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MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 121 8.76% (mh121-il)
Reynolds number: 50,000
Max Cl/Cd: 35.77 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh121-il-50000-n5.txt
Download as CSV file: xf-mh121-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 121  8.76%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3654   0.09560   0.08933  -0.0397   1.0000   0.0371
  -8.500  -0.4332   0.09876   0.09206  -0.0410   1.0000   0.0371
  -8.250  -0.4368   0.09584   0.08923  -0.0403   1.0000   0.0361
  -8.000  -0.4431   0.09301   0.08651  -0.0396   1.0000   0.0354
  -7.750  -0.4522   0.09028   0.08389  -0.0386   1.0000   0.0347
  -7.500  -0.4642   0.08762   0.08134  -0.0375   1.0000   0.0342
  -7.250  -0.4744   0.08458   0.07841  -0.0373   1.0000   0.0335
  -7.000  -0.4821   0.08082   0.07472  -0.0385   1.0000   0.0329
  -6.750  -0.4880   0.07654   0.07048  -0.0406   1.0000   0.0322
  -6.500  -0.4924   0.07222   0.06614  -0.0424   1.0000   0.0314
  -6.250  -0.4937   0.06763   0.06147  -0.0445   1.0000   0.0306
  -6.000  -0.4909   0.06274   0.05640  -0.0469   1.0000   0.0297
  -5.750  -0.4826   0.05765   0.05099  -0.0495   1.0000   0.0287
  -5.500  -0.4676   0.05269   0.04551  -0.0520   1.0000   0.0276
  -5.250  -0.4492   0.04879   0.04114  -0.0534   1.0000   0.0271
  -5.000  -0.4282   0.04522   0.03707  -0.0545   1.0000   0.0269
  -4.750  -0.4053   0.04176   0.03311  -0.0554   1.0000   0.0268
  -4.500  -0.3805   0.03833   0.02917  -0.0564   1.0000   0.0269
  -4.250  -0.3560   0.03531   0.02582  -0.0573   1.0000   0.0290
  -4.000  -0.3309   0.03331   0.02327  -0.0576   1.0000   0.0331
  -3.750  -0.3045   0.03142   0.02090  -0.0573   1.0000   0.0367
  -3.500  -0.2791   0.02975   0.01882  -0.0563   1.0000   0.0386
  -3.250  -0.2554   0.02791   0.01690  -0.0554   1.0000   0.0418
  -3.000  -0.2311   0.02659   0.01536  -0.0546   1.0000   0.0477
  -2.750  -0.2049   0.02539   0.01404  -0.0548   1.0000   0.0673
  -2.500  -0.1641   0.02190   0.01218  -0.0592   1.0000   0.3273
  -2.250  -0.1487   0.02165   0.01269  -0.0558   1.0000   0.5977
  -2.000  -0.1395   0.02174   0.01296  -0.0507   1.0000   0.6922
  -1.750  -0.1301   0.02170   0.01294  -0.0460   1.0000   0.7524
  -1.500  -0.1133   0.02159   0.01266  -0.0437   1.0000   0.7862
  -1.250  -0.0896   0.02154   0.01240  -0.0431   0.9975   0.8143
  -1.000  -0.0621   0.02157   0.01211  -0.0433   0.9937   0.8487
  -0.750  -0.0329   0.02145   0.01186  -0.0440   0.9893   0.8991
  -0.500   0.0066   0.02141   0.01158  -0.0476   0.9836   1.0000
  -0.250   0.0439   0.02182   0.01165  -0.0509   0.9800   1.0000
   0.000   0.0777   0.02217   0.01172  -0.0532   0.9754   1.0000
   0.250   0.1129   0.02263   0.01184  -0.0557   0.9712   1.0000
   0.500   0.1459   0.02306   0.01208  -0.0577   0.9667   1.0000
   0.750   0.1775   0.02346   0.01234  -0.0594   0.9613   1.0000
   1.000   0.2129   0.02399   0.01275  -0.0617   0.9569   1.0000
   1.250   0.2416   0.02437   0.01306  -0.0627   0.9506   1.0000
   1.500   0.2759   0.02487   0.01352  -0.0648   0.9454   1.0000
   1.750   0.3055   0.02530   0.01392  -0.0659   0.9389   1.0000
   2.000   0.3393   0.02579   0.01442  -0.0678   0.9328   1.0000
   2.250   0.3689   0.02623   0.01489  -0.0688   0.9255   1.0000
   2.500   0.4040   0.02672   0.01546  -0.0709   0.9191   1.0000
   2.750   0.4324   0.02714   0.01604  -0.0716   0.9105   1.0000
   3.000   0.4676   0.02760   0.01662  -0.0735   0.9032   1.0000
   3.250   0.4992   0.02799   0.01717  -0.0747   0.8939   1.0000
   3.500   0.5293   0.02837   0.01773  -0.0756   0.8836   1.0000
   3.750   0.5620   0.02871   0.01828  -0.0767   0.8729   1.0000
   4.000   0.5965   0.02896   0.01896  -0.0780   0.8613   1.0000
   4.250   0.6311   0.02909   0.01941  -0.0791   0.8479   1.0000
   4.500   0.6673   0.02899   0.01968  -0.0800   0.8316   1.0000
   4.750   0.7092   0.02829   0.01943  -0.0809   0.8096   1.0000
   5.000   0.7540   0.02635   0.01802  -0.0802   0.7708   1.0000
   5.250   0.7778   0.02475   0.01680  -0.0761   0.7126   1.0000
   5.500   0.8305   0.02322   0.01384  -0.0730   0.3326   1.0000
   5.750   0.8287   0.02608   0.01543  -0.0689   0.1684   1.0000
   6.000   0.8394   0.02862   0.01729  -0.0668   0.0983   1.0000
   6.250   0.8592   0.03108   0.01973  -0.0652   0.0716   1.0000
   6.500   0.8895   0.03362   0.02234  -0.0652   0.0447   1.0000
   6.750   0.9293   0.03669   0.02560  -0.0662   0.0336   1.0000
   7.000   0.9552   0.03928   0.02834  -0.0661   0.0256   1.0000
   7.250   0.9889   0.04323   0.03279  -0.0662   0.0238   1.0000
   7.500   1.0126   0.04705   0.03721  -0.0649   0.0229   1.0000
   7.750   1.0286   0.05098   0.04169  -0.0630   0.0224   1.0000
   8.000   1.0384   0.05493   0.04617  -0.0605   0.0221   1.0000
   8.250   1.0430   0.05892   0.05064  -0.0578   0.0220   1.0000
   8.500   1.0432   0.06289   0.05503  -0.0549   0.0220   1.0000
   8.750   1.0393   0.06681   0.05932  -0.0520   0.0220   1.0000
   9.000   1.0316   0.07065   0.06347  -0.0492   0.0221   1.0000
   9.250   1.0193   0.07426   0.06734  -0.0462   0.0221   1.0000
   9.500   1.0045   0.07802   0.07131  -0.0437   0.0222   1.0000
   9.750   0.9886   0.08202   0.07549  -0.0422   0.0224   1.0000
  10.000   0.9715   0.08644   0.08008  -0.0417   0.0226   1.0000
  10.250   0.9543   0.09135   0.08513  -0.0423   0.0227   1.0000
  10.500   0.9383   0.09673   0.09061  -0.0442   0.0230   1.0000
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