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MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 117 9.8% (mh117-il)
Reynolds number: 50,000
Max Cl/Cd: 38.4 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh117-il-50000-n5.txt
Download as CSV file: xf-mh117-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 117  9.8%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4294   0.09827   0.09121  -0.0314   1.0000   0.0419
  -9.250  -0.4311   0.09396   0.08699  -0.0333   1.0000   0.0422
  -9.000  -0.4344   0.08951   0.08264  -0.0354   1.0000   0.0425
  -8.750  -0.4395   0.08484   0.07807  -0.0376   1.0000   0.0426
  -8.500  -0.4464   0.08014   0.07350  -0.0398   1.0000   0.0425
  -8.250  -0.4558   0.07539   0.06886  -0.0422   1.0000   0.0421
  -8.000  -0.4660   0.06941   0.06297  -0.0463   1.0000   0.0416
  -7.750  -0.4770   0.06351   0.05708  -0.0497   1.0000   0.0413
  -7.500  -0.4864   0.05816   0.05165  -0.0518   1.0000   0.0409
  -7.250  -0.4928   0.05300   0.04628  -0.0531   1.0000   0.0411
  -7.000  -0.4945   0.04812   0.04107  -0.0537   1.0000   0.0420
  -6.750  -0.4915   0.04350   0.03596  -0.0537   1.0000   0.0433
  -6.500  -0.4835   0.03912   0.03093  -0.0532   1.0000   0.0448
  -6.250  -0.4713   0.03616   0.02767  -0.0523   1.0000   0.0472
  -6.000  -0.4567   0.03451   0.02587  -0.0512   1.0000   0.0525
  -5.750  -0.4403   0.03186   0.02268  -0.0501   1.0000   0.0588
  -5.500  -0.4236   0.03037   0.02105  -0.0490   1.0000   0.0673
  -5.250  -0.4059   0.02888   0.01939  -0.0478   1.0000   0.0780
  -5.000  -0.3876   0.02763   0.01791  -0.0468   1.0000   0.0930
  -4.750  -0.3685   0.02654   0.01656  -0.0458   1.0000   0.1101
  -4.500  -0.3493   0.02559   0.01552  -0.0447   1.0000   0.1261
  -4.250  -0.3303   0.02489   0.01479  -0.0438   1.0000   0.1435
  -4.000  -0.3039   0.02416   0.01391  -0.0441   0.9970   0.1641
  -3.750  -0.2676   0.02343   0.01311  -0.0462   0.9892   0.1884
  -3.500  -0.2307   0.02287   0.01243  -0.0484   0.9815   0.2188
  -3.250  -0.1955   0.02233   0.01184  -0.0503   0.9729   0.2528
  -3.000  -0.1603   0.02186   0.01140  -0.0522   0.9647   0.2946
  -2.750  -0.1245   0.02140   0.01108  -0.0541   0.9566   0.3449
  -2.500  -0.0922   0.02099   0.01080  -0.0553   0.9475   0.4039
  -2.250  -0.0575   0.02059   0.01063  -0.0567   0.9399   0.4788
  -2.000  -0.0283   0.02021   0.01055  -0.0568   0.9306   0.5629
  -1.750  -0.0008   0.01986   0.01052  -0.0561   0.9219   0.6626
  -1.500   0.0296   0.01954   0.01050  -0.0553   0.9145   0.7872
  -1.250   0.0932   0.01922   0.01018  -0.0615   0.9093   0.9938
  -1.000   0.1313   0.01935   0.00997  -0.0640   0.9007   1.0000
  -0.750   0.1631   0.01950   0.00987  -0.0652   0.8905   1.0000
  -0.500   0.1986   0.01963   0.00979  -0.0669   0.8821   1.0000
  -0.250   0.2309   0.01979   0.00975  -0.0680   0.8724   1.0000
   0.000   0.2602   0.01999   0.00979  -0.0685   0.8620   1.0000
   0.250   0.2928   0.02015   0.00982  -0.0694   0.8530   1.0000
   0.500   0.3244   0.02031   0.00987  -0.0701   0.8434   1.0000
   0.750   0.3519   0.02054   0.01001  -0.0702   0.8324   1.0000
   1.000   0.3815   0.02073   0.01013  -0.0705   0.8222   1.0000
   1.250   0.4151   0.02083   0.01017  -0.0713   0.8135   1.0000
   1.500   0.4412   0.02107   0.01038  -0.0709   0.8016   1.0000
   1.750   0.4680   0.02129   0.01058  -0.0706   0.7899   1.0000
   2.000   0.4957   0.02149   0.01076  -0.0704   0.7784   1.0000
   2.250   0.5245   0.02163   0.01090  -0.0702   0.7672   1.0000
   2.500   0.5547   0.02171   0.01101  -0.0701   0.7564   1.0000
   2.750   0.5807   0.02191   0.01123  -0.0695   0.7434   1.0000
   3.000   0.6066   0.02209   0.01145  -0.0688   0.7300   1.0000
   3.250   0.6327   0.02225   0.01169  -0.0680   0.7164   1.0000
   3.500   0.6590   0.02238   0.01188  -0.0672   0.7022   1.0000
   3.750   0.6852   0.02249   0.01205  -0.0664   0.6875   1.0000
   4.000   0.7117   0.02257   0.01220  -0.0655   0.6722   1.0000
   4.250   0.7360   0.02272   0.01247  -0.0644   0.6551   1.0000
   4.500   0.7598   0.02288   0.01272  -0.0631   0.6367   1.0000
   4.750   0.7849   0.02294   0.01287  -0.0619   0.6180   1.0000
   5.000   0.8091   0.02304   0.01306  -0.0607   0.5978   1.0000
   5.250   0.8325   0.02316   0.01332  -0.0592   0.5753   1.0000
   5.500   0.8549   0.02333   0.01358  -0.0577   0.5507   1.0000
   5.750   0.8771   0.02350   0.01382  -0.0562   0.5240   1.0000
   6.000   0.8985   0.02373   0.01410  -0.0545   0.4944   1.0000
   6.250   0.9192   0.02401   0.01444  -0.0528   0.4621   1.0000
   6.500   0.9384   0.02444   0.01484  -0.0510   0.4268   1.0000
   6.750   0.9564   0.02500   0.01531  -0.0491   0.3903   1.0000
   7.000   0.9727   0.02576   0.01598  -0.0472   0.3530   1.0000
   7.250   0.9879   0.02669   0.01677  -0.0452   0.3183   1.0000
   7.500   1.0020   0.02776   0.01777  -0.0434   0.2846   1.0000
   7.750   1.0153   0.02894   0.01892  -0.0416   0.2546   1.0000
   8.000   1.0280   0.03021   0.02014  -0.0397   0.2276   1.0000
   8.250   1.0400   0.03157   0.02143  -0.0379   0.2039   1.0000
   8.500   1.0523   0.03299   0.02285  -0.0362   0.1828   1.0000
   8.750   1.0644   0.03449   0.02430  -0.0346   0.1657   1.0000
   9.000   1.0766   0.03603   0.02589  -0.0329   0.1490   1.0000
   9.250   1.0891   0.03761   0.02752  -0.0313   0.1354   1.0000
   9.500   1.1022   0.03927   0.02919  -0.0298   0.1241   1.0000
   9.750   1.1130   0.04095   0.03107  -0.0282   0.1129   1.0000
  10.000   1.1256   0.04282   0.03315  -0.0267   0.1031   1.0000
  10.250   1.1392   0.04483   0.03525  -0.0255   0.0952   1.0000
  10.500   1.1469   0.04677   0.03733  -0.0239   0.0876   1.0000
  10.750   1.1560   0.04915   0.03995  -0.0225   0.0809   1.0000
  11.000   1.1641   0.05150   0.04249  -0.0212   0.0755   1.0000
  11.250   1.1682   0.05414   0.04528  -0.0199   0.0704   1.0000
  11.500   1.1661   0.05710   0.04859  -0.0186   0.0659   1.0000
  11.750   1.1681   0.05987   0.05147  -0.0176   0.0624   1.0000
  12.000   1.1682   0.06329   0.05505  -0.0168   0.0596   1.0000
  12.250   1.1553   0.06769   0.05987  -0.0166   0.0577   1.0000
  12.500   1.1408   0.07242   0.06493  -0.0170   0.0560   1.0000
  12.750   1.1247   0.07759   0.07037  -0.0182   0.0548   1.0000
  13.000   1.1061   0.08352   0.07654  -0.0204   0.0542   1.0000
  13.250   1.0829   0.09073   0.08399  -0.0237   0.0542   1.0000
  13.500   1.0532   0.10000   0.09348  -0.0289   0.0557   1.0000
  13.750   1.0232   0.11048   0.10410  -0.0353   0.0574   1.0000
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