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MH 94 16.03% (mh94-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 94 16.03% (mh94-il)
Reynolds number: 50,000
Max Cl/Cd: 29.5 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh94-il-50000.txt
Download as CSV file: xf-mh94-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 94  16.03%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.4918   0.11562   0.10799  -0.0431   1.0000   0.1378
 -11.750  -0.4850   0.11140   0.10376  -0.0428   1.0000   0.1339
 -11.500  -0.6360   0.08448   0.07683  -0.0613   1.0000   0.1102
 -11.250  -0.6589   0.07943   0.07177  -0.0615   1.0000   0.1093
 -11.000  -0.6844   0.07496   0.06726  -0.0609   1.0000   0.1080
 -10.750  -0.7155   0.07111   0.06334  -0.0590   1.0000   0.1067
 -10.500  -0.7508   0.06803   0.06016  -0.0552   1.0000   0.1054
 -10.250  -0.7811   0.06528   0.05728  -0.0507   1.0000   0.1045
 -10.000  -0.8052   0.06218   0.05398  -0.0465   1.0000   0.1037
  -9.750  -0.8223   0.05924   0.05081  -0.0426   1.0000   0.1034
  -9.500  -0.8326   0.05644   0.04776  -0.0390   1.0000   0.1038
  -9.250  -0.8380   0.05373   0.04479  -0.0356   1.0000   0.1046
  -9.000  -0.8395   0.05107   0.04185  -0.0325   1.0000   0.1058
  -8.750  -0.8373   0.04848   0.03892  -0.0295   1.0000   0.1072
  -8.500  -0.8313   0.04595   0.03602  -0.0267   1.0000   0.1088
  -8.250  -0.8222   0.04358   0.03327  -0.0241   1.0000   0.1110
  -8.000  -0.8020   0.04148   0.03133  -0.0230   1.0000   0.1168
  -7.750  -0.7883   0.03965   0.02919  -0.0207   1.0000   0.1227
  -7.500  -0.7663   0.03776   0.02748  -0.0194   1.0000   0.1316
  -7.250  -0.7470   0.03607   0.02588  -0.0177   1.0000   0.1435
  -7.000  -0.7305   0.03449   0.02443  -0.0156   1.0000   0.1604
  -6.750  -0.7182   0.03280   0.02298  -0.0130   1.0000   0.1854
  -6.500  -0.7132   0.03087   0.02153  -0.0096   1.0000   0.2266
  -6.250  -0.7183   0.02854   0.02022  -0.0049   1.0000   0.3117
  -6.000  -0.7215   0.02803   0.02062   0.0013   1.0000   0.4288
  -5.750  -0.7117   0.02925   0.02203   0.0067   1.0000   0.4913
  -5.500  -0.6989   0.03056   0.02335   0.0116   1.0000   0.5337
  -5.250  -0.6803   0.03282   0.02568   0.0172   1.0000   0.5657
  -5.000  -0.6632   0.03475   0.02760   0.0227   1.0000   0.5954
  -4.750  -0.6415   0.03704   0.02985   0.0283   1.0000   0.6215
  -4.500  -0.6316   0.03743   0.03013   0.0325   1.0000   0.6477
  -4.250  -0.6127   0.03845   0.03107   0.0367   1.0000   0.6686
  -4.000  -0.5964   0.03884   0.03135   0.0401   1.0000   0.6882
  -3.750  -0.5829   0.03881   0.03122   0.0432   1.0000   0.7071
  -3.500  -0.5714   0.03856   0.03087   0.0461   1.0000   0.7257
  -3.250  -0.5490   0.03887   0.03107   0.0483   1.0000   0.7418
  -3.000  -0.5304   0.03881   0.03091   0.0503   1.0000   0.7585
  -2.750  -0.5139   0.03858   0.03058   0.0522   1.0000   0.7755
  -2.500  -0.4991   0.03823   0.03015   0.0540   1.0000   0.7924
  -2.250  -0.4839   0.03788   0.02971   0.0556   1.0000   0.8097
  -2.000  -0.4686   0.03753   0.02927   0.0569   1.0000   0.8268
  -1.750  -0.4520   0.03721   0.02888   0.0578   1.0000   0.8439
  -1.500  -0.4339   0.03695   0.02853   0.0584   1.0000   0.8607
  -1.250  -0.4045   0.03697   0.02846   0.0570   1.0000   0.8769
  -1.000  -0.3631   0.03722   0.02861   0.0534   1.0000   0.8917
  -0.750  -0.3201   0.03750   0.02879   0.0490   1.0000   0.9064
  -0.500  -0.2742   0.03784   0.02904   0.0437   1.0000   0.9207
  -0.250  -0.2307   0.03819   0.02933   0.0385   1.0000   0.9352
   0.000  -0.1864   0.03863   0.02971   0.0328   1.0000   0.9498
   0.250  -0.0955   0.03991   0.03090   0.0185   0.9842   0.9616
   0.500  -0.0025   0.04078   0.03171   0.0040   0.9629   0.9728
   0.750   0.0967   0.04134   0.03225  -0.0113   0.9425   0.9843
   1.000   0.1783   0.04126   0.03218  -0.0232   0.9198   0.9950
   1.250   0.2481   0.04097   0.03192  -0.0325   0.8985   1.0000
   1.500   0.3018   0.04050   0.03146  -0.0383   0.8780   1.0000
   1.750   0.3275   0.04014   0.03114  -0.0393   0.8542   1.0000
   2.000   0.3688   0.03952   0.03056  -0.0423   0.8322   1.0000
   2.250   0.4194   0.03857   0.02966  -0.0461   0.8112   1.0000
   2.500   0.4808   0.03710   0.02828  -0.0509   0.7912   1.0000
   2.750   0.5627   0.03476   0.02604  -0.0579   0.7713   1.0000
   3.000   0.5919   0.03379   0.02512  -0.0573   0.7452   1.0000
   3.250   0.6607   0.03135   0.02273  -0.0614   0.7192   1.0000
   3.500   0.7016   0.02991   0.02127  -0.0618   0.6886   1.0000
   3.750   0.7425   0.02859   0.01986  -0.0620   0.6551   1.0000
   4.000   0.7717   0.02785   0.01895  -0.0608   0.6201   1.0000
   4.250   0.7911   0.02757   0.01850  -0.0585   0.5855   1.0000
   4.500   0.8014   0.02768   0.01847  -0.0550   0.5521   1.0000
   4.750   0.8132   0.02785   0.01848  -0.0519   0.5202   1.0000
   5.000   0.8282   0.02807   0.01842  -0.0492   0.4893   1.0000
   5.250   0.8331   0.02856   0.01881  -0.0453   0.4611   1.0000
   5.500   0.8463   0.02902   0.01901  -0.0426   0.4340   1.0000
   5.750   0.8493   0.02969   0.01962  -0.0385   0.4103   1.0000
   6.000   0.8555   0.03038   0.02018  -0.0350   0.3884   1.0000
   6.250   0.8629   0.03114   0.02082  -0.0316   0.3686   1.0000
   6.500   0.8698   0.03199   0.02158  -0.0282   0.3510   1.0000
   6.750   0.8776   0.03293   0.02245  -0.0251   0.3352   1.0000
   7.000   0.8899   0.03398   0.02340  -0.0226   0.3208   1.0000
   7.250   0.9105   0.03511   0.02432  -0.0215   0.3071   1.0000
   7.500   0.9129   0.03644   0.02587  -0.0179   0.2962   1.0000
   7.750   0.9304   0.03789   0.02728  -0.0166   0.2859   1.0000
   8.000   0.9427   0.03947   0.02896  -0.0146   0.2769   1.0000
   8.250   0.9596   0.04122   0.03072  -0.0134   0.2690   1.0000
   8.500   0.9636   0.04314   0.03290  -0.0106   0.2621   1.0000
   8.750   0.9952   0.04475   0.03430  -0.0114   0.2545   1.0000
   9.000   0.9851   0.04736   0.03733  -0.0072   0.2511   1.0000
   9.250   0.9755   0.05017   0.04046  -0.0034   0.2477   1.0000
   9.500   0.9688   0.05298   0.04348  -0.0003   0.2442   1.0000
   9.750   1.0040   0.05453   0.04491  -0.0014   0.2382   1.0000
  10.000   0.9905   0.05794   0.04853   0.0020   0.2361   1.0000
  10.250   0.9568   0.06197   0.05282   0.0067   0.2357   1.0000
  10.500   0.9131   0.06692   0.05796   0.0110   0.2360   1.0000
  10.750   0.8660   0.07353   0.06468   0.0128   0.2369   1.0000
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