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MH 38 9.68% (mh38-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 38 9.68% (mh38-il)
Reynolds number: 50,000
Max Cl/Cd: 37.69 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh38-il-50000.txt
Download as CSV file: xf-mh38-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 38  9.68%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3386   0.10751   0.10125  -0.0337   1.0000   0.1934
  -8.250  -0.3159   0.10165   0.09538  -0.0319   1.0000   0.2025
  -8.000  -0.3374   0.10189   0.09584  -0.0328   1.0000   0.2071
  -7.750  -0.3175   0.09664   0.09060  -0.0310   1.0000   0.2164
  -7.500  -0.3443   0.09717   0.09139  -0.0299   1.0000   0.2207
  -7.250  -0.3333   0.09319   0.08747  -0.0276   1.0000   0.2319
  -7.000  -0.3607   0.09353   0.08802  -0.0241   1.0000   0.2338
  -6.750  -0.3602   0.09081   0.08538  -0.0207   1.0000   0.2438
  -6.500  -0.3867   0.09084   0.08558  -0.0172   1.0000   0.2466
  -6.250  -0.4126   0.09069   0.08557  -0.0159   1.0000   0.2483
  -6.000  -0.4151   0.08826   0.08321  -0.0123   1.0000   0.2610
  -5.750  -0.4206   0.08613   0.08116  -0.0093   1.0000   0.2735
  -5.500  -0.4263   0.08395   0.07905  -0.0068   1.0000   0.2843
  -5.250  -0.4336   0.08186   0.07704  -0.0051   1.0000   0.2965
  -5.000  -0.4391   0.07968   0.07491  -0.0036   1.0000   0.3094
  -4.750  -0.4420   0.07720   0.07249  -0.0020   1.0000   0.3252
  -4.500  -0.4479   0.07521   0.07053  -0.0031   1.0000   0.3464
  -4.250  -0.3740   0.05547   0.04970  -0.0434   1.0000   0.1551
  -4.000  -0.3363   0.04718   0.04066  -0.0510   1.0000   0.1308
  -3.750  -0.3057   0.04240   0.03525  -0.0545   1.0000   0.1334
  -3.500  -0.2772   0.03887   0.03115  -0.0566   1.0000   0.1431
  -3.250  -0.2449   0.03533   0.02679  -0.0584   1.0000   0.1503
  -3.000  -0.2225   0.03383   0.02508  -0.0584   1.0000   0.1712
  -2.750  -0.1956   0.03186   0.02267  -0.0588   1.0000   0.1875
  -2.500  -0.1720   0.03070   0.02131  -0.0587   1.0000   0.2134
  -2.250  -0.1480   0.02960   0.02001  -0.0585   1.0000   0.2408
  -2.000  -0.1254   0.02892   0.01921  -0.0583   1.0000   0.2772
  -1.750  -0.1035   0.02825   0.01858  -0.0577   1.0000   0.3146
  -1.500  -0.0801   0.02778   0.01817  -0.0575   1.0000   0.3656
  -1.250  -0.0564   0.02730   0.01790  -0.0572   1.0000   0.4370
  -1.000  -0.0281   0.02645   0.01782  -0.0571   0.9973   0.5907
  -0.750   0.0018   0.02529   0.01728  -0.0572   0.9894   1.0000
  -0.500   0.0453   0.02645   0.01776  -0.0614   0.9815   1.0000
  -0.250   0.0778   0.02728   0.01817  -0.0637   0.9731   1.0000
   0.000   0.1140   0.02831   0.01879  -0.0665   0.9650   1.0000
   0.250   0.1483   0.02929   0.01948  -0.0689   0.9564   1.0000
   0.500   0.1777   0.03020   0.02015  -0.0705   0.9479   1.0000
   0.750   0.2137   0.03131   0.02103  -0.0733   0.9392   1.0000
   1.000   0.2417   0.03223   0.02175  -0.0746   0.9302   1.0000
   1.250   0.2698   0.03322   0.02260  -0.0759   0.9210   1.0000
   1.500   0.3039   0.03436   0.02360  -0.0782   0.9119   1.0000
   1.750   0.3311   0.03536   0.02450  -0.0793   0.9022   1.0000
   2.000   0.3552   0.03638   0.02544  -0.0799   0.8924   1.0000
   2.250   0.3847   0.03751   0.02650  -0.0814   0.8823   1.0000
   2.500   0.4197   0.03870   0.02765  -0.0836   0.8721   1.0000
   2.750   0.4413   0.03976   0.02870  -0.0838   0.8612   1.0000
   3.000   0.4639   0.04089   0.02982  -0.0841   0.8502   1.0000
   3.250   0.4893   0.04207   0.03100  -0.0849   0.8388   1.0000
   3.500   0.5165   0.04327   0.03222  -0.0858   0.8273   1.0000
   3.750   0.5450   0.04447   0.03346  -0.0868   0.8153   1.0000
   4.000   0.5743   0.04566   0.03474  -0.0878   0.8029   1.0000
   4.250   0.6030   0.04684   0.03599  -0.0887   0.7901   1.0000
   4.500   0.6312   0.04800   0.03724  -0.0894   0.7770   1.0000
   4.750   0.6563   0.04918   0.03852  -0.0897   0.7633   1.0000
   5.000   0.6781   0.05040   0.03989  -0.0895   0.7490   1.0000
   5.250   0.6982   0.05166   0.04127  -0.0892   0.7343   1.0000
   5.500   0.7180   0.05295   0.04268  -0.0888   0.7192   1.0000
   5.750   0.7391   0.05420   0.04407  -0.0884   0.7035   1.0000
   6.000   0.7632   0.05534   0.04537  -0.0882   0.6875   1.0000
   6.250   0.7920   0.05625   0.04655  -0.0882   0.6714   1.0000
   6.500   0.8282   0.05674   0.04729  -0.0885   0.6554   1.0000
   6.750   0.8426   0.05812   0.04883  -0.0873   0.6375   1.0000
   7.000   0.8636   0.05912   0.05005  -0.0864   0.6192   1.0000
   7.250   0.9073   0.05858   0.04986  -0.0860   0.6015   1.0000
   7.500   0.9213   0.05977   0.05134  -0.0844   0.5815   1.0000
   7.750   0.9731   0.05767   0.04972  -0.0832   0.5613   1.0000
   8.000   1.1160   0.04379   0.03699  -0.0800   0.5311   1.0000
   8.250   1.1877   0.03274   0.02647  -0.0724   0.4599   1.0000
   8.500   1.1872   0.03150   0.02496  -0.0653   0.3781   1.0000
   8.750   1.1662   0.03330   0.02586  -0.0582   0.2837   1.0000
   9.000   1.1438   0.03663   0.02828  -0.0529   0.2155   1.0000
   9.250   1.1312   0.04043   0.03129  -0.0490   0.1635   1.0000
   9.500   1.1315   0.04374   0.03405  -0.0463   0.1267   1.0000
   9.750   1.1718   0.04700   0.03714  -0.0451   0.0934   1.0000
  10.000   1.2471   0.05293   0.04298  -0.0486   0.0751   1.0000
  10.250   1.2591   0.05647   0.04713  -0.0466   0.0720   1.0000
  10.500   1.2673   0.06005   0.05109  -0.0447   0.0684   1.0000
  10.750   1.2880   0.06506   0.05612  -0.0447   0.0641   1.0000
  11.000   1.2910   0.06976   0.06121  -0.0430   0.0638   1.0000
  11.250   1.2825   0.07333   0.06520  -0.0402   0.0642   1.0000
  11.500   1.2650   0.07655   0.06881  -0.0371   0.0648   1.0000
  11.750   1.2358   0.08000   0.07267  -0.0348   0.0658   1.0000
  12.000   1.2072   0.08450   0.07752  -0.0340   0.0668   1.0000
  12.250   1.1792   0.08981   0.08312  -0.0347   0.0678   1.0000
  12.500   1.1507   0.09596   0.08952  -0.0366   0.0690   1.0000
  12.750   1.1229   0.10295   0.09671  -0.0396   0.0706   1.0000
  13.000   1.0988   0.11049   0.10438  -0.0434   0.0724   1.0000
  13.250   1.0794   0.11826   0.11222  -0.0474   0.0739   1.0000
  13.500   1.0674   0.12564   0.11964  -0.0509   0.0750   1.0000
  13.750   1.0617   0.13269   0.12670  -0.0537   0.0757   1.0000
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