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MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH 122 9.32% (mh122-il)
Reynolds number: 1,000,000
Max Cl/Cd: 161.21 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh122-il-1000000.txt
Download as CSV file: xf-mh122-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4151   0.14078   0.13907  -0.0308   1.0000   0.0050
 -12.000  -0.4130   0.13773   0.13604  -0.0311   1.0000   0.0051
 -11.750  -0.4120   0.13475   0.13307  -0.0311   1.0000   0.0051
 -11.500  -0.4065   0.13124   0.12958  -0.0325   0.9998   0.0054
 -11.250  -0.3955   0.12710   0.12543  -0.0357   0.9991   0.0056
 -11.000  -0.3857   0.12283   0.12117  -0.0388   0.9983   0.0056
 -10.750  -0.3753   0.11867   0.11700  -0.0420   0.9974   0.0056
 -10.500  -0.3627   0.11470   0.11304  -0.0455   0.9965   0.0059
 -10.250  -0.3510   0.11063   0.10897  -0.0489   0.9956   0.0060
 -10.000  -0.3391   0.10647   0.10480  -0.0525   0.9948   0.0060
  -6.750  -0.1683   0.03040   0.02780  -0.1364   0.9419   0.0068
  -6.500  -0.1469   0.02676   0.02387  -0.1389   0.9347   0.0072
  -6.250  -0.1234   0.02451   0.02140  -0.1402   0.9289   0.0076
  -6.000  -0.1007   0.02248   0.01915  -0.1407   0.9227   0.0082
  -5.750  -0.0752   0.02042   0.01682  -0.1414   0.9179   0.0090
  -5.500  -0.0520   0.01874   0.01493  -0.1410   0.9123   0.0100
  -5.250  -0.0249   0.01762   0.01361  -0.1409   0.9080   0.0115
  -5.000   0.0054   0.01818   0.01404  -0.1410   0.9047   0.0126
  -4.750   0.0249   0.01350   0.00890  -0.1406   0.8998   0.0148
  -4.500   0.0524   0.01099   0.00613  -0.1392   0.8960   0.0058
  -4.250   0.0786   0.00936   0.00426  -0.1389   0.8925   0.0049
  -4.000   0.1051   0.00849   0.00324  -0.1387   0.8891   0.0045
  -3.750   0.1325   0.00797   0.00258  -0.1386   0.8858   0.0044
  -3.500   0.1606   0.00764   0.00214  -0.1387   0.8828   0.0045
  -3.250   0.1894   0.00742   0.00182  -0.1389   0.8800   0.0053
  -2.750   0.2440   0.00614   0.00132  -0.1397   0.8743   0.2552
  -2.500   0.2711   0.00559   0.00128  -0.1401   0.8713   0.4237
  -2.250   0.2993   0.00549   0.00126  -0.1403   0.8687   0.4670
  -2.000   0.3281   0.00546   0.00124  -0.1406   0.8662   0.4893
  -1.750   0.3562   0.00543   0.00125  -0.1408   0.8636   0.5109
  -1.500   0.3839   0.00540   0.00124  -0.1409   0.8607   0.5320
  -1.250   0.4120   0.00538   0.00125  -0.1410   0.8578   0.5500
  -1.000   0.4402   0.00536   0.00125  -0.1411   0.8548   0.5648
  -0.750   0.4688   0.00537   0.00125  -0.1413   0.8513   0.5772
  -0.500   0.4958   0.00535   0.00126  -0.1412   0.8470   0.5884
  -0.250   0.5235   0.00532   0.00125  -0.1412   0.8424   0.5993
   0.000   0.5516   0.00533   0.00126  -0.1413   0.8377   0.6109
   0.250   0.5783   0.00529   0.00126  -0.1411   0.8321   0.6229
   0.500   0.6060   0.00528   0.00127  -0.1411   0.8264   0.6358
   0.750   0.6327   0.00526   0.00129  -0.1408   0.8199   0.6495
   1.000   0.6598   0.00525   0.00129  -0.1407   0.8128   0.6644
   1.250   0.6858   0.00521   0.00131  -0.1403   0.8037   0.6805
   1.500   0.7121   0.00520   0.00133  -0.1399   0.7939   0.6976
   1.750   0.7387   0.00519   0.00139  -0.1396   0.7854   0.7161
   2.000   0.7650   0.00517   0.00145  -0.1393   0.7758   0.7369
   2.250   0.7909   0.00517   0.00151  -0.1389   0.7642   0.7591
   2.500   0.8159   0.00517   0.00158  -0.1383   0.7488   0.7844
   2.750   0.8399   0.00521   0.00165  -0.1374   0.7276   0.8131
   3.250   0.8726   0.00569   0.00195  -0.1323   0.6157   0.8977
   3.500   0.8835   0.00627   0.00223  -0.1287   0.5247   1.0000
   3.750   0.8972   0.00711   0.00261  -0.1261   0.4251   1.0000
   4.000   0.9113   0.00800   0.00302  -0.1236   0.3232   1.0000
   4.250   0.9290   0.00870   0.00339  -0.1219   0.2494   1.0000
   4.500   0.9470   0.00940   0.00377  -0.1202   0.1820   1.0000
   4.750   0.9664   0.01001   0.00416  -0.1188   0.1314   1.0000
   5.000   0.9875   0.01050   0.00450  -0.1178   0.1003   1.0000
   5.250   1.0095   0.01092   0.00483  -0.1168   0.0782   1.0000
   5.500   1.0313   0.01135   0.00518  -0.1158   0.0589   1.0000
   5.750   1.0529   0.01180   0.00553  -0.1148   0.0427   1.0000
   6.000   1.0740   0.01229   0.00591  -0.1137   0.0279   1.0000
   6.250   1.0959   0.01269   0.00629  -0.1128   0.0204   1.0000
   6.500   1.1176   0.01310   0.00668  -0.1118   0.0141   1.0000
   6.750   1.1360   0.01385   0.00734  -0.1102   0.0041   1.0000
   7.000   1.1566   0.01436   0.00794  -0.1089   0.0031   1.0000
   7.250   1.1756   0.01497   0.00861  -0.1073   0.0024   1.0000
   7.500   1.1908   0.01604   0.00984  -0.1049   0.0018   1.0000
   7.750   1.2108   0.01648   0.01032  -0.1037   0.0016   1.0000
   8.000   1.2290   0.01713   0.01105  -0.1020   0.0014   1.0000
   8.250   1.2463   0.01789   0.01189  -0.1002   0.0012   1.0000
   8.500   1.2627   0.01877   0.01287  -0.0983   0.0011   1.0000
   8.750   1.2785   0.01974   0.01395  -0.0964   0.0010   1.0000
   9.000   1.2931   0.02084   0.01518  -0.0942   0.0010   1.0000
   9.250   1.3065   0.02213   0.01662  -0.0920   0.0009   1.0000
   9.500   1.3187   0.02364   0.01831  -0.0895   0.0009   1.0000
   9.750   1.3300   0.02530   0.02017  -0.0871   0.0009   1.0000
  10.000   1.3391   0.02730   0.02244  -0.0843   0.0009   1.0000
  10.250   1.3451   0.02976   0.02520  -0.0811   0.0009   1.0000
  10.500   1.3379   0.03441   0.03038  -0.0762   0.0010   1.0000
  10.750   1.3066   0.04164   0.03830  -0.0687   0.0012   1.0000
  11.000   1.2772   0.04739   0.04448  -0.0629   0.0013   1.0000
  11.250   1.2522   0.05240   0.04979  -0.0589   0.0014   1.0000
  11.500   1.2271   0.05759   0.05524  -0.0560   0.0015   1.0000
  11.750   1.2039   0.06286   0.06069  -0.0545   0.0015   1.0000
  12.000   1.1809   0.06860   0.06662  -0.0542   0.0015   1.0000
  12.250   1.1578   0.07498   0.07317  -0.0553   0.0015   1.0000
  12.500   1.1380   0.08171   0.08005  -0.0578   0.0015   1.0000
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