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MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 25 9.98% (mh25-il)
Reynolds number: 100,000
Max Cl/Cd: 47.96 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh25-il-100000-n5.txt
Download as CSV file: xf-mh25-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 25  9.98%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4860   0.09215   0.08726  -0.0363   1.0000   0.0166
  -9.000  -0.4956   0.08832   0.08350  -0.0369   1.0000   0.0163
  -8.750  -0.5074   0.08443   0.07967  -0.0378   1.0000   0.0160
  -8.500  -0.5248   0.08026   0.07556  -0.0388   1.0000   0.0158
  -8.250  -0.5435   0.07722   0.07254  -0.0375   1.0000   0.0156
  -8.000  -0.5650   0.07457   0.06989  -0.0344   1.0000   0.0155
  -7.750  -0.5810   0.07129   0.06658  -0.0319   1.0000   0.0152
  -7.500  -0.5950   0.06767   0.06289  -0.0292   1.0000   0.0149
  -7.250  -0.6053   0.06413   0.05924  -0.0265   1.0000   0.0145
  -7.000  -0.6145   0.06015   0.05509  -0.0235   1.0000   0.0141
  -6.750  -0.6204   0.05600   0.05071  -0.0203   1.0000   0.0135
  -6.500  -0.6246   0.05131   0.04567  -0.0166   1.0000   0.0129
  -6.250  -0.6229   0.04756   0.04156  -0.0132   1.0000   0.0124
  -6.000  -0.6172   0.04455   0.03820  -0.0100   1.0000   0.0120
  -5.750  -0.6098   0.04175   0.03503  -0.0070   1.0000   0.0119
  -5.500  -0.6003   0.03918   0.03209  -0.0042   1.0000   0.0118
  -5.000  -0.5638   0.03403   0.02604  -0.0016   0.9966   0.0115
  -4.500  -0.5144   0.02885   0.01993  -0.0005   0.9917   0.0118
  -4.250  -0.4882   0.02661   0.01734  -0.0002   0.9891   0.0122
  -4.000  -0.4608   0.02507   0.01562  -0.0003   0.9864   0.0136
  -3.750  -0.4309   0.02420   0.01457  -0.0010   0.9837   0.0173
  -3.500  -0.4021   0.02313   0.01326  -0.0011   0.9809   0.0191
  -3.250  -0.3777   0.02186   0.01184  -0.0003   0.9771   0.0215
  -3.000  -0.3502   0.02100   0.01087  -0.0003   0.9734   0.0268
  -2.750  -0.3209   0.02006   0.00999  -0.0006   0.9703   0.0532
  -2.500  -0.3014   0.01829   0.00947   0.0002   0.9664   0.2663
  -2.000  -0.1866   0.01802   0.01122  -0.0080   0.9718   0.9433
  -1.750  -0.1097   0.01855   0.01138  -0.0177   0.9751   0.9727
  -1.500  -0.0243   0.01876   0.01126  -0.0298   0.9806   0.9969
  -1.250   0.0141   0.01873   0.01104  -0.0326   0.9764   1.0000
  -1.000   0.0492   0.01876   0.01093  -0.0348   0.9714   1.0000
  -0.750   0.0806   0.01875   0.01081  -0.0361   0.9651   1.0000
  -0.500   0.1150   0.01875   0.01070  -0.0380   0.9592   1.0000
  -0.250   0.1476   0.01874   0.01062  -0.0395   0.9527   1.0000
   0.000   0.1818   0.01871   0.01053  -0.0412   0.9459   1.0000
   0.250   0.2132   0.01866   0.01046  -0.0424   0.9386   1.0000
   0.500   0.2499   0.01859   0.01037  -0.0445   0.9317   1.0000
   0.750   0.2787   0.01850   0.01027  -0.0449   0.9226   1.0000
   1.000   0.3204   0.01835   0.01014  -0.0479   0.9168   1.0000
   1.250   0.3467   0.01820   0.01002  -0.0478   0.9058   1.0000
   1.750   0.4071   0.01778   0.00972  -0.0487   0.8848   1.0000
   2.000   0.4409   0.01748   0.00949  -0.0498   0.8745   1.0000
   2.250   0.4643   0.01722   0.00930  -0.0487   0.8602   1.0000
   2.500   0.4853   0.01696   0.00917  -0.0471   0.8439   1.0000
   2.750   0.5093   0.01665   0.00894  -0.0460   0.8270   1.0000
   3.000   0.5368   0.01632   0.00871  -0.0455   0.8082   1.0000
   3.250   0.5678   0.01595   0.00844  -0.0456   0.7854   1.0000
   3.500   0.6071   0.01548   0.00810  -0.0472   0.7568   1.0000
   3.750   0.6525   0.01503   0.00765  -0.0499   0.7131   1.0000
   4.000   0.6932   0.01484   0.00733  -0.0517   0.6518   1.0000
   4.250   0.7209   0.01503   0.00732  -0.0512   0.5862   1.0000
   4.500   0.7404   0.01544   0.00748  -0.0493   0.5224   1.0000
   4.750   0.7557   0.01595   0.00782  -0.0468   0.4620   1.0000
   5.000   0.7692   0.01652   0.00818  -0.0441   0.4055   1.0000
   5.250   0.7816   0.01713   0.00859  -0.0413   0.3518   1.0000
   5.500   0.7937   0.01777   0.00904  -0.0384   0.3023   1.0000
   5.750   0.8052   0.01845   0.00954  -0.0355   0.2546   1.0000
   6.000   0.8164   0.01916   0.01008  -0.0327   0.2109   1.0000
   6.250   0.8276   0.01991   0.01067  -0.0298   0.1707   1.0000
   6.500   0.8386   0.02070   0.01132  -0.0270   0.1344   1.0000
   6.750   0.8490   0.02154   0.01205  -0.0241   0.1059   1.0000
   7.000   0.8590   0.02242   0.01284  -0.0211   0.0817   1.0000
   7.250   0.8679   0.02336   0.01376  -0.0178   0.0671   1.0000
   7.500   0.8764   0.02433   0.01487  -0.0144   0.0564   1.0000
   7.750   0.8845   0.02532   0.01592  -0.0110   0.0477   1.0000
   8.000   0.8906   0.02643   0.01700  -0.0075   0.0413   1.0000
   8.250   0.8994   0.02753   0.01832  -0.0042   0.0374   1.0000
   8.500   0.9076   0.02878   0.01970  -0.0009   0.0339   1.0000
   8.750   0.9142   0.03019   0.02116   0.0024   0.0310   1.0000
   9.000   0.9247   0.03174   0.02292   0.0052   0.0274   1.0000
   9.250   0.9350   0.03326   0.02466   0.0080   0.0242   1.0000
   9.500   0.9430   0.03493   0.02648   0.0108   0.0221   1.0000
   9.750   0.9473   0.03738   0.02904   0.0137   0.0197   1.0000
  10.000   0.9527   0.03896   0.03100   0.0169   0.0176   1.0000
  10.250   0.9549   0.04153   0.03392   0.0203   0.0160   1.0000
  10.500   0.9542   0.04403   0.03673   0.0236   0.0155   1.0000
  10.750   0.9489   0.04662   0.03962   0.0272   0.0148   1.0000
  11.000   0.9422   0.04895   0.04219   0.0304   0.0141   1.0000
  11.250   0.9337   0.05140   0.04485   0.0331   0.0135   1.0000
  11.500   0.9230   0.05422   0.04789   0.0355   0.0132   1.0000
  11.750   0.9101   0.05746   0.05135   0.0373   0.0130   1.0000
  12.000   0.8951   0.06080   0.05485   0.0381   0.0122   1.0000
  12.250   0.8730   0.06572   0.05990   0.0380   0.0119   1.0000
  12.500   0.8611   0.06988   0.06429   0.0371   0.0123   1.0000
  12.750   0.8421   0.07565   0.07028   0.0346   0.0124   1.0000
  13.000   0.7995   0.08812   0.08315   0.0272   0.0144   1.0000
  13.250   0.7669   0.10066   0.09581   0.0190   0.0154   1.0000
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