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MH 95 15.86% (mh95-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 95 15.86% (mh95-il)
Reynolds number: 100,000
Max Cl/Cd: 44.54 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh95-il-100000.txt
Download as CSV file: xf-mh95-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5467   0.08741   0.08222  -0.0558   1.0000   0.1004
 -10.750  -0.6403   0.07349   0.06805  -0.0599   1.0000   0.0815
 -10.500  -0.6969   0.06907   0.06347  -0.0562   1.0000   0.0793
 -10.250  -0.7660   0.06686   0.06104  -0.0475   1.0000   0.0777
 -10.000  -0.7846   0.06390   0.05792  -0.0428   1.0000   0.0739
  -9.750  -0.8025   0.06081   0.05469  -0.0383   1.0000   0.0721
  -9.500  -0.8715   0.05720   0.05011  -0.0269   1.0000   0.0667
  -9.250  -0.8612   0.05377   0.04670  -0.0253   1.0000   0.0658
  -9.000  -0.8612   0.05092   0.04366  -0.0221   1.0000   0.0649
  -8.750  -0.8621   0.04820   0.04069  -0.0186   1.0000   0.0640
  -8.500  -0.8605   0.04572   0.03793  -0.0153   1.0000   0.0635
  -8.250  -0.8564   0.04344   0.03534  -0.0121   1.0000   0.0634
  -8.000  -0.8495   0.04145   0.03306  -0.0092   1.0000   0.0638
  -7.750  -0.8399   0.03955   0.03086  -0.0066   1.0000   0.0643
  -7.500  -0.8276   0.03775   0.02877  -0.0042   1.0000   0.0647
  -7.250  -0.8125   0.03604   0.02680  -0.0022   1.0000   0.0650
  -7.000  -0.7957   0.03449   0.02503  -0.0003   1.0000   0.0654
  -6.750  -0.7779   0.03312   0.02345   0.0014   1.0000   0.0661
  -6.500  -0.7590   0.03185   0.02202   0.0030   1.0000   0.0671
  -6.250  -0.7387   0.03041   0.02069   0.0041   1.0000   0.0688
  -6.000  -0.7210   0.02946   0.01978   0.0057   1.0000   0.0714
  -5.750  -0.7040   0.02867   0.01892   0.0074   1.0000   0.0749
  -5.500  -0.6878   0.02764   0.01800   0.0091   1.0000   0.0785
  -5.250  -0.6728   0.02681   0.01725   0.0110   1.0000   0.0831
  -5.000  -0.6592   0.02593   0.01641   0.0131   1.0000   0.0882
  -4.750  -0.6464   0.02514   0.01569   0.0153   1.0000   0.0961
  -4.500  -0.6349   0.02415   0.01486   0.0175   1.0000   0.1123
  -4.250  -0.6280   0.02228   0.01378   0.0203   1.0000   0.1875
  -4.000  -0.6226   0.02013   0.01333   0.0230   0.9982   0.4404
  -3.750  -0.5925   0.02033   0.01445   0.0233   0.9899   0.6031
  -3.500  -0.5573   0.02156   0.01586   0.0232   0.9813   0.6875
  -3.250  -0.5268   0.02279   0.01708   0.0241   0.9713   0.7367
  -3.000  -0.4991   0.02412   0.01838   0.0260   0.9611   0.7714
  -2.750  -0.4645   0.02584   0.02005   0.0275   0.9525   0.7975
  -2.500  -0.4316   0.02698   0.02109   0.0284   0.9429   0.8190
  -2.250  -0.3953   0.02782   0.02180   0.0280   0.9336   0.8347
  -2.000  -0.3487   0.02857   0.02240   0.0254   0.9258   0.8489
  -1.750  -0.3152   0.02894   0.02266   0.0249   0.9155   0.8635
  -1.500  -0.2449   0.02982   0.02338   0.0180   0.9099   0.8727
  -1.250  -0.1942   0.03019   0.02364   0.0141   0.9011   0.8837
  -1.000  -0.1225   0.03055   0.02387   0.0064   0.8947   0.8927
  -0.750  -0.0378   0.03066   0.02386  -0.0038   0.8911   0.8994
  -0.500   0.0150   0.03055   0.02368  -0.0085   0.8797   0.9077
  -0.250   0.0861   0.03013   0.02318  -0.0163   0.8749   0.9150
   0.000   0.1416   0.02972   0.02274  -0.0214   0.8632   0.9223
   0.250   0.2101   0.02892   0.02189  -0.0285   0.8583   0.9296
   0.500   0.2687   0.02819   0.02116  -0.0342   0.8469   0.9356
   0.750   0.3407   0.02701   0.01996  -0.0418   0.8422   0.9414
   1.000   0.3984   0.02603   0.01899  -0.0471   0.8307   0.9469
   1.250   0.4752   0.02460   0.01757  -0.0557   0.8242   0.9514
   1.500   0.5167   0.02378   0.01675  -0.0580   0.8091   0.9579
   1.750   0.5758   0.02262   0.01560  -0.0635   0.7927   0.9626
   2.000   0.6234   0.02174   0.01469  -0.0668   0.7734   0.9681
   2.250   0.6692   0.02094   0.01384  -0.0699   0.7498   0.9730
   2.500   0.7085   0.02036   0.01319  -0.0719   0.7216   0.9783
   2.750   0.7434   0.01995   0.01266  -0.0731   0.6913   0.9836
   3.000   0.7789   0.01956   0.01212  -0.0744   0.6574   0.9885
   3.250   0.8088   0.01938   0.01177  -0.0748   0.6225   0.9935
   3.500   0.8398   0.01921   0.01141  -0.0756   0.5861   0.9984
   3.750   0.8590   0.01932   0.01132  -0.0742   0.5543   1.0000
   4.000   0.8707   0.01955   0.01144  -0.0713   0.5248   1.0000
   4.250   0.8830   0.01983   0.01155  -0.0687   0.4978   1.0000
   4.500   0.8939   0.02014   0.01173  -0.0658   0.4716   1.0000
   4.750   0.9058   0.02048   0.01189  -0.0631   0.4484   1.0000
   5.000   0.9160   0.02084   0.01216  -0.0602   0.4255   1.0000
   5.250   0.9260   0.02121   0.01244  -0.0572   0.4045   1.0000
   5.500   0.9355   0.02160   0.01273  -0.0542   0.3846   1.0000
   5.750   0.9447   0.02201   0.01305  -0.0511   0.3661   1.0000
   6.000   0.9533   0.02244   0.01340  -0.0480   0.3485   1.0000
   6.250   0.9611   0.02288   0.01376  -0.0447   0.3318   1.0000
   6.500   0.9684   0.02334   0.01414  -0.0414   0.3161   1.0000
   6.750   0.9755   0.02383   0.01454  -0.0380   0.3014   1.0000
   7.000   0.9833   0.02435   0.01493  -0.0348   0.2877   1.0000
   7.250   0.9870   0.02479   0.01537  -0.0309   0.2745   1.0000
   7.500   0.9911   0.02530   0.01587  -0.0270   0.2622   1.0000
   7.750   0.9981   0.02587   0.01634  -0.0237   0.2516   1.0000
   8.000   1.0018   0.02634   0.01680  -0.0198   0.2418   1.0000
   8.250   1.0074   0.02693   0.01738  -0.0162   0.2331   1.0000
   8.500   1.0114   0.02741   0.01783  -0.0124   0.2251   1.0000
   8.750   1.0190   0.02807   0.01846  -0.0092   0.2179   1.0000
   9.000   1.0217   0.02856   0.01901  -0.0051   0.2112   1.0000
   9.250   1.0431   0.02950   0.01978  -0.0045   0.2043   1.0000
   9.500   1.0469   0.03018   0.02065  -0.0007   0.1989   1.0000
   9.750   1.0642   0.03101   0.02145   0.0006   0.1930   1.0000
  10.000   1.0884   0.03221   0.02259   0.0006   0.1874   1.0000
  10.250   1.0975   0.03317   0.02376   0.0032   0.1827   1.0000
  10.500   1.1159   0.03419   0.02482   0.0042   0.1781   1.0000
  10.750   1.1506   0.03580   0.02626   0.0023   0.1735   1.0000
  11.000   1.1542   0.03698   0.02777   0.0055   0.1706   1.0000
  11.250   1.1626   0.03828   0.02927   0.0079   0.1672   1.0000
  11.500   1.1746   0.03949   0.03060   0.0096   0.1638   1.0000
  11.750   1.1984   0.04087   0.03195   0.0095   0.1605   1.0000
  12.000   1.2163   0.04300   0.03418   0.0099   0.1580   1.0000
  12.250   1.2077   0.04464   0.03614   0.0144   0.1564   1.0000
  12.500   1.1987   0.04654   0.03832   0.0185   0.1546   1.0000
  12.750   1.1906   0.04860   0.04062   0.0220   0.1529   1.0000
  13.000   1.1842   0.05072   0.04294   0.0250   0.1510   1.0000
  13.250   1.1838   0.05278   0.04513   0.0270   0.1491   1.0000
  13.500   1.1854   0.05491   0.04738   0.0287   0.1474   1.0000
  13.750   1.1979   0.05707   0.04958   0.0291   0.1455   1.0000
  14.000   1.1923   0.06047   0.05310   0.0306   0.1442   1.0000
  14.250   1.1544   0.06461   0.05753   0.0338   0.1439   1.0000
  14.500   1.1119   0.06995   0.06313   0.0355   0.1439   1.0000
  14.750   1.0563   0.07756   0.07099   0.0352   0.1442   1.0000
  15.000   0.5245   0.15645   0.15093  -0.0037   0.2051   1.0000
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