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MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 117 9.8% (mh117-il)
Reynolds number: 100,000
Max Cl/Cd: 55.75 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh117-il-100000-n5.txt
Download as CSV file: xf-mh117-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4539   0.08926   0.08425  -0.0333   1.0000   0.0179
  -9.500  -0.4599   0.08395   0.07901  -0.0356   1.0000   0.0178
  -9.250  -0.4674   0.07858   0.07371  -0.0381   1.0000   0.0177
  -9.000  -0.4787   0.07258   0.06781  -0.0411   1.0000   0.0175
  -8.750  -0.4961   0.06571   0.06102  -0.0448   1.0000   0.0173
  -8.500  -0.5170   0.05740   0.05279  -0.0518   1.0000   0.0169
  -8.250  -0.5340   0.05100   0.04621  -0.0556   1.0000   0.0166
  -8.000  -0.5466   0.04538   0.04028  -0.0571   1.0000   0.0165
  -7.750  -0.5511   0.04065   0.03516  -0.0571   1.0000   0.0165
  -7.500  -0.5489   0.03674   0.03080  -0.0563   1.0000   0.0167
  -7.250  -0.5420   0.03342   0.02701  -0.0551   1.0000   0.0170
  -7.000  -0.5313   0.03069   0.02378  -0.0536   1.0000   0.0175
  -6.750  -0.5188   0.02849   0.02128  -0.0523   1.0000   0.0187
  -6.500  -0.5043   0.02723   0.01992  -0.0510   1.0000   0.0205
  -6.250  -0.4750   0.02549   0.01785  -0.0523   0.9956   0.0231
  -6.000  -0.4414   0.02344   0.01541  -0.0539   0.9894   0.0255
  -5.750  -0.4071   0.02193   0.01379  -0.0561   0.9831   0.0310
  -5.500  -0.3743   0.02062   0.01235  -0.0576   0.9758   0.0404
  -5.250  -0.3382   0.01960   0.01115  -0.0596   0.9697   0.0579
  -5.000  -0.3055   0.01888   0.01043  -0.0610   0.9615   0.0785
  -4.750  -0.2686   0.01827   0.00973  -0.0632   0.9557   0.0999
  -4.500  -0.2361   0.01770   0.00912  -0.0643   0.9474   0.1175
  -4.250  -0.1990   0.01715   0.00848  -0.0663   0.9419   0.1371
  -4.000  -0.1676   0.01665   0.00797  -0.0672   0.9331   0.1571
  -3.750  -0.1315   0.01618   0.00745  -0.0689   0.9272   0.1811
  -3.500  -0.1013   0.01577   0.00708  -0.0695   0.9176   0.2080
  -3.250  -0.0682   0.01537   0.00673  -0.0706   0.9103   0.2399
  -3.000  -0.0368   0.01501   0.00641  -0.0713   0.9016   0.2772
  -2.750  -0.0063   0.01467   0.00617  -0.0719   0.8928   0.3190
  -2.500   0.0257   0.01434   0.00593  -0.0726   0.8852   0.3676
  -2.250   0.0537   0.01404   0.00577  -0.0726   0.8753   0.4205
  -2.000   0.0833   0.01374   0.00563  -0.0727   0.8669   0.4817
  -1.750   0.1111   0.01346   0.00553  -0.0724   0.8580   0.5485
  -1.500   0.1370   0.01321   0.00548  -0.0716   0.8483   0.6209
  -1.250   0.1633   0.01296   0.00542  -0.0706   0.8400   0.6988
  -1.000   0.1877   0.01277   0.00541  -0.0690   0.8305   0.7781
  -0.750   0.2171   0.01262   0.00536  -0.0684   0.8216   0.8606
  -0.500   0.2623   0.01247   0.00517  -0.0712   0.8143   0.9400
  -0.250   0.3088   0.01241   0.00501  -0.0751   0.8048   1.0000
   0.000   0.3344   0.01248   0.00495  -0.0746   0.7949   1.0000
   0.250   0.3607   0.01255   0.00489  -0.0741   0.7854   1.0000
   0.500   0.3856   0.01266   0.00491  -0.0735   0.7742   1.0000
   0.750   0.4111   0.01276   0.00492  -0.0729   0.7634   1.0000
   1.000   0.4371   0.01286   0.00494  -0.0724   0.7530   1.0000
   1.250   0.4634   0.01295   0.00495  -0.0719   0.7427   1.0000
   1.500   0.4887   0.01307   0.00502  -0.0713   0.7309   1.0000
   1.750   0.5143   0.01320   0.00510  -0.0707   0.7192   1.0000
   2.000   0.5401   0.01332   0.00518  -0.0701   0.7075   1.0000
   2.250   0.5660   0.01344   0.00528  -0.0696   0.6957   1.0000
   2.500   0.5919   0.01356   0.00537  -0.0690   0.6835   1.0000
   2.750   0.6177   0.01368   0.00546  -0.0684   0.6706   1.0000
   3.000   0.6433   0.01381   0.00560  -0.0677   0.6570   1.0000
   3.250   0.6687   0.01395   0.00574  -0.0670   0.6424   1.0000
   3.500   0.6938   0.01410   0.00590  -0.0663   0.6269   1.0000
   3.750   0.7189   0.01426   0.00608  -0.0656   0.6103   1.0000
   4.000   0.7438   0.01442   0.00627  -0.0649   0.5926   1.0000
   4.250   0.7687   0.01459   0.00644  -0.0641   0.5740   1.0000
   4.500   0.7930   0.01478   0.00666  -0.0632   0.5531   1.0000
   4.750   0.8171   0.01499   0.00685  -0.0623   0.5305   1.0000
   5.000   0.8406   0.01524   0.00713  -0.0614   0.5044   1.0000
   5.250   0.8636   0.01553   0.00738  -0.0603   0.4752   1.0000
   5.500   0.8859   0.01589   0.00768  -0.0592   0.4423   1.0000
   5.750   0.9072   0.01633   0.00802  -0.0580   0.4058   1.0000
   6.000   0.9277   0.01687   0.00847  -0.0567   0.3679   1.0000
   6.250   0.9474   0.01751   0.00896  -0.0554   0.3308   1.0000
   6.500   0.9668   0.01820   0.00954  -0.0541   0.2955   1.0000
   6.750   0.9854   0.01897   0.01018  -0.0528   0.2624   1.0000
   7.000   1.0042   0.01974   0.01088  -0.0516   0.2319   1.0000
   7.250   1.0225   0.02056   0.01162  -0.0503   0.2045   1.0000
   7.500   1.0403   0.02142   0.01247  -0.0490   0.1803   1.0000
   7.750   1.0579   0.02230   0.01332  -0.0477   0.1578   1.0000
   8.000   1.0743   0.02327   0.01424  -0.0462   0.1391   1.0000
   8.250   1.0904   0.02426   0.01522  -0.0448   0.1236   1.0000
   8.500   1.1058   0.02528   0.01626  -0.0432   0.1097   1.0000
   9.000   1.1347   0.02745   0.01854  -0.0400   0.0885   1.0000
   9.250   1.1476   0.02862   0.01981  -0.0382   0.0801   1.0000
   9.500   1.1573   0.02988   0.02109  -0.0362   0.0732   1.0000
   9.750   1.1687   0.03109   0.02246  -0.0341   0.0669   1.0000
  10.000   1.1762   0.03247   0.02387  -0.0320   0.0615   1.0000
  10.250   1.1858   0.03387   0.02544  -0.0301   0.0560   1.0000
  10.500   1.1935   0.03538   0.02705  -0.0282   0.0516   1.0000
  10.750   1.1984   0.03721   0.02893  -0.0263   0.0477   1.0000
  11.000   1.2060   0.03884   0.03080  -0.0248   0.0430   1.0000
  11.250   1.2095   0.04071   0.03276  -0.0233   0.0395   1.0000
  11.500   1.2122   0.04295   0.03512  -0.0219   0.0364   1.0000
  11.750   1.2158   0.04509   0.03751  -0.0208   0.0327   1.0000
  12.000   1.2163   0.04747   0.04006  -0.0200   0.0302   1.0000
  12.250   1.2125   0.05045   0.04307  -0.0193   0.0280   1.0000
  12.500   1.2128   0.05335   0.04631  -0.0188   0.0257   1.0000
  12.750   1.2103   0.05660   0.04978  -0.0186   0.0239   1.0000
  13.000   1.2060   0.06010   0.05346  -0.0188   0.0226   1.0000
  13.250   1.1994   0.06389   0.05737  -0.0196   0.0213   1.0000
  13.500   1.1911   0.06814   0.06172  -0.0207   0.0205   1.0000
  13.750   1.1815   0.07299   0.06676  -0.0220   0.0197   1.0000
  14.000   1.1703   0.07834   0.07241  -0.0240   0.0190   1.0000
  14.250   1.1569   0.08434   0.07866  -0.0266   0.0185   1.0000
  14.500   1.1425   0.09087   0.08543  -0.0298   0.0182   1.0000
  14.750   1.1261   0.09821   0.09300  -0.0338   0.0179   1.0000
  15.000   1.1088   0.10621   0.10119  -0.0384   0.0180   1.0000
  15.250   1.0886   0.11544   0.11062  -0.0439   0.0182   1.0000
  15.500   1.0686   0.12517   0.12051  -0.0498   0.0187   1.0000
  15.750   1.0477   0.13576   0.13122  -0.0562   0.0192   1.0000
  16.000   1.0279   0.14657   0.14210  -0.0626   0.0197   1.0000
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