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MH 20 9.01% (mh20-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 20 9.01% (mh20-il)
Reynolds number: 50,000
Max Cl/Cd: 34.88 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh20-il-50000-n5.txt
Download as CSV file: xf-mh20-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 20  9.01%                                    
  
 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  -0.5006   0.09558   0.08935  -0.0091   1.0000   0.0354
  -8.500  -0.4997   0.09118   0.08502  -0.0117   1.0000   0.0351
  -8.250  -0.4992   0.08677   0.08069  -0.0146   1.0000   0.0346
  -8.000  -0.5008   0.08213   0.07614  -0.0181   1.0000   0.0343
  -7.750  -0.5020   0.07762   0.07167  -0.0210   1.0000   0.0338
  -7.500  -0.5012   0.07293   0.06698  -0.0238   1.0000   0.0331
  -7.250  -0.5000   0.06805   0.06207  -0.0264   1.0000   0.0326
  -7.000  -0.4974   0.06326   0.05719  -0.0285   1.0000   0.0321
  -6.750  -0.4931   0.05859   0.05236  -0.0300   1.0000   0.0316
  -6.500  -0.4872   0.05402   0.04757  -0.0309   1.0000   0.0312
  -6.250  -0.4793   0.04970   0.04296  -0.0311   1.0000   0.0309
  -6.000  -0.4703   0.04564   0.03855  -0.0306   1.0000   0.0308
  -5.750  -0.4607   0.04216   0.03469  -0.0295   1.0000   0.0306
  -5.500  -0.4527   0.03914   0.03115  -0.0274   1.0000   0.0309
  -5.250  -0.4462   0.03660   0.02823  -0.0247   1.0000   0.0313
  -5.000  -0.4384   0.03431   0.02554  -0.0219   1.0000   0.0319
  -4.750  -0.4171   0.03169   0.02239  -0.0212   0.9941   0.0332
  -4.500  -0.3819   0.02911   0.01915  -0.0223   0.9837   0.0372
  -4.250  -0.3483   0.02715   0.01698  -0.0240   0.9742   0.0469
  -4.000  -0.3116   0.02506   0.01467  -0.0254   0.9667   0.0582
  -3.750  -0.2753   0.02329   0.01286  -0.0270   0.9586   0.0932
  -3.500  -0.2388   0.02177   0.01155  -0.0292   0.9509   0.1679
  -3.250  -0.2060   0.02051   0.01069  -0.0308   0.9428   0.2654
  -3.000  -0.1797   0.01933   0.01012  -0.0310   0.9334   0.4013
  -2.750  -0.1471   0.01787   0.00981  -0.0305   0.9282   0.6887
  -2.500  -0.0264   0.01758   0.00918  -0.0454   0.9372   0.9741
  -2.250   0.0284   0.01747   0.00857  -0.0513   0.9313   1.0000
  -2.000   0.0593   0.01752   0.00822  -0.0525   0.9197   1.0000
  -1.750   0.0885   0.01761   0.00801  -0.0533   0.9083   1.0000
  -1.500   0.1161   0.01773   0.00788  -0.0537   0.8974   1.0000
  -1.250   0.1428   0.01788   0.00780  -0.0538   0.8869   1.0000
  -1.000   0.1674   0.01806   0.00778  -0.0534   0.8760   1.0000
  -0.750   0.1905   0.01826   0.00778  -0.0528   0.8650   1.0000
  -0.500   0.2136   0.01848   0.00785  -0.0521   0.8544   1.0000
  -0.250   0.2367   0.01870   0.00794  -0.0513   0.8443   1.0000
   0.000   0.2602   0.01890   0.00803  -0.0504   0.8346   1.0000
   0.250   0.2818   0.01916   0.00821  -0.0494   0.8236   1.0000
   0.500   0.3037   0.01942   0.00839  -0.0484   0.8130   1.0000
   0.750   0.3259   0.01968   0.00858  -0.0473   0.8027   1.0000
   1.000   0.3486   0.01990   0.00875  -0.0462   0.7930   1.0000
   1.250   0.3706   0.02015   0.00897  -0.0451   0.7823   1.0000
   1.500   0.3926   0.02043   0.00924  -0.0440   0.7711   1.0000
   1.750   0.4148   0.02070   0.00954  -0.0429   0.7601   1.0000
   2.000   0.4372   0.02095   0.00980  -0.0417   0.7492   1.0000
   2.250   0.4598   0.02117   0.01002  -0.0405   0.7386   1.0000
   2.500   0.4824   0.02137   0.01026  -0.0392   0.7275   1.0000
   2.750   0.5044   0.02164   0.01058  -0.0380   0.7152   1.0000
   3.000   0.5264   0.02188   0.01098  -0.0367   0.7026   1.0000
   3.250   0.5485   0.02212   0.01131  -0.0353   0.6898   1.0000
   3.500   0.5707   0.02233   0.01162  -0.0340   0.6767   1.0000
   3.750   0.5930   0.02253   0.01193  -0.0326   0.6631   1.0000
   4.000   0.6154   0.02271   0.01223  -0.0312   0.6491   1.0000
   4.250   0.6379   0.02285   0.01259  -0.0297   0.6346   1.0000
   4.500   0.6606   0.02296   0.01284  -0.0282   0.6196   1.0000
   4.750   0.6818   0.02322   0.01330  -0.0269   0.6012   1.0000
   5.000   0.7041   0.02334   0.01359  -0.0254   0.5832   1.0000
   5.250   0.7266   0.02338   0.01381  -0.0237   0.5647   1.0000
   5.500   0.7481   0.02352   0.01416  -0.0222   0.5428   1.0000
   5.750   0.7697   0.02361   0.01444  -0.0205   0.5194   1.0000
   6.000   0.7914   0.02367   0.01481  -0.0187   0.4940   1.0000
   6.250   0.8125   0.02379   0.01506  -0.0168   0.4653   1.0000
   6.500   0.8329   0.02396   0.01530  -0.0148   0.4328   1.0000
   6.750   0.8507   0.02439   0.01576  -0.0127   0.3928   1.0000
   7.000   0.8648   0.02508   0.01639  -0.0105   0.3413   1.0000
   7.250   0.8746   0.02615   0.01725  -0.0082   0.2776   1.0000
   7.500   0.8795   0.02779   0.01849  -0.0059   0.2027   1.0000
   7.750   0.8805   0.03009   0.02028  -0.0036   0.1340   1.0000
   8.000   0.8806   0.03269   0.02245  -0.0013   0.0916   1.0000
   8.250   0.8822   0.03515   0.02470   0.0010   0.0693   1.0000
   8.500   0.8854   0.03748   0.02702   0.0033   0.0594   1.0000
   8.750   0.8885   0.03977   0.02932   0.0055   0.0504   1.0000
   9.000   0.8954   0.04183   0.03156   0.0074   0.0419   1.0000
   9.250   0.9041   0.04430   0.03402   0.0091   0.0373   1.0000
   9.500   0.9273   0.04692   0.03707   0.0108   0.0336   1.0000
   9.750   0.9403   0.04956   0.04000   0.0122   0.0310   1.0000
  10.000   0.9433   0.05221   0.04295   0.0134   0.0282   1.0000
  10.250   0.9454   0.05570   0.04659   0.0145   0.0262   1.0000
  10.500   0.9424   0.05896   0.05026   0.0154   0.0250   1.0000
  10.750   0.9371   0.06267   0.05431   0.0158   0.0243   1.0000
  11.000   0.9303   0.06658   0.05849   0.0157   0.0243   1.0000
  11.250   0.9187   0.07113   0.06331   0.0149   0.0241   1.0000
  11.500   0.9044   0.07624   0.06865   0.0132   0.0240   1.0000
  11.750   0.8904   0.08157   0.07416   0.0109   0.0241   1.0000
  12.000   0.8741   0.08773   0.08048   0.0077   0.0242   1.0000
  12.250   0.8604   0.09390   0.08677   0.0042   0.0247   1.0000
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