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MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MH 122 9.32% (mh122-il)
Reynolds number: 1,000,000
Max Cl/Cd: 125.13 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh122-il-1000000-n5.txt
Download as CSV file: xf-mh122-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2809   0.08333   0.08160  -0.0764   0.9779   0.0040
  -8.750  -0.2742   0.07932   0.07760  -0.0793   0.9721   0.0042
  -8.500  -0.2713   0.07500   0.07329  -0.0820   0.9634   0.0042
  -6.000  -0.1092   0.01731   0.01324  -0.1374   0.8761   0.0026
  -5.750  -0.0868   0.01473   0.01027  -0.1370   0.8718   0.0024
  -5.500  -0.0624   0.01291   0.00815  -0.1366   0.8679   0.0023
  -5.250  -0.0370   0.01155   0.00657  -0.1363   0.8646   0.0022
  -5.000  -0.0114   0.01047   0.00533  -0.1360   0.8613   0.0021
  -4.750   0.0148   0.00961   0.00432  -0.1358   0.8581   0.0021
  -4.500   0.0417   0.00895   0.00353  -0.1358   0.8552   0.0021
  -4.250   0.0692   0.00848   0.00291  -0.1359   0.8525   0.0021
  -4.000   0.0968   0.00810   0.00244  -0.1359   0.8497   0.0021
  -3.750   0.1247   0.00781   0.00208  -0.1360   0.8470   0.0022
  -3.500   0.1527   0.00760   0.00180  -0.1362   0.8443   0.0023
  -3.250   0.1808   0.00744   0.00158  -0.1363   0.8417   0.0026
  -3.000   0.2090   0.00731   0.00142  -0.1364   0.8393   0.0047
  -2.750   0.2368   0.00700   0.00125  -0.1367   0.8370   0.0453
  -2.500   0.2645   0.00653   0.00111  -0.1371   0.8344   0.1466
  -2.250   0.2918   0.00586   0.00097  -0.1377   0.8317   0.3206
  -2.000   0.3197   0.00568   0.00093  -0.1379   0.8292   0.3788
  -1.750   0.3479   0.00556   0.00091  -0.1382   0.8269   0.4245
  -1.500   0.3761   0.00548   0.00090  -0.1384   0.8245   0.4593
  -1.250   0.4041   0.00542   0.00090  -0.1385   0.8219   0.4857
  -1.000   0.4320   0.00539   0.00091  -0.1386   0.8187   0.5038
  -0.750   0.4600   0.00537   0.00090  -0.1387   0.8149   0.5161
  -0.500   0.4878   0.00538   0.00090  -0.1388   0.8105   0.5252
  -0.250   0.5153   0.00537   0.00090  -0.1387   0.8047   0.5337
   0.000   0.5427   0.00538   0.00090  -0.1387   0.7987   0.5423
   0.250   0.5699   0.00537   0.00092  -0.1386   0.7914   0.5507
   0.500   0.5970   0.00539   0.00093  -0.1385   0.7835   0.5600
   0.750   0.6237   0.00540   0.00096  -0.1383   0.7735   0.5691
   1.000   0.6501   0.00542   0.00098  -0.1380   0.7609   0.5787
   1.250   0.6756   0.00548   0.00101  -0.1375   0.7430   0.5892
   1.500   0.6995   0.00559   0.00105  -0.1367   0.7123   0.5997
   1.750   0.7213   0.00581   0.00113  -0.1354   0.6691   0.6107
   2.000   0.7400   0.00622   0.00132  -0.1335   0.6044   0.6223
   2.250   0.7574   0.00677   0.00158  -0.1315   0.5298   0.6342
   2.500   0.7756   0.00734   0.00185  -0.1297   0.4538   0.6475
   2.750   0.7943   0.00790   0.00214  -0.1281   0.3810   0.6615
   3.000   0.8145   0.00838   0.00241  -0.1268   0.3197   0.6771
   3.250   0.8349   0.00885   0.00270  -0.1255   0.2625   0.6943
   3.500   0.8550   0.00936   0.00300  -0.1242   0.2052   0.7125
   3.750   0.8772   0.00971   0.00327  -0.1233   0.1688   0.7328
   4.000   0.8983   0.01013   0.00357  -0.1221   0.1280   0.7561
   4.250   0.9209   0.01042   0.00385  -0.1213   0.1040   0.7830
   4.500   0.9431   0.01070   0.00414  -0.1203   0.0841   0.8163
   4.750   0.9642   0.01093   0.00445  -0.1190   0.0669   0.8600
   5.000   0.9815   0.01097   0.00466  -0.1168   0.0566   1.0000
   5.250   1.0047   0.01130   0.00495  -0.1160   0.0463   1.0000
   5.500   1.0274   0.01167   0.00527  -0.1152   0.0353   1.0000
   5.750   1.0496   0.01207   0.00561  -0.1143   0.0248   1.0000
   6.000   1.0710   0.01253   0.00600  -0.1133   0.0143   1.0000
   6.250   1.0926   0.01298   0.00640  -0.1123   0.0083   1.0000
   6.500   1.1136   0.01346   0.00685  -0.1112   0.0038   1.0000
   6.750   1.1346   0.01394   0.00733  -0.1101   0.0018   1.0000
   7.000   1.1561   0.01435   0.00781  -0.1091   0.0014   1.0000
   7.250   1.1766   0.01479   0.00830  -0.1078   0.0011   1.0000
   7.500   1.1964   0.01528   0.00884  -0.1065   0.0009   1.0000
   7.750   1.2153   0.01583   0.00946  -0.1049   0.0007   1.0000
   8.000   1.2337   0.01646   0.01016  -0.1033   0.0006   1.0000
   8.250   1.2530   0.01694   0.01069  -0.1020   0.0006   1.0000
   8.500   1.2719   0.01747   0.01129  -0.1006   0.0005   1.0000
   8.750   1.2903   0.01807   0.01195  -0.0991   0.0005   1.0000
   9.000   1.3080   0.01873   0.01269  -0.0975   0.0004   1.0000
   9.250   1.3250   0.01945   0.01350  -0.0958   0.0004   1.0000
   9.500   1.3414   0.02025   0.01439  -0.0941   0.0003   1.0000
   9.750   1.3573   0.02109   0.01537  -0.0923   0.0003   1.0000
  10.000   1.3721   0.02203   0.01642  -0.0904   0.0003   1.0000
  10.250   1.3863   0.02302   0.01753  -0.0884   0.0002   1.0000
  10.500   1.3994   0.02411   0.01875  -0.0864   0.0002   1.0000
  10.750   1.4115   0.02527   0.02004  -0.0842   0.0002   1.0000
  11.000   1.4218   0.02660   0.02153  -0.0819   0.0002   1.0000
  11.250   1.4313   0.02797   0.02306  -0.0795   0.0002   1.0000
  11.500   1.4387   0.02954   0.02480  -0.0770   0.0002   1.0000
  11.750   1.4451   0.03116   0.02659  -0.0745   0.0002   1.0000
  12.000   1.4493   0.03299   0.02861  -0.0718   0.0002   1.0000
  12.250   1.4509   0.03508   0.03089  -0.0691   0.0002   1.0000
  12.500   1.4506   0.03735   0.03339  -0.0664   0.0002   1.0000
  12.750   1.4466   0.04003   0.03628  -0.0636   0.0002   1.0000
  13.000   1.4415   0.04286   0.03932  -0.0611   0.0002   1.0000
  13.250   1.4345   0.04596   0.04263  -0.0588   0.0002   1.0000
  13.500   1.4238   0.04960   0.04648  -0.0568   0.0002   1.0000
  13.750   1.4105   0.05373   0.05083  -0.0552   0.0002   1.0000
  14.000   1.3924   0.05873   0.05606  -0.0542   0.0002   1.0000
  14.250   1.3745   0.06407   0.06161  -0.0542   0.0002   1.0000
  14.500   1.3533   0.07047   0.06821  -0.0553   0.0002   1.0000
  14.750   1.3301   0.07803   0.07597  -0.0579   0.0002   1.0000
  15.000   1.3044   0.08723   0.08536  -0.0625   0.0002   1.0000
  15.250   1.2770   0.09858   0.09690  -0.0694   0.0002   1.0000
  15.500   1.2434   0.11434   0.11286  -0.0796   0.0002   1.0000
  15.750   1.1968   0.13518   0.13384  -0.0911   0.0002   1.0000
  16.000   1.1505   0.15441   0.15314  -0.1015   0.0002   1.0000
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