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MH 93 15.98% (mh93-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 93 15.98% (mh93-il)
Reynolds number: 100,000
Max Cl/Cd: 33.36 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh93-il-100000.txt
Download as CSV file: xf-mh93-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 93  15.98%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6802   0.08055   0.07580  -0.0197   1.0000   0.0725
 -11.000  -0.7445   0.07188   0.06683  -0.0236   1.0000   0.0696
 -10.750  -0.7783   0.06649   0.06114  -0.0229   1.0000   0.0650
 -10.500  -0.7985   0.06221   0.05667  -0.0211   1.0000   0.0628
 -10.250  -0.8523   0.05802   0.05172  -0.0147   1.0000   0.0582
 -10.000  -0.8437   0.05413   0.04774  -0.0138   1.0000   0.0570
  -9.750  -0.8436   0.05054   0.04387  -0.0117   1.0000   0.0555
  -9.500  -0.8443   0.04683   0.03971  -0.0090   1.0000   0.0538
  -9.250  -0.8496   0.04354   0.03560  -0.0049   1.0000   0.0519
  -9.000  -0.8359   0.04121   0.03290  -0.0031   1.0000   0.0515
  -8.750  -0.8154   0.03839   0.02985  -0.0024   1.0000   0.0517
  -8.500  -0.7904   0.03575   0.02710  -0.0024   1.0000   0.0523
  -8.250  -0.7636   0.03363   0.02494  -0.0025   1.0000   0.0533
  -8.000  -0.7380   0.03197   0.02326  -0.0025   1.0000   0.0555
  -7.750  -0.7178   0.03066   0.02172  -0.0015   1.0000   0.0584
  -7.500  -0.6959   0.02904   0.02023  -0.0011   1.0000   0.0608
  -7.250  -0.6949   0.02841   0.01964   0.0026   1.0000   0.0627
  -7.000  -0.6759   0.02740   0.01859   0.0033   0.9959   0.0659
  -6.750  -0.6238   0.02546   0.01680  -0.0016   0.9847   0.0754
  -6.500  -0.5780   0.02340   0.01499  -0.0058   0.9726   0.0912
  -6.250  -0.5441   0.02117   0.01319  -0.0081   0.9572   0.1342
  -6.000  -0.5406   0.01849   0.01192  -0.0056   0.9357   0.3180
  -5.750  -0.5282   0.01777   0.01174  -0.0028   0.9161   0.4325
  -5.500  -0.5129   0.01758   0.01174   0.0001   0.8982   0.4992
  -5.250  -0.4968   0.01755   0.01184   0.0032   0.8813   0.5503
  -5.000  -0.4784   0.01766   0.01206   0.0062   0.8652   0.5949
  -4.750  -0.4584   0.01793   0.01238   0.0091   0.8499   0.6349
  -4.500  -0.4356   0.01838   0.01285   0.0118   0.8354   0.6699
  -4.250  -0.4107   0.01899   0.01341   0.0145   0.8220   0.6996
  -4.000  -0.3823   0.01969   0.01402   0.0166   0.8085   0.7229
  -3.750  -0.3526   0.02033   0.01455   0.0181   0.7938   0.7422
  -3.500  -0.3198   0.02100   0.01508   0.0191   0.7798   0.7577
  -3.250  -0.2874   0.02159   0.01552   0.0202   0.7670   0.7720
  -3.000  -0.2576   0.02205   0.01580   0.0215   0.7542   0.7866
  -2.750  -0.2290   0.02244   0.01606   0.0224   0.7397   0.8017
  -2.500  -0.1811   0.02310   0.01655   0.0207   0.7255   0.8089
  -2.250  -0.1512   0.02330   0.01658   0.0214   0.7133   0.8221
  -2.000  -0.1235   0.02346   0.01660   0.0222   0.7001   0.8363
  -1.750  -0.0687   0.02377   0.01675   0.0185   0.6847   0.8419
  -1.500  -0.0419   0.02383   0.01667   0.0191   0.6720   0.8559
  -1.250   0.0075   0.02392   0.01656   0.0162   0.6588   0.8628
  -1.000   0.0375   0.02391   0.01644   0.0160   0.6450   0.8754
  -0.750   0.0796   0.02396   0.01637   0.0137   0.6306   0.8848
  -0.500   0.1149   0.02389   0.01617   0.0126   0.6180   0.8956
  -0.250   0.1424   0.02384   0.01597   0.0128   0.6064   0.9087
   0.000   0.1908   0.02370   0.01574   0.0091   0.5913   0.9165
   0.250   0.2242   0.02361   0.01555   0.0079   0.5786   0.9280
   0.500   0.2630   0.02341   0.01518   0.0059   0.5671   0.9382
   0.750   0.3033   0.02318   0.01488   0.0033   0.5531   0.9475
   1.000   0.3383   0.02306   0.01471   0.0015   0.5403   0.9579
   1.250   0.3786   0.02279   0.01430  -0.0011   0.5288   0.9668
   1.500   0.4185   0.02247   0.01390  -0.0038   0.5164   0.9753
   1.750   0.4569   0.02229   0.01370  -0.0064   0.5037   0.9840
   2.000   0.4979   0.02197   0.01326  -0.0094   0.4927   0.9921
   2.250   0.5396   0.02161   0.01283  -0.0127   0.4809   0.9994
   2.500   0.5619   0.02171   0.01294  -0.0125   0.4709   1.0000
   2.750   0.5822   0.02174   0.01288  -0.0117   0.4628   1.0000
   3.000   0.6028   0.02195   0.01313  -0.0111   0.4534   1.0000
   3.250   0.6233   0.02203   0.01312  -0.0103   0.4454   1.0000
   3.500   0.6439   0.02230   0.01342  -0.0097   0.4366   1.0000
   3.750   0.6646   0.02244   0.01353  -0.0088   0.4287   1.0000
   4.000   0.6852   0.02273   0.01382  -0.0081   0.4208   1.0000
   4.250   0.7057   0.02297   0.01407  -0.0074   0.4126   1.0000
   4.500   0.7267   0.02322   0.01422  -0.0065   0.4063   1.0000
   4.750   0.7464   0.02365   0.01480  -0.0058   0.3977   1.0000
   5.000   0.7677   0.02380   0.01483  -0.0049   0.3915   1.0000
   5.250   0.7866   0.02437   0.01556  -0.0041   0.3835   1.0000
   5.500   0.8069   0.02465   0.01583  -0.0032   0.3768   1.0000
   5.750   0.8270   0.02510   0.01626  -0.0023   0.3709   1.0000
   6.000   0.8445   0.02570   0.01701  -0.0012   0.3633   1.0000
   6.250   0.8653   0.02595   0.01717  -0.0002   0.3577   1.0000
   6.500   0.8816   0.02673   0.01810   0.0010   0.3511   1.0000
   6.750   0.8988   0.02731   0.01876   0.0022   0.3447   1.0000
   7.000   0.9202   0.02758   0.01890   0.0033   0.3398   1.0000
   7.250   0.9317   0.02864   0.02022   0.0049   0.3330   1.0000
   7.500   0.9480   0.02920   0.02083   0.0063   0.3271   1.0000
   7.750   0.9699   0.02949   0.02097   0.0074   0.3226   1.0000
   8.000   0.9756   0.03082   0.02262   0.0096   0.3164   1.0000
   8.250   0.9895   0.03146   0.02332   0.0114   0.3107   1.0000
   8.500   1.0121   0.03166   0.02339   0.0125   0.3062   1.0000
   8.750   1.0122   0.03322   0.02524   0.0154   0.3008   1.0000
   9.000   1.0201   0.03411   0.02625   0.0178   0.2952   1.0000
   9.250   1.0429   0.03421   0.02624   0.0189   0.2906   1.0000
   9.500   1.0432   0.03563   0.02784   0.0219   0.2859   1.0000
   9.750   1.0375   0.03712   0.02953   0.0256   0.2807   1.0000
  10.000   1.0582   0.03724   0.02961   0.0269   0.2757   1.0000
  10.250   1.0743   0.03792   0.03025   0.0285   0.2712   1.0000
  10.500   1.0460   0.04053   0.03317   0.0338   0.2668   1.0000
  10.750   1.0507   0.04152   0.03423   0.0361   0.2619   1.0000
  11.000   1.1097   0.04025   0.03268   0.0341   0.2564   1.0000
  11.250   1.0561   0.04425   0.03708   0.0404   0.2532   1.0000
  11.500   0.5031   0.11934   0.11233   0.0130   0.2918   1.0000
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