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MH 201 13.08% (mh201-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 201 13.08% (mh201-il)
Reynolds number: 50,000
Max Cl/Cd: 34.64 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh201-il-50000-n5.txt
Download as CSV file: xf-mh201-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 201  13.08%                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4064   0.10466   0.09746  -0.0516   1.0000   0.0398
 -10.250  -0.4086   0.10095   0.09383  -0.0520   1.0000   0.0394
 -10.000  -0.4139   0.09676   0.08973  -0.0528   1.0000   0.0391
  -9.750  -0.4205   0.09253   0.08558  -0.0537   1.0000   0.0386
  -9.500  -0.4310   0.08759   0.08074  -0.0552   1.0000   0.0381
  -9.250  -0.4455   0.08281   0.07603  -0.0567   1.0000   0.0375
  -9.000  -0.4669   0.07845   0.07175  -0.0574   1.0000   0.0371
  -8.750  -0.4928   0.07508   0.06844  -0.0566   1.0000   0.0367
  -8.500  -0.5217   0.07265   0.06607  -0.0540   1.0000   0.0363
  -8.250  -0.5479   0.06973   0.06314  -0.0518   1.0000   0.0360
  -8.000  -0.5685   0.06674   0.06007  -0.0495   1.0000   0.0357
  -7.750  -0.5852   0.06351   0.05669  -0.0475   1.0000   0.0353
  -7.500  -0.5968   0.06011   0.05306  -0.0456   1.0000   0.0352
  -7.250  -0.6026   0.05671   0.04938  -0.0440   1.0000   0.0350
  -7.000  -0.6030   0.05339   0.04573  -0.0426   1.0000   0.0349
  -6.750  -0.5987   0.05013   0.04210  -0.0414   1.0000   0.0350
  -6.500  -0.5898   0.04716   0.03871  -0.0404   1.0000   0.0351
  -6.250  -0.5690   0.04400   0.03507  -0.0412   0.9973   0.0359
  -6.000  -0.5414   0.04126   0.03183  -0.0426   0.9932   0.0375
  -5.750  -0.5126   0.03886   0.02881  -0.0436   0.9888   0.0397
  -5.500  -0.4839   0.03695   0.02677  -0.0447   0.9849   0.0426
  -5.250  -0.4553   0.03529   0.02486  -0.0451   0.9808   0.0450
  -5.000  -0.4261   0.03389   0.02309  -0.0452   0.9764   0.0491
  -4.750  -0.3966   0.03265   0.02189  -0.0460   0.9724   0.0557
  -4.500  -0.3705   0.03150   0.02063  -0.0458   0.9675   0.0628
  -4.250  -0.3424   0.03038   0.01947  -0.0464   0.9626   0.0769
  -4.000  -0.3122   0.02906   0.01828  -0.0476   0.9584   0.1076
  -3.750  -0.2884   0.02714   0.01712  -0.0485   0.9529   0.2053
  -3.500  -0.2640   0.02535   0.01677  -0.0494   0.9483   0.4360
  -3.250  -0.2518   0.02562   0.01783  -0.0442   0.9421   0.5986
  -3.000  -0.2328   0.02632   0.01845  -0.0410   0.9352   0.6809
  -2.750  -0.2104   0.02694   0.01884  -0.0387   0.9292   0.7294
  -2.500  -0.1925   0.02734   0.01903  -0.0359   0.9218   0.7624
  -2.250  -0.1674   0.02772   0.01918  -0.0342   0.9165   0.7913
  -2.000  -0.1526   0.02786   0.01914  -0.0313   0.9084   0.8155
  -1.750  -0.1277   0.02802   0.01910  -0.0299   0.9026   0.8381
  -1.500  -0.1102   0.02806   0.01896  -0.0277   0.8949   0.8598
  -1.250  -0.0834   0.02809   0.01882  -0.0269   0.8888   0.8801
  -1.000  -0.0567   0.02809   0.01865  -0.0264   0.8823   0.8998
  -0.750  -0.0265   0.02808   0.01847  -0.0270   0.8753   0.9171
  -0.500   0.0182   0.02810   0.01829  -0.0303   0.8708   0.9305
  -0.250   0.0504   0.02814   0.01820  -0.0318   0.8625   0.9429
   0.000   0.0988   0.02818   0.01807  -0.0361   0.8572   0.9527
   0.250   0.1396   0.02826   0.01803  -0.0393   0.8497   0.9626
   0.500   0.1862   0.02830   0.01795  -0.0435   0.8431   0.9711
   0.750   0.2343   0.02834   0.01790  -0.0480   0.8366   0.9783
   1.000   0.2769   0.02837   0.01789  -0.0515   0.8283   0.9862
   1.250   0.3213   0.02835   0.01781  -0.0552   0.8211   0.9939
   1.500   0.3512   0.02835   0.01778  -0.0562   0.8116   1.0000
   1.750   0.3626   0.02839   0.01781  -0.0540   0.7999   1.0000
   2.000   0.3979   0.02816   0.01756  -0.0553   0.7933   1.0000
   2.250   0.4057   0.02826   0.01765  -0.0524   0.7803   1.0000
   2.500   0.4213   0.02833   0.01772  -0.0508   0.7683   1.0000
   2.750   0.4627   0.02800   0.01741  -0.0528   0.7619   1.0000
   3.000   0.4793   0.02813   0.01755  -0.0514   0.7487   1.0000
   3.250   0.5014   0.02822   0.01767  -0.0507   0.7361   1.0000
   3.500   0.5299   0.02817   0.01765  -0.0509   0.7247   1.0000
   3.750   0.5703   0.02777   0.01733  -0.0526   0.7159   1.0000
   4.000   0.5947   0.02781   0.01742  -0.0521   0.7020   1.0000
   4.250   0.6213   0.02778   0.01745  -0.0519   0.6881   1.0000
   4.500   0.6493   0.02770   0.01747  -0.0518   0.6740   1.0000
   4.750   0.6785   0.02757   0.01741  -0.0518   0.6595   1.0000
   5.000   0.7080   0.02740   0.01733  -0.0518   0.6442   1.0000
   5.250   0.7382   0.02719   0.01722  -0.0518   0.6280   1.0000
   5.500   0.7695   0.02693   0.01705  -0.0519   0.6108   1.0000
   5.750   0.8030   0.02661   0.01679  -0.0522   0.5929   1.0000
   6.000   0.8267   0.02670   0.01697  -0.0514   0.5710   1.0000
   6.250   0.8577   0.02655   0.01686  -0.0513   0.5489   1.0000
   6.500   0.8837   0.02665   0.01698  -0.0508   0.5245   1.0000
   6.750   0.9121   0.02673   0.01704  -0.0505   0.4992   1.0000
   7.000   0.9338   0.02711   0.01742  -0.0494   0.4724   1.0000
   7.250   0.9547   0.02759   0.01787  -0.0484   0.4457   1.0000
   7.500   0.9750   0.02815   0.01838  -0.0473   0.4195   1.0000
   7.750   0.9930   0.02885   0.01904  -0.0459   0.3939   1.0000
   8.000   1.0091   0.02968   0.01984  -0.0445   0.3691   1.0000
   8.250   1.0255   0.03055   0.02063  -0.0432   0.3460   1.0000
   8.500   1.0400   0.03155   0.02167  -0.0417   0.3236   1.0000
   8.750   1.0543   0.03260   0.02269  -0.0403   0.3027   1.0000
   9.000   1.0687   0.03370   0.02374  -0.0390   0.2836   1.0000
   9.250   1.0822   0.03491   0.02500  -0.0377   0.2651   1.0000
   9.500   1.0952   0.03616   0.02630  -0.0364   0.2478   1.0000
   9.750   1.1087   0.03747   0.02767  -0.0352   0.2320   1.0000
  10.000   1.1214   0.03885   0.02909  -0.0341   0.2172   1.0000
  10.250   1.1345   0.04028   0.03057  -0.0330   0.2038   1.0000
  10.500   1.1475   0.04175   0.03208  -0.0319   0.1915   1.0000
  10.750   1.1595   0.04327   0.03364  -0.0308   0.1799   1.0000
  11.000   1.1704   0.04500   0.03558  -0.0298   0.1690   1.0000
  11.250   1.1811   0.04677   0.03747  -0.0288   0.1592   1.0000
  11.500   1.1928   0.04842   0.03908  -0.0279   0.1505   1.0000
  11.750   1.1994   0.05060   0.04156  -0.0268   0.1419   1.0000
  12.000   1.2089   0.05253   0.04355  -0.0260   0.1345   1.0000
  12.250   1.2132   0.05492   0.04619  -0.0250   0.1274   1.0000
  12.500   1.2222   0.05703   0.04837  -0.0243   0.1212   1.0000
  12.750   1.2211   0.06000   0.05166  -0.0235   0.1153   1.0000
  13.000   1.2301   0.06201   0.05365  -0.0229   0.1098   1.0000
  13.250   1.2242   0.06573   0.05773  -0.0224   0.1056   1.0000
  13.500   1.2190   0.06933   0.06160  -0.0222   0.1014   1.0000
  13.750   1.2274   0.07142   0.06364  -0.0219   0.0967   1.0000
  14.000   1.2130   0.07637   0.06895  -0.0224   0.0941   1.0000
  14.250   1.1947   0.08204   0.07496  -0.0235   0.0920   1.0000
  14.500   1.1752   0.08818   0.08139  -0.0254   0.0901   1.0000
  14.750   1.1536   0.09505   0.08849  -0.0281   0.0886   1.0000
  15.000   1.1212   0.10447   0.09814  -0.0328   0.0883   1.0000
  15.250   1.0417   0.12585   0.11971  -0.0459   0.0914   1.0000
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