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MH 110 10.01% (mh110-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 110 10.01% (mh110-il)
Reynolds number: 200,000
Max Cl/Cd: 55.96 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh110-il-200000-n5.txt
Download as CSV file: xf-mh110-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 110  10.01%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6896   0.08046   0.07727   0.0133   1.0000   0.0077
  -9.500  -0.7043   0.06956   0.06633   0.0045   1.0000   0.0075
  -9.250  -0.7254   0.06225   0.05889  -0.0013   1.0000   0.0075
  -9.000  -0.7446   0.05764   0.05414  -0.0021   1.0000   0.0074
  -8.750  -0.7624   0.05354   0.04985  -0.0005   1.0000   0.0074
  -8.500  -0.7727   0.04920   0.04525   0.0009   1.0000   0.0073
  -8.250  -0.7771   0.04497   0.04069   0.0026   1.0000   0.0072
  -8.000  -0.7764   0.04096   0.03631   0.0045   1.0000   0.0071
  -7.750  -0.7714   0.03716   0.03209   0.0065   1.0000   0.0071
  -7.500  -0.7619   0.03376   0.02826   0.0084   1.0000   0.0070
  -7.250  -0.7484   0.03084   0.02492   0.0102   1.0000   0.0070
  -7.000  -0.7320   0.02825   0.02194   0.0119   1.0000   0.0070
  -6.750  -0.7132   0.02595   0.01928   0.0134   1.0000   0.0070
  -6.500  -0.6926   0.02399   0.01702   0.0147   1.0000   0.0071
  -6.250  -0.6709   0.02230   0.01510   0.0158   1.0000   0.0072
  -6.000  -0.6487   0.02082   0.01344   0.0170   1.0000   0.0074
  -5.750  -0.6262   0.01953   0.01196   0.0181   1.0000   0.0076
  -5.500  -0.6036   0.01844   0.01074   0.0192   1.0000   0.0079
  -5.250  -0.5830   0.01708   0.00929   0.0205   1.0000   0.0086
  -5.000  -0.5603   0.01621   0.00835   0.0215   1.0000   0.0094
  -4.750  -0.5365   0.01557   0.00766   0.0223   1.0000   0.0113
  -4.500  -0.5131   0.01485   0.00687   0.0232   1.0000   0.0142
  -4.250  -0.4895   0.01416   0.00613   0.0242   1.0000   0.0194
  -4.000  -0.4532   0.01311   0.00526   0.0223   0.9136   0.0582
  -3.750  -0.4242   0.01236   0.00477   0.0220   0.8362   0.1356
  -3.500  -0.4034   0.01182   0.00443   0.0235   0.7837   0.2150
  -3.250  -0.3819   0.01141   0.00412   0.0248   0.7418   0.2816
  -3.000  -0.3603   0.01103   0.00384   0.0261   0.7060   0.3507
  -2.750  -0.3386   0.01066   0.00360   0.0275   0.6746   0.4245
  -2.500  -0.3169   0.01031   0.00336   0.0289   0.6460   0.4974
  -2.250  -0.2952   0.00998   0.00318   0.0304   0.6200   0.5703
  -2.000  -0.2731   0.00968   0.00305   0.0319   0.5957   0.6450
  -1.750  -0.2494   0.00946   0.00297   0.0332   0.5730   0.7152
  -1.500  -0.2223   0.00934   0.00292   0.0340   0.5511   0.7775
  -1.250  -0.1898   0.00935   0.00290   0.0336   0.5291   0.8282
  -1.000  -0.1518   0.00947   0.00292   0.0320   0.5076   0.8650
  -0.750  -0.1129   0.00962   0.00294   0.0301   0.4869   0.8911
  -0.500  -0.0755   0.00979   0.00295   0.0285   0.4680   0.9104
  -0.250  -0.0397   0.00995   0.00297   0.0271   0.4501   0.9263
   0.000  -0.0023   0.01012   0.00300   0.0253   0.4329   0.9386
   0.250   0.0346   0.01029   0.00303   0.0236   0.4174   0.9485
   0.500   0.0699   0.01045   0.00306   0.0222   0.4027   0.9582
   0.750   0.1048   0.01060   0.00309   0.0208   0.3883   0.9670
   1.000   0.1424   0.01072   0.00310   0.0188   0.3744   0.9733
   1.250   0.1771   0.01084   0.00313   0.0174   0.3623   0.9805
   1.500   0.2145   0.01093   0.00312   0.0153   0.3509   0.9856
   1.750   0.2511   0.01103   0.00315   0.0134   0.3401   0.9912
   2.000   0.2883   0.01110   0.00316   0.0113   0.3291   0.9961
   2.250   0.3238   0.01117   0.00317   0.0095   0.3192   1.0000
   2.500   0.3478   0.01127   0.00322   0.0101   0.3118   1.0000
   2.750   0.3721   0.01136   0.00331   0.0108   0.3046   1.0000
   3.000   0.3962   0.01150   0.00340   0.0114   0.2984   1.0000
   3.250   0.4206   0.01161   0.00353   0.0120   0.2917   1.0000
   3.500   0.4448   0.01178   0.00364   0.0127   0.2857   1.0000
   3.750   0.4692   0.01191   0.00383   0.0133   0.2795   1.0000
   4.000   0.4935   0.01208   0.00399   0.0139   0.2742   1.0000
   4.250   0.5178   0.01228   0.00419   0.0146   0.2697   1.0000
   4.500   0.5423   0.01246   0.00442   0.0152   0.2648   1.0000
   4.750   0.5667   0.01267   0.00466   0.0158   0.2602   1.0000
   5.000   0.5910   0.01290   0.00491   0.0164   0.2559   1.0000
   5.250   0.6155   0.01311   0.00520   0.0170   0.2511   1.0000
   5.500   0.6398   0.01335   0.00549   0.0177   0.2473   1.0000
   5.750   0.6639   0.01365   0.00579   0.0183   0.2438   1.0000
   6.000   0.6885   0.01389   0.00618   0.0189   0.2394   1.0000
   6.250   0.7128   0.01415   0.00653   0.0196   0.2350   1.0000
   6.500   0.7368   0.01445   0.00686   0.0202   0.2309   1.0000
   6.750   0.7611   0.01468   0.00724   0.0208   0.2247   1.0000
   7.000   0.7849   0.01491   0.00751   0.0215   0.2172   1.0000
   7.250   0.8092   0.01508   0.00783   0.0221   0.2073   1.0000
   7.500   0.8332   0.01528   0.00817   0.0227   0.1961   1.0000
   7.750   0.8570   0.01551   0.00850   0.0233   0.1839   1.0000
   8.000   0.8806   0.01579   0.00888   0.0239   0.1706   1.0000
   8.250   0.9037   0.01615   0.00929   0.0245   0.1496   1.0000
   8.500   0.9228   0.01711   0.00999   0.0252   0.0976   1.0000
   8.750   0.9378   0.01872   0.01136   0.0262   0.0550   1.0000
   9.000   0.9537   0.02012   0.01270   0.0272   0.0341   1.0000
   9.250   0.9697   0.02141   0.01404   0.0283   0.0233   1.0000
   9.500   0.9841   0.02280   0.01551   0.0296   0.0167   1.0000
   9.750   0.9962   0.02432   0.01719   0.0308   0.0126   1.0000
  10.000   1.0073   0.02583   0.01889   0.0322   0.0109   1.0000
  10.250   1.0180   0.02724   0.02044   0.0335   0.0091   1.0000
  10.500   1.0252   0.02884   0.02215   0.0348   0.0078   1.0000
  10.750   1.0255   0.03092   0.02437   0.0362   0.0067   1.0000
  11.000   1.0211   0.03301   0.02663   0.0379   0.0064   1.0000
  11.250   1.0114   0.03605   0.02982   0.0376   0.0063   1.0000
  11.500   1.0044   0.03991   0.03383   0.0355   0.0063   1.0000
  11.750   0.9954   0.04441   0.03848   0.0330   0.0063   1.0000
  12.000   0.9869   0.04892   0.04312   0.0306   0.0059   1.0000
  12.250   0.9778   0.05347   0.04778   0.0284   0.0059   1.0000
  12.500   0.9686   0.05807   0.05248   0.0263   0.0056   1.0000
  12.750   0.9599   0.06256   0.05707   0.0243   0.0055   1.0000
  13.000   0.9527   0.06683   0.06144   0.0225   0.0057   1.0000
  13.250   0.9430   0.07165   0.06635   0.0203   0.0053   1.0000
  13.500   0.9374   0.07572   0.07052   0.0187   0.0055   1.0000
  13.750   0.9275   0.08083   0.07570   0.0163   0.0050   1.0000
  14.000   0.9230   0.08505   0.08002   0.0146   0.0051   1.0000
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