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MH 91 14.98% (mh91-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 91 14.98% (mh91-il)
Reynolds number: 50,000
Max Cl/Cd: 25.16 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh91-il-50000-n5.txt
Download as CSV file: xf-mh91-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 91  14.98%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6941   0.07958   0.07218  -0.0232   1.0000   0.0406
 -11.250  -0.7119   0.07452   0.06697  -0.0254   1.0000   0.0404
 -11.000  -0.7316   0.06990   0.06217  -0.0266   1.0000   0.0403
 -10.750  -0.7497   0.06592   0.05796  -0.0265   1.0000   0.0404
 -10.500  -0.7642   0.06244   0.05424  -0.0254   1.0000   0.0404
 -10.250  -0.7757   0.05930   0.05083  -0.0235   1.0000   0.0406
 -10.000  -0.7809   0.05636   0.04763  -0.0216   1.0000   0.0409
  -9.750  -0.7737   0.05376   0.04492  -0.0205   1.0000   0.0416
  -9.500  -0.7666   0.05115   0.04212  -0.0192   1.0000   0.0421
  -9.250  -0.7569   0.04854   0.03928  -0.0179   1.0000   0.0427
  -9.000  -0.7440   0.04603   0.03653  -0.0168   1.0000   0.0435
  -8.750  -0.7279   0.04362   0.03385  -0.0158   1.0000   0.0446
  -8.500  -0.7095   0.04138   0.03128  -0.0149   1.0000   0.0464
  -8.250  -0.6886   0.03950   0.02934  -0.0143   1.0000   0.0486
  -8.000  -0.6665   0.03780   0.02755  -0.0138   1.0000   0.0517
  -7.750  -0.6403   0.03605   0.02562  -0.0134   1.0000   0.0547
  -7.500  -0.6180   0.03454   0.02419  -0.0129   1.0000   0.0582
  -7.250  -0.5958   0.03320   0.02274  -0.0121   1.0000   0.0633
  -7.000  -0.5777   0.03190   0.02150  -0.0111   1.0000   0.0689
  -6.750  -0.5620   0.03065   0.02031  -0.0097   1.0000   0.0761
  -6.500  -0.5502   0.02951   0.01922  -0.0078   1.0000   0.0855
  -6.250  -0.5449   0.02852   0.01833  -0.0050   1.0000   0.0971
  -6.000  -0.5473   0.02770   0.01766  -0.0009   1.0000   0.1107
  -5.750  -0.5190   0.02549   0.01609  -0.0031   0.9765   0.1785
  -5.500  -0.4946   0.02363   0.01520  -0.0044   0.9556   0.3229
  -5.250  -0.4684   0.02285   0.01491  -0.0045   0.9355   0.4343
  -5.000  -0.4405   0.02263   0.01499  -0.0038   0.9170   0.5188
  -4.750  -0.4102   0.02280   0.01531  -0.0027   0.8996   0.5825
  -4.500  -0.3794   0.02308   0.01553  -0.0017   0.8823   0.6259
  -4.250  -0.3468   0.02342   0.01575  -0.0009   0.8654   0.6563
  -4.000  -0.3188   0.02367   0.01581   0.0004   0.8482   0.6826
  -3.750  -0.2878   0.02401   0.01598   0.0014   0.8315   0.7041
  -3.500  -0.2590   0.02428   0.01606   0.0026   0.8149   0.7242
  -3.250  -0.2310   0.02451   0.01609   0.0038   0.7984   0.7427
  -3.000  -0.2027   0.02471   0.01610   0.0048   0.7824   0.7599
  -2.750  -0.1742   0.02488   0.01607   0.0057   0.7666   0.7760
  -2.500  -0.1460   0.02500   0.01600   0.0066   0.7512   0.7916
  -2.000  -0.0917   0.02514   0.01577   0.0084   0.7214   0.8222
  -1.750  -0.0587   0.02525   0.01570   0.0082   0.7055   0.8350
  -1.500  -0.0248   0.02532   0.01561   0.0077   0.6898   0.8472
  -1.250   0.0053   0.02534   0.01547   0.0077   0.6747   0.8606
  -1.000   0.0335   0.02534   0.01531   0.0079   0.6604   0.8747
  -0.750   0.0751   0.02530   0.01508   0.0059   0.6453   0.8844
  -0.500   0.1079   0.02525   0.01488   0.0053   0.6309   0.8965
  -0.250   0.1373   0.02525   0.01477   0.0049   0.6159   0.9095
   0.000   0.1783   0.02517   0.01455   0.0025   0.6004   0.9185
   0.250   0.2109   0.02512   0.01439   0.0016   0.5861   0.9295
   0.500   0.2449   0.02504   0.01418   0.0003   0.5724   0.9398
   0.750   0.2815   0.02492   0.01392  -0.0014   0.5591   0.9488
   1.000   0.3149   0.02492   0.01385  -0.0029   0.5445   0.9586
   1.250   0.3516   0.02487   0.01372  -0.0050   0.5304   0.9673
   1.500   0.3875   0.02481   0.01358  -0.0069   0.5174   0.9756
   1.750   0.4223   0.02473   0.01336  -0.0085   0.5055   0.9840
   2.000   0.4590   0.02473   0.01334  -0.0109   0.4917   0.9920
   2.250   0.4954   0.02476   0.01334  -0.0132   0.4788   0.9997
   2.500   0.5155   0.02486   0.01334  -0.0122   0.4694   1.0000
   2.750   0.5349   0.02511   0.01360  -0.0113   0.4585   1.0000
   3.000   0.5542   0.02534   0.01379  -0.0103   0.4491   1.0000
   3.250   0.5734   0.02558   0.01401  -0.0092   0.4395   1.0000
   3.500   0.5922   0.02593   0.01435  -0.0082   0.4301   1.0000
   3.750   0.6111   0.02620   0.01458  -0.0070   0.4217   1.0000
   4.000   0.6293   0.02663   0.01505  -0.0059   0.4126   1.0000
   4.250   0.6479   0.02694   0.01533  -0.0046   0.4046   1.0000
   4.500   0.6654   0.02745   0.01588  -0.0034   0.3961   1.0000
   4.750   0.6834   0.02785   0.01628  -0.0021   0.3885   1.0000
   5.000   0.7005   0.02836   0.01680  -0.0008   0.3809   1.0000
   5.250   0.7171   0.02890   0.01741   0.0006   0.3730   1.0000
   5.500   0.7353   0.02929   0.01774   0.0021   0.3669   1.0000
   5.750   0.7489   0.03011   0.01871   0.0036   0.3586   1.0000
   6.000   0.7670   0.03049   0.01905   0.0051   0.3527   1.0000
   6.250   0.7795   0.03139   0.02007   0.0068   0.3453   1.0000
   6.500   0.7944   0.03204   0.02077   0.0084   0.3389   1.0000
   6.750   0.8126   0.03248   0.02114   0.0099   0.3337   1.0000
   7.000   0.8199   0.03370   0.02259   0.0120   0.3262   1.0000
   7.250   0.8364   0.03424   0.02312   0.0136   0.3205   1.0000
   7.500   0.8486   0.03515   0.02410   0.0154   0.3148   1.0000
   7.750   0.8553   0.03641   0.02551   0.0175   0.3083   1.0000
   8.000   0.8737   0.03688   0.02597   0.0189   0.3032   1.0000
   8.250   0.8792   0.03825   0.02747   0.0210   0.2973   1.0000
   8.500   0.8832   0.03972   0.02907   0.0231   0.2913   1.0000
   8.750   0.9042   0.04012   0.02944   0.0242   0.2866   1.0000
   9.000   0.9013   0.04211   0.03161   0.0264   0.2808   1.0000
   9.250   0.8977   0.04412   0.03376   0.0285   0.2750   1.0000
   9.500   0.9228   0.04430   0.03392   0.0293   0.2703   1.0000
   9.750   0.9033   0.04747   0.03726   0.0316   0.2651   1.0000
  10.000   0.8469   0.05341   0.04332   0.0338   0.2595   1.0000
  10.250   0.8793   0.05280   0.04272   0.0349   0.2551   1.0000
  10.500   0.7379   0.07216   0.06213   0.0275   0.2424   1.0000
  10.750   0.7616   0.07190   0.06193   0.0288   0.2393   1.0000
  11.000   0.8001   0.06955   0.05962   0.0312   0.2371   1.0000
  11.500   0.7470   0.08424   0.07436   0.0252   0.2218   1.0000
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