Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MH 95 15.86% (mh95-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 95 15.86% (mh95-il)
Reynolds number: 50,000
Max Cl/Cd: 28.97 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh95-il-50000-n5.txt
Download as CSV file: xf-mh95-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 95  15.86%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.5310   0.10114   0.09300  -0.0575   1.0000   0.0512
 -12.500  -0.5533   0.09388   0.08571  -0.0609   1.0000   0.0507
 -12.250  -0.5834   0.08654   0.07831  -0.0641   1.0000   0.0503
 -12.000  -0.6128   0.08055   0.07222  -0.0660   1.0000   0.0498
 -11.750  -0.6423   0.07552   0.06705  -0.0664   1.0000   0.0496
 -11.500  -0.6682   0.07148   0.06288  -0.0655   1.0000   0.0493
 -11.250  -0.6923   0.06808   0.05934  -0.0635   1.0000   0.0492
 -11.000  -0.7151   0.06517   0.05627  -0.0606   1.0000   0.0491
 -10.750  -0.7363   0.06270   0.05364  -0.0569   1.0000   0.0491
 -10.500  -0.7567   0.06058   0.05137  -0.0524   1.0000   0.0491
 -10.250  -0.7743   0.05864   0.04927  -0.0476   1.0000   0.0492
 -10.000  -0.7864   0.05653   0.04694  -0.0433   1.0000   0.0495
  -9.750  -0.7953   0.05437   0.04454  -0.0393   1.0000   0.0501
  -9.500  -0.8009   0.05228   0.04215  -0.0354   1.0000   0.0507
  -9.250  -0.8033   0.05024   0.03977  -0.0317   1.0000   0.0515
  -9.000  -0.7949   0.04865   0.03820  -0.0295   1.0000   0.0527
  -8.750  -0.7871   0.04708   0.03653  -0.0270   1.0000   0.0540
  -8.500  -0.7776   0.04548   0.03477  -0.0246   1.0000   0.0552
  -8.250  -0.7656   0.04385   0.03293  -0.0224   1.0000   0.0566
  -8.000  -0.7502   0.04229   0.03113  -0.0205   1.0000   0.0579
  -7.750  -0.7328   0.04088   0.02963  -0.0189   1.0000   0.0594
  -7.500  -0.7175   0.03971   0.02848  -0.0171   1.0000   0.0615
  -7.250  -0.7026   0.03865   0.02733  -0.0151   1.0000   0.0645
  -7.000  -0.6873   0.03762   0.02622  -0.0131   1.0000   0.0678
  -6.750  -0.6749   0.03665   0.02528  -0.0108   1.0000   0.0712
  -6.500  -0.6614   0.03574   0.02425  -0.0085   1.0000   0.0755
  -6.250  -0.6513   0.03477   0.02334  -0.0060   1.0000   0.0800
  -6.000  -0.6414   0.03388   0.02240  -0.0034   1.0000   0.0871
  -5.750  -0.6332   0.03290   0.02147  -0.0007   1.0000   0.0957
  -5.500  -0.6253   0.03190   0.02056   0.0021   1.0000   0.1080
  -5.250  -0.6188   0.03072   0.01963   0.0049   1.0000   0.1297
  -5.000  -0.6135   0.02943   0.01875   0.0077   1.0000   0.1725
  -4.750  -0.6016   0.02792   0.01798   0.0090   0.9964   0.2716
  -4.500  -0.5827   0.02676   0.01765   0.0094   0.9894   0.4011
  -4.250  -0.5582   0.02662   0.01828   0.0107   0.9829   0.5242
  -4.000  -0.5309   0.02749   0.01954   0.0128   0.9758   0.6193
  -3.750  -0.5009   0.02855   0.02053   0.0139   0.9687   0.6803
  -3.500  -0.4742   0.02932   0.02116   0.0153   0.9603   0.7152
  -3.250  -0.4364   0.03025   0.02188   0.0147   0.9540   0.7388
  -3.000  -0.4064   0.03076   0.02222   0.0151   0.9456   0.7586
  -2.750  -0.3665   0.03139   0.02264   0.0136   0.9393   0.7772
  -2.500  -0.3377   0.03172   0.02280   0.0138   0.9300   0.7940
  -2.250  -0.2957   0.03217   0.02306   0.0117   0.9237   0.8101
  -2.000  -0.2706   0.03230   0.02305   0.0123   0.9133   0.8259
  -1.750  -0.2169   0.03276   0.02334   0.0081   0.9079   0.8368
  -1.500  -0.1866   0.03284   0.02330   0.0076   0.8973   0.8491
  -1.250  -0.1483   0.03288   0.02320   0.0056   0.8897   0.8620
  -1.000  -0.1040   0.03300   0.02321   0.0026   0.8799   0.8705
  -0.750  -0.0655   0.03294   0.02305   0.0005   0.8711   0.8813
  -0.500  -0.0192   0.03290   0.02292  -0.0030   0.8614   0.8892
  -0.250   0.0155   0.03274   0.02269  -0.0045   0.8505   0.8986
   0.000   0.0715   0.03251   0.02238  -0.0098   0.8422   0.9043
   0.250   0.0994   0.03229   0.02212  -0.0101   0.8292   0.9136
   0.500   0.1560   0.03188   0.02166  -0.0153   0.8205   0.9181
   0.750   0.1961   0.03149   0.02124  -0.0176   0.8083   0.9248
   1.000   0.2327   0.03111   0.02085  -0.0192   0.7949   0.9312
   1.250   0.2813   0.03054   0.02026  -0.0229   0.7832   0.9358
   1.500   0.3271   0.02992   0.01964  -0.0258   0.7714   0.9411
   2.000   0.4077   0.02895   0.01868  -0.0301   0.7395   0.9508
   2.250   0.4429   0.02849   0.01823  -0.0313   0.7225   0.9564
   2.500   0.4857   0.02796   0.01769  -0.0337   0.7042   0.9603
   2.750   0.5272   0.02746   0.01718  -0.0360   0.6844   0.9646
   3.000   0.5645   0.02706   0.01673  -0.0374   0.6638   0.9691
   3.250   0.5991   0.02682   0.01649  -0.0387   0.6395   0.9737
   3.500   0.6340   0.02659   0.01620  -0.0398   0.6144   0.9783
   3.750   0.6669   0.02644   0.01596  -0.0407   0.5893   0.9829
   4.000   0.6981   0.02641   0.01588  -0.0415   0.5617   0.9877
   4.250   0.7281   0.02644   0.01579  -0.0420   0.5350   0.9927
   4.500   0.7564   0.02657   0.01584  -0.0425   0.5069   0.9979
   4.750   0.7754   0.02677   0.01592  -0.0411   0.4829   1.0000
   5.000   0.7834   0.02707   0.01616  -0.0378   0.4612   1.0000
   5.250   0.7907   0.02739   0.01640  -0.0344   0.4406   1.0000
   5.500   0.7973   0.02772   0.01665  -0.0310   0.4213   1.0000
   5.750   0.8030   0.02807   0.01693  -0.0274   0.4031   1.0000
   6.000   0.8078   0.02843   0.01724  -0.0236   0.3862   1.0000
   6.250   0.8115   0.02880   0.01754  -0.0198   0.3702   1.0000
   6.500   0.8151   0.02918   0.01784  -0.0159   0.3557   1.0000
   6.750   0.8176   0.02956   0.01815  -0.0119   0.3419   1.0000
   7.000   0.8175   0.02995   0.01854  -0.0074   0.3286   1.0000
   7.250   0.8173   0.03033   0.01888  -0.0030   0.3164   1.0000
   7.500   0.8189   0.03072   0.01919   0.0012   0.3048   1.0000
   7.750   0.8199   0.03119   0.01966   0.0052   0.2929   1.0000
   8.000   0.8258   0.03176   0.02020   0.0084   0.2813   1.0000
   8.250   0.8355   0.03237   0.02071   0.0109   0.2702   1.0000
   8.500   0.8444   0.03311   0.02147   0.0134   0.2583   1.0000
   8.750   0.8562   0.03392   0.02229   0.0153   0.2475   1.0000
   9.000   0.8713   0.03470   0.02295   0.0167   0.2380   1.0000
   9.250   0.8820   0.03570   0.02405   0.0186   0.2277   1.0000
   9.500   0.8974   0.03659   0.02489   0.0198   0.2194   1.0000
   9.750   0.9098   0.03770   0.02610   0.0213   0.2109   1.0000
  10.000   0.9275   0.03865   0.02696   0.0221   0.2040   1.0000
  10.250   0.9373   0.03996   0.02847   0.0237   0.1968   1.0000
  10.500   0.9539   0.04098   0.02943   0.0246   0.1907   1.0000
  10.750   0.9654   0.04240   0.03099   0.0258   0.1851   1.0000
  11.000   0.9756   0.04388   0.03260   0.0271   0.1799   1.0000
  11.250   0.9924   0.04503   0.03374   0.0278   0.1753   1.0000
  11.500   1.0017   0.04667   0.03551   0.0290   0.1712   1.0000
  11.750   1.0032   0.04870   0.03777   0.0307   0.1671   1.0000
  12.000   1.0098   0.05045   0.03964   0.0318   0.1633   1.0000
  12.250   1.0253   0.05184   0.04104   0.0324   0.1601   1.0000
  12.500   1.0304   0.05396   0.04328   0.0334   0.1574   1.0000
  12.750   1.0160   0.05729   0.04693   0.0349   0.1551   1.0000
  13.000   0.9992   0.06102   0.05092   0.0360   0.1527   1.0000
  13.250   0.9822   0.06510   0.05521   0.0364   0.1506   1.0000
  13.500   0.9666   0.06934   0.05961   0.0362   0.1484   1.0000
  13.750   0.9682   0.07206   0.06239   0.0361   0.1461   1.0000
  14.000   0.9737   0.07463   0.06499   0.0359   0.1441   1.0000
  14.250   0.7312   0.11805   0.10886   0.0137   0.1413   1.0000
  14.500   0.7029   0.12843   0.11925   0.0084   0.1389   1.0000
<< Back to MH 95 15.86% (mh95-il)

Polar data table (+)

Polar graphs


<< Back to MH 95 15.86% (mh95-il)