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MH 93 15.98% (mh93-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 93 15.98% (mh93-il)
Reynolds number: 50,000
Max Cl/Cd: 24.39 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh93-il-50000-n5.txt
Download as CSV file: xf-mh93-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 93  15.98%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6617   0.09526   0.08813  -0.0123   1.0000   0.0435
 -12.250  -0.6899   0.08677   0.07950  -0.0179   1.0000   0.0430
 -12.000  -0.7174   0.07969   0.07223  -0.0220   1.0000   0.0425
 -11.750  -0.7408   0.07401   0.06636  -0.0243   1.0000   0.0423
 -11.500  -0.7599   0.06933   0.06145  -0.0253   1.0000   0.0421
 -11.250  -0.7762   0.06520   0.05708  -0.0252   1.0000   0.0421
 -11.000  -0.7878   0.06163   0.05324  -0.0244   1.0000   0.0422
 -10.750  -0.7955   0.05836   0.04972  -0.0231   1.0000   0.0425
 -10.500  -0.7989   0.05535   0.04642  -0.0215   1.0000   0.0428
 -10.250  -0.7975   0.05254   0.04332  -0.0198   1.0000   0.0433
 -10.000  -0.7916   0.04983   0.04030  -0.0182   1.0000   0.0439
  -9.750  -0.7818   0.04734   0.03748  -0.0168   1.0000   0.0451
  -9.500  -0.7637   0.04542   0.03557  -0.0163   1.0000   0.0467
  -9.250  -0.7460   0.04350   0.03350  -0.0156   1.0000   0.0490
  -9.000  -0.7224   0.04140   0.03111  -0.0152   1.0000   0.0516
  -8.750  -0.6960   0.03960   0.02938  -0.0154   1.0000   0.0543
  -8.500  -0.6687   0.03793   0.02753  -0.0153   1.0000   0.0584
  -8.250  -0.6469   0.03647   0.02615  -0.0149   1.0000   0.0626
  -8.000  -0.6238   0.03507   0.02467  -0.0144   1.0000   0.0680
  -7.750  -0.6063   0.03370   0.02333  -0.0135   1.0000   0.0752
  -7.500  -0.5917   0.03237   0.02210  -0.0123   1.0000   0.0829
  -7.250  -0.5799   0.03105   0.02088  -0.0108   1.0000   0.0944
  -7.000  -0.5714   0.02979   0.01976  -0.0088   1.0000   0.1103
  -6.750  -0.5695   0.02859   0.01887  -0.0060   1.0000   0.1313
  -6.500  -0.5648   0.02721   0.01792  -0.0041   0.9841   0.1749
  -6.000  -0.5211   0.02437   0.01636  -0.0051   0.9340   0.3897
  -5.750  -0.4966   0.02398   0.01626  -0.0044   0.9139   0.4666
  -5.500  -0.4719   0.02399   0.01642  -0.0028   0.8952   0.5292
  -5.250  -0.4448   0.02429   0.01675  -0.0011   0.8775   0.5769
  -4.750  -0.3897   0.02502   0.01724   0.0021   0.8436   0.6392
  -4.500  -0.3617   0.02538   0.01745   0.0035   0.8273   0.6617
  -4.250  -0.3321   0.02579   0.01768   0.0046   0.8114   0.6811
  -4.000  -0.3038   0.02614   0.01784   0.0058   0.7959   0.6993
  -3.750  -0.2765   0.02643   0.01793   0.0071   0.7810   0.7163
  -3.500  -0.2503   0.02665   0.01797   0.0084   0.7667   0.7327
  -3.250  -0.2256   0.02681   0.01792   0.0099   0.7533   0.7486
  -3.000  -0.1941   0.02708   0.01801   0.0102   0.7382   0.7616
  -2.750  -0.1625   0.02729   0.01805   0.0104   0.7239   0.7739
  -2.500  -0.1359   0.02739   0.01797   0.0112   0.7105   0.7877
  -2.250  -0.1122   0.02741   0.01781   0.0125   0.6982   0.8021
  -2.000  -0.0762   0.02758   0.01782   0.0117   0.6834   0.8124
  -1.750  -0.0460   0.02764   0.01773   0.0117   0.6698   0.8244
  -1.500  -0.0218   0.02762   0.01755   0.0127   0.6581   0.8380
  -1.250   0.0165   0.02767   0.01745   0.0113   0.6442   0.8474
  -1.000   0.0460   0.02769   0.01736   0.0110   0.6307   0.8591
  -0.750   0.0738   0.02768   0.01720   0.0112   0.6188   0.8712
  -0.500   0.1111   0.02761   0.01699   0.0097   0.6062   0.8799
  -0.250   0.1371   0.02764   0.01695   0.0098   0.5931   0.8920
   0.000   0.1755   0.02757   0.01675   0.0079   0.5805   0.9001
   0.250   0.2037   0.02750   0.01655   0.0079   0.5695   0.9105
   0.500   0.2395   0.02748   0.01646   0.0061   0.5560   0.9189
   0.750   0.2694   0.02745   0.01635   0.0054   0.5448   0.9281
   1.000   0.3035   0.02735   0.01614   0.0041   0.5336   0.9364
   1.250   0.3351   0.02739   0.01614   0.0029   0.5211   0.9447
   1.500   0.3683   0.02733   0.01598   0.0016   0.5108   0.9527
   1.750   0.4013   0.02731   0.01592   0.0002   0.4993   0.9602
   2.000   0.4338   0.02737   0.01595  -0.0013   0.4879   0.9679
   2.250   0.4680   0.02726   0.01573  -0.0028   0.4787   0.9747
   2.500   0.5002   0.02743   0.01593  -0.0045   0.4667   0.9821
   2.750   0.5354   0.02739   0.01584  -0.0064   0.4571   0.9884
   3.000   0.5690   0.02749   0.01593  -0.0082   0.4468   0.9950
   3.250   0.6000   0.02764   0.01610  -0.0095   0.4370   1.0000
   3.500   0.6189   0.02788   0.01631  -0.0085   0.4288   1.0000
   3.750   0.6376   0.02821   0.01664  -0.0075   0.4210   1.0000
   4.000   0.6559   0.02858   0.01705  -0.0066   0.4127   1.0000
   4.250   0.6746   0.02883   0.01724  -0.0053   0.4060   1.0000
   4.500   0.6915   0.02941   0.01792  -0.0044   0.3973   1.0000
   5.000   0.7255   0.03037   0.01896  -0.0019   0.3831   1.0000
   5.250   0.7427   0.03076   0.01934  -0.0005   0.3765   1.0000
   5.500   0.7589   0.03130   0.01990   0.0008   0.3702   1.0000
   5.750   0.7723   0.03209   0.02081   0.0023   0.3628   1.0000
   6.000   0.7901   0.03240   0.02107   0.0038   0.3575   1.0000
   6.250   0.8007   0.03339   0.02221   0.0055   0.3506   1.0000
   6.500   0.8133   0.03413   0.02301   0.0072   0.3443   1.0000
   6.750   0.8316   0.03440   0.02323   0.0088   0.3397   1.0000
   7.000   0.8347   0.03584   0.02487   0.0110   0.3329   1.0000
   7.250   0.8445   0.03666   0.02576   0.0131   0.3271   1.0000
   7.500   0.8635   0.03687   0.02591   0.0147   0.3228   1.0000
   7.750   0.8576   0.03871   0.02797   0.0178   0.3167   1.0000
   8.000   0.8596   0.03993   0.02928   0.0205   0.3113   1.0000
   8.250   0.8778   0.04018   0.02949   0.0221   0.3070   1.0000
   8.500   0.8682   0.04207   0.03151   0.0255   0.3018   1.0000
   8.750   0.8481   0.04449   0.03406   0.0294   0.2963   1.0000
   9.000   0.8590   0.04518   0.03476   0.0313   0.2919   1.0000
   9.250   0.8784   0.04553   0.03509   0.0327   0.2880   1.0000
   9.500   0.7316   0.05767   0.04733   0.0373   0.2790   1.0000
   9.750   0.7525   0.05781   0.04749   0.0386   0.2752   1.0000
  10.000   0.8047   0.05505   0.04475   0.0404   0.2730   1.0000
  10.500   0.6354   0.08179   0.07149   0.0310   0.2488   1.0000
  10.750   0.6437   0.08383   0.07355   0.0311   0.2442   1.0000
  11.000   0.6671   0.08378   0.07356   0.0322   0.2416   1.0000
  11.500   0.6356   0.09506   0.08487   0.0282   0.2281   1.0000
  11.750   0.6607   0.09481   0.08469   0.0294   0.2255   1.0000
  12.000   0.6203   0.10433   0.09420   0.0250   0.2169   1.0000
  12.250   0.6332   0.10596   0.09589   0.0250   0.2128   1.0000
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