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MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 122 9.32% (mh122-il)
Reynolds number: 500,000
Max Cl/Cd: 137.68 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh122-il-500000.txt
Download as CSV file: xf-mh122-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.3263   0.14596   0.14379  -0.0326   1.0000   0.0095
 -13.000  -0.3283   0.14411   0.14195  -0.0318   1.0000   0.0096
 -12.750  -0.3295   0.14200   0.13987  -0.0313   0.9999   0.0098
 -12.500  -0.3224   0.13850   0.13636  -0.0335   0.9991   0.0101
 -12.250  -0.3155   0.13489   0.13275  -0.0357   0.9983   0.0104
 -12.000  -0.3092   0.13127   0.12912  -0.0379   0.9975   0.0107
 -11.750  -0.3027   0.12750   0.12535  -0.0402   0.9966   0.0111
 -11.500  -0.2965   0.12370   0.12155  -0.0426   0.9957   0.0115
 -11.250  -0.2901   0.11985   0.11770  -0.0452   0.9949   0.0117
 -11.000  -0.2835   0.11595   0.11379  -0.0480   0.9942   0.0120
 -10.750  -0.2763   0.11214   0.10998  -0.0502   0.9928   0.0122
 -10.500  -0.2692   0.10813   0.10594  -0.0526   0.9912   0.0124
 -10.250  -0.2623   0.10398   0.10179  -0.0550   0.9896   0.0124
 -10.000  -0.2551   0.09966   0.09748  -0.0575   0.9881   0.0125
  -9.750  -0.2480   0.09524   0.09305  -0.0602   0.9867   0.0125
  -9.500  -0.2407   0.09063   0.08844  -0.0630   0.9854   0.0126
  -9.250  -0.2332   0.08582   0.08364  -0.0660   0.9842   0.0126
  -9.000  -0.2254   0.08094   0.07876  -0.0693   0.9832   0.0126
  -8.750  -0.2171   0.07587   0.07369  -0.0729   0.9823   0.0126
  -8.500  -0.2152   0.07137   0.06920  -0.0748   0.9772   0.0126
  -8.250  -0.2229   0.06308   0.06096  -0.0791   0.9743   0.0131
  -8.000  -0.2225   0.05640   0.05429  -0.0840   0.9721   0.0134
  -7.750  -0.2167   0.05007   0.04796  -0.0902   0.9703   0.0136
  -7.500  -0.2214   0.04310   0.04097  -0.0976   0.9621   0.0134
  -7.250  -0.2137   0.03548   0.03316  -0.1103   0.9586   0.0135
  -4.750  -0.0053   0.01601   0.01070  -0.1348   0.9332   0.0107
  -4.500   0.0270   0.01333   0.00768  -0.1354   0.9318   0.0085
  -4.250   0.0488   0.01213   0.00628  -0.1340   0.9269   0.0077
  -4.000   0.0779   0.01121   0.00523  -0.1344   0.9241   0.0075
  -3.750   0.1093   0.01045   0.00434  -0.1353   0.9219   0.0077
  -3.500   0.1416   0.00989   0.00364  -0.1363   0.9201   0.0089
  -3.250   0.1740   0.00915   0.00302  -0.1374   0.9183   0.0683
  -3.000   0.1957   0.00782   0.00285  -0.1376   0.9139   0.3919
  -2.750   0.2239   0.00761   0.00287  -0.1379   0.9111   0.4836
  -2.500   0.2542   0.00756   0.00277  -0.1384   0.9088   0.5078
  -2.250   0.2851   0.00751   0.00273  -0.1391   0.9067   0.5356
  -2.000   0.3147   0.00749   0.00271  -0.1396   0.9045   0.5562
  -1.750   0.3396   0.00752   0.00278  -0.1390   0.9008   0.5786
  -1.500   0.3674   0.00751   0.00278  -0.1391   0.8977   0.5967
  -1.250   0.3969   0.00748   0.00275  -0.1395   0.8953   0.6106
  -1.000   0.4274   0.00746   0.00273  -0.1401   0.8931   0.6228
  -0.750   0.4550   0.00747   0.00276  -0.1402   0.8901   0.6348
  -0.500   0.4809   0.00748   0.00281  -0.1398   0.8861   0.6472
  -0.250   0.5095   0.00745   0.00281  -0.1400   0.8827   0.6605
   0.000   0.5399   0.00741   0.00279  -0.1406   0.8798   0.6747
   0.250   0.5660   0.00741   0.00284  -0.1402   0.8753   0.6897
   0.500   0.5929   0.00736   0.00286  -0.1400   0.8703   0.7062
   0.750   0.6233   0.00729   0.00282  -0.1405   0.8660   0.7244
   1.000   0.6477   0.00724   0.00287  -0.1396   0.8594   0.7438
   1.250   0.6766   0.00714   0.00281  -0.1397   0.8533   0.7659
   1.500   0.7008   0.00705   0.00283  -0.1387   0.8451   0.7902
   1.750   0.7271   0.00693   0.00277  -0.1381   0.8364   0.8184
   2.000   0.7511   0.00678   0.00275  -0.1370   0.8260   0.8515
   2.250   0.7707   0.00664   0.00276  -0.1348   0.8161   0.8968
   2.500   0.7979   0.00647   0.00270  -0.1344   0.8071   1.0000
   2.750   0.8249   0.00648   0.00270  -0.1342   0.7968   1.0000
   3.000   0.8507   0.00650   0.00275  -0.1337   0.7841   1.0000
   3.250   0.8750   0.00652   0.00280  -0.1329   0.7671   1.0000
   3.500   0.8994   0.00657   0.00283  -0.1320   0.7460   1.0000
   3.750   0.9211   0.00669   0.00287  -0.1306   0.7076   1.0000
   4.000   0.9373   0.00709   0.00297  -0.1279   0.6356   1.0000
   4.250   0.9425   0.00809   0.00337  -0.1233   0.5185   1.0000
   4.500   0.9479   0.00928   0.00394  -0.1191   0.3957   1.0000
   4.750   0.9590   0.01031   0.00452  -0.1162   0.2953   1.0000
   5.000   0.9725   0.01129   0.00506  -0.1138   0.2086   1.0000
   5.250   0.9880   0.01217   0.00559  -0.1118   0.1417   1.0000
   5.500   1.0063   0.01287   0.00609  -0.1102   0.1021   1.0000
   5.750   1.0257   0.01349   0.00660  -0.1088   0.0767   1.0000
   6.000   1.0454   0.01409   0.00713  -0.1075   0.0577   1.0000
   6.250   1.0647   0.01469   0.00768  -0.1060   0.0435   1.0000
   6.500   1.0839   0.01524   0.00821  -0.1046   0.0326   1.0000
   6.750   1.1027   0.01583   0.00878  -0.1031   0.0238   1.0000
   7.000   1.1199   0.01662   0.00955  -0.1012   0.0136   1.0000
   7.250   1.1339   0.01781   0.01084  -0.0987   0.0074   1.0000
   7.500   1.1529   0.01841   0.01147  -0.0973   0.0056   1.0000
   7.750   1.1641   0.01998   0.01319  -0.0944   0.0044   1.0000
   8.000   1.1776   0.02142   0.01479  -0.0920   0.0040   1.0000
   8.250   1.1948   0.02240   0.01588  -0.0903   0.0036   1.0000
   8.500   1.2112   0.02360   0.01723  -0.0885   0.0031   1.0000
   8.750   1.2272   0.02504   0.01883  -0.0867   0.0028   1.0000
   9.000   1.2427   0.02670   0.02068  -0.0849   0.0026   1.0000
   9.250   1.2572   0.02870   0.02290  -0.0829   0.0025   1.0000
   9.500   1.2695   0.03103   0.02550  -0.0807   0.0024   1.0000
   9.750   1.2779   0.03404   0.02888  -0.0780   0.0024   1.0000
  10.000   1.2774   0.03835   0.03370  -0.0741   0.0025   1.0000
  10.250   1.2617   0.04408   0.04000  -0.0685   0.0027   1.0000
  10.500   1.2399   0.04940   0.04577  -0.0631   0.0029   1.0000
  10.750   1.2180   0.05426   0.05097  -0.0588   0.0030   1.0000
  11.000   1.1946   0.05927   0.05626  -0.0555   0.0032   1.0000
  11.250   1.1720   0.06435   0.06159  -0.0534   0.0032   1.0000
  11.500   1.1496   0.06974   0.06719  -0.0525   0.0033   1.0000
  11.750   1.1277   0.07555   0.07318  -0.0530   0.0033   1.0000
  12.000   1.1063   0.08199   0.07979  -0.0548   0.0033   1.0000
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