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MH 95 15.86% (mh95-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: MH 95 15.86% (mh95-il)
Reynolds number: 50,000
Max Cl/Cd: 29.69 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh95-il-50000.txt
Download as CSV file: xf-mh95-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 95  15.86%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5438   0.09461   0.08729  -0.0526   1.0000   0.1380
 -10.500  -0.5142   0.09402   0.08676  -0.0487   1.0000   0.1413
 -10.250  -0.5540   0.08536   0.07813  -0.0521   1.0000   0.1323
 -10.000  -0.6773   0.07760   0.07021  -0.0499   1.0000   0.1230
  -9.750  -0.6929   0.07445   0.06705  -0.0466   1.0000   0.1217
  -9.500  -0.7154   0.07142   0.06399  -0.0425   1.0000   0.1204
  -9.250  -0.7386   0.06822   0.06068  -0.0383   1.0000   0.1187
  -9.000  -0.7621   0.06496   0.05723  -0.0338   1.0000   0.1172
  -8.750  -0.7830   0.06162   0.05362  -0.0292   1.0000   0.1155
  -8.500  -0.7987   0.05835   0.05000  -0.0248   1.0000   0.1140
  -8.250  -0.8064   0.05535   0.04667  -0.0209   1.0000   0.1136
  -8.000  -0.8076   0.05260   0.04360  -0.0176   1.0000   0.1137
  -7.750  -0.8037   0.05006   0.04080  -0.0147   1.0000   0.1146
  -7.500  -0.7972   0.04757   0.03802  -0.0119   1.0000   0.1154
  -7.250  -0.7876   0.04519   0.03534  -0.0094   1.0000   0.1164
  -7.000  -0.7748   0.04294   0.03279  -0.0072   1.0000   0.1175
  -6.750  -0.7591   0.04087   0.03042  -0.0052   1.0000   0.1194
  -6.500  -0.7418   0.03905   0.02824  -0.0032   1.0000   0.1224
  -6.250  -0.7213   0.03728   0.02647  -0.0019   1.0000   0.1278
  -6.000  -0.7007   0.03589   0.02500  -0.0005   1.0000   0.1354
  -5.750  -0.6764   0.03439   0.02360   0.0006   1.0000   0.1446
  -5.500  -0.6536   0.03310   0.02241   0.0020   1.0000   0.1587
  -5.250  -0.6343   0.03179   0.02125   0.0038   1.0000   0.1840
  -5.000  -0.6227   0.03004   0.02008   0.0066   1.0000   0.2300
  -4.750  -0.6302   0.02710   0.01867   0.0121   1.0000   0.3691
  -4.500  -0.6361   0.02652   0.01966   0.0210   1.0000   0.5752
  -4.250  -0.6291   0.02802   0.02131   0.0281   1.0000   0.6618
  -4.000  -0.6168   0.03009   0.02332   0.0349   1.0000   0.7138
  -3.750  -0.5874   0.03348   0.02657   0.0409   1.0000   0.7587
  -3.500  -0.5373   0.03710   0.02989   0.0435   1.0000   0.8054
  -3.250  -0.4476   0.03970   0.03201   0.0370   1.0000   0.8428
  -3.000  -0.3459   0.04077   0.03262   0.0256   1.0000   0.8726
  -2.750  -0.2858   0.04083   0.03239   0.0196   1.0000   0.9011
  -2.500  -0.2336   0.04069   0.03202   0.0141   1.0000   0.9288
  -2.250  -0.1620   0.04027   0.03136   0.0046   1.0000   0.9545
  -2.000  -0.0919   0.03973   0.03059  -0.0053   1.0000   0.9793
  -1.750  -0.0211   0.03915   0.02980  -0.0160   1.0000   1.0000
  -1.500  -0.0240   0.03904   0.02967  -0.0135   1.0000   1.0000
  -1.250  -0.0269   0.03900   0.02960  -0.0111   1.0000   1.0000
  -1.000  -0.0296   0.03902   0.02960  -0.0086   1.0000   1.0000
  -0.750  -0.0323   0.03909   0.02965  -0.0061   1.0000   1.0000
  -0.500  -0.0349   0.03922   0.02975  -0.0037   1.0000   1.0000
  -0.250  -0.0375   0.03939   0.02991  -0.0013   1.0000   1.0000
   0.000  -0.0343   0.03962   0.03012   0.0001   0.9986   1.0000
   0.250   0.0359   0.04037   0.03080  -0.0105   0.9762   1.0000
   0.500   0.0945   0.04094   0.03132  -0.0184   0.9557   1.0000
   0.750   0.1384   0.04118   0.03153  -0.0233   0.9342   1.0000
   1.000   0.1831   0.04136   0.03170  -0.0279   0.9132   1.0000
   1.250   0.2321   0.04142   0.03175  -0.0329   0.8932   1.0000
   1.500   0.2805   0.04131   0.03164  -0.0373   0.8733   1.0000
   1.750   0.3085   0.04123   0.03157  -0.0382   0.8513   1.0000
   2.000   0.3470   0.04098   0.03134  -0.0405   0.8306   1.0000
   2.250   0.3913   0.04050   0.03090  -0.0432   0.8106   1.0000
   2.500   0.4412   0.03973   0.03018  -0.0464   0.7912   1.0000
   2.750   0.4954   0.03863   0.02915  -0.0498   0.7726   1.0000
   3.000   0.5626   0.03692   0.02752  -0.0546   0.7544   1.0000
   3.250   0.6374   0.03477   0.02546  -0.0602   0.7354   1.0000
   3.500   0.6657   0.03407   0.02480  -0.0592   0.7109   1.0000
   3.750   0.7222   0.03235   0.02311  -0.0618   0.6865   1.0000
   4.000   0.7717   0.03096   0.02169  -0.0635   0.6596   1.0000
   4.250   0.8048   0.03026   0.02092  -0.0629   0.6309   1.0000
   4.500   0.8283   0.03004   0.02062  -0.0611   0.6027   1.0000
   4.750   0.8598   0.02961   0.02001  -0.0605   0.5740   1.0000
   5.000   0.8693   0.02999   0.02034  -0.0570   0.5475   1.0000
   5.250   0.8916   0.03003   0.02022  -0.0552   0.5213   1.0000
   5.500   0.9034   0.03047   0.02057  -0.0522   0.4971   1.0000
   5.750   0.9142   0.03098   0.02101  -0.0490   0.4739   1.0000
   6.000   0.9292   0.03144   0.02134  -0.0465   0.4515   1.0000
   6.500   0.9558   0.03268   0.02234  -0.0412   0.4105   1.0000
   6.750   0.9649   0.03347   0.02307  -0.0380   0.3923   1.0000
   7.000   0.9755   0.03429   0.02381  -0.0350   0.3751   1.0000
   7.250   0.9872   0.03516   0.02461  -0.0323   0.3589   1.0000
   7.500   0.9828   0.03627   0.02588  -0.0272   0.3461   1.0000
   7.750   0.9861   0.03738   0.02701  -0.0234   0.3338   1.0000
   8.000   1.0006   0.03838   0.02791  -0.0212   0.3214   1.0000
   8.250   0.9938   0.03966   0.02936  -0.0160   0.3124   1.0000
   8.500   1.0033   0.04095   0.03062  -0.0132   0.3030   1.0000
   8.750   0.9962   0.04238   0.03221  -0.0081   0.2955   1.0000
   9.000   1.0110   0.04371   0.03347  -0.0063   0.2867   1.0000
   9.250   0.9942   0.04570   0.03572  -0.0005   0.2815   1.0000
   9.500   1.0144   0.04715   0.03713   0.0004   0.2737   1.0000
   9.750   1.0065   0.04956   0.03970   0.0044   0.2693   1.0000
  10.000   0.9776   0.05256   0.04298   0.0104   0.2665   1.0000
  10.250   0.9423   0.05593   0.04656   0.0164   0.2645   1.0000
  10.500   0.8851   0.06112   0.05193   0.0222   0.2646   1.0000
  10.750   0.7714   0.07378   0.06470   0.0238   0.2690   1.0000
  11.000   0.6887   0.08981   0.08073   0.0177   0.2719   1.0000
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