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

MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: MH 122 9.32% (mh122-il)
Reynolds number: 500,000
Max Cl/Cd: 114.87 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh122-il-500000-n5.txt
Download as CSV file: xf-mh122-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 122  9.32%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3422   0.10965   0.10727  -0.0529   0.9934   0.0062
 -10.000  -0.3397   0.10403   0.10167  -0.0559   0.9914   0.0064
  -9.750  -0.3343   0.09927   0.09692  -0.0590   0.9892   0.0066
  -9.500  -0.3259   0.09490   0.09256  -0.0623   0.9869   0.0067
  -9.250  -0.3169   0.09045   0.08812  -0.0660   0.9847   0.0069
  -9.000  -0.3061   0.08647   0.08411  -0.0698   0.9829   0.0071
  -7.750  -0.2742   0.06311   0.06082  -0.0906   0.9510   0.0072
  -7.500  -0.2546   0.05092   0.04849  -0.1109   0.9439   0.0070
  -7.250  -0.2365   0.04406   0.04140  -0.1198   0.9368   0.0070
  -7.000  -0.2118   0.03798   0.03500  -0.1262   0.9323   0.0067
  -6.750  -0.1912   0.03540   0.03227  -0.1287   0.9264   0.0053
  -6.500  -0.1712   0.02961   0.02603  -0.1323   0.9204   0.0046
  -6.250  -0.1531   0.02173   0.01735  -0.1329   0.9134   0.0034
  -6.000  -0.1267   0.01941   0.01465  -0.1333   0.9088   0.0032
  -5.750  -0.0983   0.01783   0.01277  -0.1340   0.9055   0.0031
  -5.250  -0.0479   0.01463   0.00901  -0.1339   0.8972   0.0030
  -5.000  -0.0207   0.01326   0.00741  -0.1340   0.8939   0.0029
  -4.750   0.0064   0.01217   0.00615  -0.1341   0.8907   0.0029
  -4.500   0.0321   0.01133   0.00518  -0.1339   0.8868   0.0030
  -4.250   0.0593   0.01066   0.00436  -0.1340   0.8835   0.0030
  -4.000   0.0876   0.01001   0.00358  -0.1343   0.8807   0.0031
  -3.750   0.1164   0.00954   0.00295  -0.1346   0.8782   0.0035
  -3.500   0.1435   0.00925   0.00259  -0.1346   0.8748   0.0044
  -3.250   0.1713   0.00901   0.00230  -0.1347   0.8716   0.0092
  -3.000   0.1991   0.00835   0.00204  -0.1353   0.8689   0.1088
  -2.750   0.2268   0.00740   0.00181  -0.1362   0.8665   0.3305
  -2.500   0.2548   0.00721   0.00173  -0.1365   0.8638   0.3913
  -2.250   0.2820   0.00707   0.00172  -0.1366   0.8608   0.4451
  -2.000   0.3099   0.00701   0.00170  -0.1367   0.8580   0.4756
  -1.750   0.3381   0.00695   0.00169  -0.1368   0.8554   0.5087
  -1.500   0.3668   0.00692   0.00166  -0.1371   0.8531   0.5304
  -1.250   0.3950   0.00691   0.00166  -0.1372   0.8506   0.5438
  -1.000   0.4223   0.00690   0.00166  -0.1372   0.8475   0.5537
  -0.750   0.4501   0.00690   0.00167  -0.1373   0.8445   0.5635
  -0.500   0.4783   0.00689   0.00168  -0.1374   0.8417   0.5734
  -0.250   0.5072   0.00689   0.00168  -0.1377   0.8389   0.5833
   0.000   0.5339   0.00689   0.00172  -0.1375   0.8346   0.5936
   0.250   0.5612   0.00689   0.00174  -0.1374   0.8297   0.6045
   0.500   0.5897   0.00689   0.00175  -0.1376   0.8251   0.6162
   0.750   0.6155   0.00687   0.00180  -0.1372   0.8181   0.6280
   1.000   0.6432   0.00687   0.00181  -0.1371   0.8115   0.6408
   1.250   0.6688   0.00685   0.00185  -0.1367   0.8023   0.6541
   1.500   0.6949   0.00684   0.00188  -0.1362   0.7918   0.6685
   1.750   0.7203   0.00683   0.00191  -0.1357   0.7782   0.6840
   2.000   0.7451   0.00683   0.00196  -0.1349   0.7593   0.7004
   2.250   0.7695   0.00685   0.00201  -0.1341   0.7382   0.7185
   2.500   0.7935   0.00692   0.00208  -0.1332   0.7133   0.7385
   2.750   0.8144   0.00709   0.00217  -0.1317   0.6693   0.7601
   3.000   0.8281   0.00759   0.00240  -0.1286   0.5900   0.7847
   3.250   0.8388   0.00829   0.00277  -0.1251   0.5012   0.8144
   3.500   0.8502   0.00894   0.00315  -0.1219   0.4194   0.8532
   3.750   0.8598   0.00939   0.00346  -0.1181   0.3534   0.9264
   4.000   0.8780   0.01013   0.00385  -0.1165   0.2718   1.0000
   4.250   0.8967   0.01077   0.00423  -0.1151   0.2133   1.0000
   4.500   0.9158   0.01142   0.00462  -0.1137   0.1611   1.0000
   4.750   0.9359   0.01198   0.00504  -0.1124   0.1220   1.0000
   5.000   0.9572   0.01246   0.00542  -0.1114   0.0977   1.0000
   5.250   0.9784   0.01294   0.00581  -0.1104   0.0759   1.0000
   5.500   0.9998   0.01339   0.00621  -0.1093   0.0601   1.0000
   5.750   1.0214   0.01383   0.00662  -0.1083   0.0485   1.0000
   6.000   1.0427   0.01429   0.00705  -0.1073   0.0384   1.0000
   6.250   1.0635   0.01474   0.00750  -0.1061   0.0301   1.0000
   6.500   1.0834   0.01523   0.00798  -0.1048   0.0219   1.0000
   6.750   1.1026   0.01578   0.00849  -0.1035   0.0146   1.0000
   7.000   1.1214   0.01637   0.00906  -0.1020   0.0094   1.0000
   7.250   1.1397   0.01701   0.00978  -0.1004   0.0055   1.0000
   7.500   1.1573   0.01775   0.01057  -0.0987   0.0033   1.0000
   7.750   1.1754   0.01843   0.01128  -0.0972   0.0022   1.0000
   8.000   1.1924   0.01927   0.01222  -0.0955   0.0018   1.0000
   8.250   1.2102   0.02001   0.01306  -0.0939   0.0016   1.0000
   8.500   1.2273   0.02082   0.01399  -0.0922   0.0014   1.0000
   8.750   1.2440   0.02168   0.01496  -0.0906   0.0012   1.0000
   9.000   1.2601   0.02260   0.01600  -0.0888   0.0011   1.0000
   9.250   1.2755   0.02359   0.01711  -0.0870   0.0010   1.0000
   9.500   1.2906   0.02461   0.01824  -0.0853   0.0009   1.0000
   9.750   1.3036   0.02588   0.01966  -0.0833   0.0008   1.0000
  10.000   1.3117   0.02783   0.02189  -0.0806   0.0007   1.0000
  10.250   1.3178   0.03000   0.02432  -0.0777   0.0006   1.0000
  10.500   1.3271   0.03162   0.02614  -0.0754   0.0006   1.0000
  10.750   1.3343   0.03345   0.02820  -0.0729   0.0006   1.0000
  11.000   1.3383   0.03561   0.03061  -0.0702   0.0006   1.0000
  11.250   1.3398   0.03800   0.03327  -0.0674   0.0006   1.0000
  11.500   1.3377   0.04074   0.03628  -0.0646   0.0005   1.0000
  11.750   1.3331   0.04370   0.03953  -0.0618   0.0005   1.0000
  12.000   1.3250   0.04709   0.04319  -0.0591   0.0005   1.0000
  12.250   1.3130   0.05098   0.04737  -0.0567   0.0005   1.0000
  12.500   1.2987   0.05528   0.05194  -0.0548   0.0005   1.0000
  12.750   1.2806   0.06029   0.05721  -0.0537   0.0005   1.0000
  13.000   1.2623   0.06564   0.06281  -0.0534   0.0005   1.0000
  13.250   1.2426   0.07170   0.06908  -0.0543   0.0005   1.0000
  13.500   1.2215   0.07871   0.07630  -0.0567   0.0005   1.0000
  13.750   1.1998   0.08693   0.08470  -0.0607   0.0005   1.0000
  14.000   1.1763   0.09729   0.09524  -0.0672   0.0005   1.0000
  14.250   1.1549   0.10960   0.10771  -0.0754   0.0006   1.0000
  14.500   1.1273   0.12592   0.12415  -0.0847   0.0006   1.0000
  14.750   1.0952   0.14188   0.14015  -0.0929   0.0006   1.0000
<< Back to MH 122 9.32% (mh122-il)

Polar data table (+)

Polar graphs


<< Back to MH 122 9.32% (mh122-il)