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MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 24 9.01% (mh24-il)
Reynolds number: 50,000
Max Cl/Cd: 33.03 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh24-il-50000-n5.txt
Download as CSV file: xf-mh24-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 24  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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4815   0.09954   0.09248  -0.0341   1.0000   0.0345
  -9.250  -0.4836   0.09576   0.08877  -0.0351   1.0000   0.0339
  -9.000  -0.4878   0.09182   0.08490  -0.0364   1.0000   0.0336
  -8.750  -0.4936   0.08783   0.08099  -0.0378   1.0000   0.0328
  -8.500  -0.5026   0.08392   0.07716  -0.0391   1.0000   0.0321
  -8.250  -0.5163   0.08048   0.07379  -0.0388   1.0000   0.0320
  -8.000  -0.5298   0.07738   0.07073  -0.0373   1.0000   0.0307
  -7.750  -0.5415   0.07403   0.06738  -0.0359   1.0000   0.0304
  -7.500  -0.5521   0.07072   0.06404  -0.0342   1.0000   0.0301
  -7.250  -0.5617   0.06711   0.06033  -0.0322   1.0000   0.0288
  -7.000  -0.5679   0.06394   0.05704  -0.0299   1.0000   0.0292
  -6.750  -0.5725   0.06044   0.05336  -0.0275   1.0000   0.0286
  -6.500  -0.5739   0.05721   0.04992  -0.0250   1.0000   0.0289
  -6.250  -0.5729   0.05390   0.04635  -0.0225   1.0000   0.0286
  -6.000  -0.5692   0.05072   0.04287  -0.0199   1.0000   0.0286
  -5.750  -0.5630   0.04782   0.03966  -0.0175   1.0000   0.0296
  -5.500  -0.5545   0.04487   0.03634  -0.0150   1.0000   0.0301
  -5.250  -0.5434   0.04197   0.03303  -0.0126   1.0000   0.0301
  -5.000  -0.5299   0.03917   0.02979  -0.0103   1.0000   0.0307
  -4.750  -0.5136   0.03655   0.02670  -0.0082   1.0000   0.0308
  -4.500  -0.4948   0.03408   0.02365  -0.0062   1.0000   0.0310
  -4.250  -0.4736   0.03180   0.02094  -0.0045   1.0000   0.0319
  -4.000  -0.4509   0.02986   0.01863  -0.0029   1.0000   0.0331
  -3.750  -0.4268   0.02813   0.01655  -0.0015   1.0000   0.0352
  -3.500  -0.4042   0.02664   0.01496  -0.0003   1.0000   0.0419
  -3.250  -0.3801   0.02547   0.01351   0.0010   1.0000   0.0502
  -3.000  -0.3566   0.02411   0.01213   0.0019   1.0000   0.0683
  -2.750  -0.3350   0.02240   0.01076   0.0032   1.0000   0.1290
  -2.500  -0.1351   0.02033   0.01089  -0.0253   1.0000   1.0000
  -2.250  -0.1244   0.02020   0.01049  -0.0227   1.0000   1.0000
  -2.000  -0.1133   0.02010   0.01016  -0.0201   1.0000   1.0000
  -1.750  -0.1019   0.02003   0.00987  -0.0176   1.0000   1.0000
  -1.500  -0.0901   0.01999   0.00963  -0.0152   1.0000   1.0000
  -1.250  -0.0782   0.01998   0.00944  -0.0127   1.0000   1.0000
  -1.000  -0.0660   0.01999   0.00924  -0.0103   1.0000   1.0000
  -0.750  -0.0537   0.02003   0.00913  -0.0080   1.0000   1.0000
  -0.500  -0.0412   0.02009   0.00907  -0.0057   1.0000   1.0000
  -0.250  -0.0286   0.02018   0.00904  -0.0035   1.0000   1.0000
   0.000  -0.0158   0.02030   0.00905  -0.0013   1.0000   1.0000
   0.250  -0.0030   0.02045   0.00911   0.0008   1.0000   1.0000
   0.500   0.0099   0.02063   0.00918   0.0029   1.0000   1.0000
   0.750   0.0507   0.02107   0.00955  -0.0007   0.9908   1.0000
   1.000   0.0935   0.02157   0.01000  -0.0046   0.9810   1.0000
   1.250   0.1346   0.02198   0.01041  -0.0080   0.9701   1.0000
   1.500   0.1748   0.02234   0.01079  -0.0112   0.9583   1.0000
   1.750   0.2151   0.02265   0.01115  -0.0142   0.9457   1.0000
   2.000   0.2552   0.02290   0.01149  -0.0171   0.9323   1.0000
   2.500   0.3362   0.02317   0.01203  -0.0225   0.9032   1.0000
   2.750   0.3694   0.02316   0.01216  -0.0236   0.8852   1.0000
   3.000   0.4047   0.02306   0.01224  -0.0249   0.8664   1.0000
   3.250   0.4404   0.02286   0.01223  -0.0260   0.8466   1.0000
   3.500   0.4754   0.02254   0.01223  -0.0267   0.8246   1.0000
   3.750   0.5069   0.02214   0.01207  -0.0265   0.7997   1.0000
   4.000   0.5404   0.02165   0.01182  -0.0264   0.7719   1.0000
   4.250   0.5741   0.02118   0.01166  -0.0262   0.7375   1.0000
   4.500   0.6123   0.02069   0.01137  -0.0265   0.6928   1.0000
   4.750   0.6499   0.02039   0.01112  -0.0267   0.6336   1.0000
   5.000   0.6773   0.02055   0.01116  -0.0253   0.5640   1.0000
   5.250   0.6960   0.02107   0.01147  -0.0228   0.4938   1.0000
   5.500   0.7098   0.02179   0.01195  -0.0198   0.4269   1.0000
   5.750   0.7210   0.02266   0.01256  -0.0167   0.3634   1.0000
   6.000   0.7316   0.02363   0.01344  -0.0137   0.3031   1.0000
   6.250   0.7419   0.02473   0.01431  -0.0108   0.2462   1.0000
   6.500   0.7532   0.02596   0.01532  -0.0083   0.1959   1.0000
   6.750   0.7654   0.02733   0.01649  -0.0060   0.1527   1.0000
   7.000   0.7789   0.02887   0.01788  -0.0039   0.1221   1.0000
   7.250   0.7936   0.03040   0.01937  -0.0019   0.0970   1.0000
   7.500   0.8098   0.03208   0.02112  -0.0001   0.0802   1.0000
   7.750   0.8285   0.03409   0.02317   0.0014   0.0696   1.0000
   8.000   0.8442   0.03578   0.02505   0.0032   0.0589   1.0000
   8.250   0.8637   0.03809   0.02773   0.0046   0.0513   1.0000
   8.500   0.8814   0.04062   0.03045   0.0061   0.0471   1.0000
   8.750   0.8975   0.04407   0.03424   0.0077   0.0444   1.0000
   9.000   0.9050   0.04726   0.03802   0.0105   0.0416   1.0000
   9.250   0.9077   0.04960   0.04069   0.0133   0.0373   1.0000
   9.500   0.9095   0.05204   0.04315   0.0155   0.0342   1.0000
   9.750   0.9046   0.05566   0.04730   0.0187   0.0334   1.0000
  10.000   0.8959   0.05896   0.05097   0.0219   0.0331   1.0000
  10.250   0.8813   0.06222   0.05453   0.0253   0.0329   1.0000
  10.500   0.8638   0.06574   0.05829   0.0280   0.0326   1.0000
  10.750   0.8482   0.06933   0.06208   0.0294   0.0328   1.0000
  11.000   0.8285   0.07364   0.06657   0.0297   0.0328   1.0000
  11.250   0.8112   0.07825   0.07130   0.0287   0.0330   1.0000
  11.500   0.7930   0.08370   0.07670   0.0264   0.0332   1.0000
  11.750   0.7782   0.08944   0.08250   0.0233   0.0335   1.0000
  12.000   0.7622   0.09634   0.08943   0.0190   0.0337   1.0000
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