250   0.9153   0.01489   0.00781  -0.0971   0.0016   1.0000
   5.500   0.9352   0.01583   0.00888  -0.0955   0.0016   1.0000
   5.750   0.9544   0.01696   0.01014  -0.0938   0.0016   1.0000
   6.000   0.9742   0.01829   0.01162  -0.0923   0.0016   1.0000
   6.250   0.9955   0.01989   0.01340  -0.0909   0.0017   1.0000
   6.500   1.0185   0.02192   0.01566  -0.0899   0.0017   1.0000
   6.750   1.0416   0.02422   0.01823  -0.0888   0.0017   1.0000
   7.000   1.0625   0.02708   0.02146  -0.0874   0.0018   1.0000
   7.250   1.0789   0.03045   0.02523  -0.0852   0.0019   1.0000
   7.500   1.0893   0.03443   0.02966  -0.0821   0.0019   1.0000
   8.000   1.1080   0.04022   0.03600  -0.0767   0.0022   1.0000
   8.250   1.1186   0.04238   0.03838  -0.0743   0.0023   1.0000
   8.500   1.1267   0.04550   0.04185  -0.0713   0.0025   1.0000
   8.750   1.1023   0.05764   0.05460  -0.0634   0.0037   1.0000
   9.000   1.0881   0.06213   0.05932  -0.0590   0.0039   1.0000
   9.250   1.0694   0.06580   0.06316  -0.0544   0.0041   1.0000
   9.500   1.0495   0.06962   0.06714  -0.0509   0.0042   1.0000
   9.750   1.0306   0.07368   0.07134  -0.0487   0.0042   1.0000
  10.000   1.0104   0.07837   0.07616  -0.0479   0.0043   1.0000
  10.250   0.9909   0.08367   0.08158  -0.0486   0.0042   1.0000
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