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MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 116 9.84% (mh116-il)
Reynolds number: 100,000
Max Cl/Cd: 63.03 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh116-il-100000-n5.txt
Download as CSV file: xf-mh116-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 116  9.84%                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3482   0.09225   0.08768  -0.0390   1.0000   0.0184
  -8.000  -0.3596   0.09025   0.08578  -0.0371   1.0000   0.0182
  -7.750  -0.3708   0.08801   0.08363  -0.0357   0.9993   0.0179
  -7.500  -0.3601   0.08296   0.07861  -0.0416   0.9919   0.0174
  -7.250  -0.3488   0.07740   0.07307  -0.0486   0.9833   0.0169
  -7.000  -0.3353   0.07051   0.06618  -0.0578   0.9730   0.0165
  -6.750  -0.3202   0.06163   0.05725  -0.0695   0.9628   0.0158
  -6.500  -0.3047   0.04617   0.04127  -0.0857   0.9523   0.0147
  -6.250  -0.2811   0.03867   0.03304  -0.0927   0.9451   0.0144
  -6.000  -0.2560   0.03398   0.02773  -0.0961   0.9388   0.0146
  -5.750  -0.2280   0.03062   0.02385  -0.0984   0.9332   0.0152
  -5.500  -0.1939   0.02841   0.02123  -0.1010   0.9299   0.0169
  -5.250  -0.1671   0.02648   0.01883  -0.1016   0.9233   0.0191
  -5.000  -0.1343   0.02448   0.01635  -0.1028   0.9191   0.0212
  -4.750  -0.0996   0.02253   0.01421  -0.1047   0.9161   0.0241
  -4.500  -0.0724   0.02142   0.01286  -0.1047   0.9095   0.0289
  -4.250  -0.0401   0.02021   0.01152  -0.1057   0.9050   0.0400
  -4.000  -0.0048   0.01918   0.01048  -0.1075   0.9018   0.0638
  -3.750   0.0210   0.01850   0.00978  -0.1073   0.8944   0.0887
  -3.500   0.0541   0.01787   0.00914  -0.1084   0.8901   0.1214
  -3.250   0.0851   0.01738   0.00870  -0.1093   0.8851   0.1572
  -3.000   0.1134   0.01699   0.00835  -0.1095   0.8786   0.1944
  -2.750   0.1470   0.01655   0.00796  -0.1106   0.8747   0.2399
  -2.500   0.1731   0.01629   0.00775  -0.1104   0.8675   0.2858
  -2.250   0.2042   0.01593   0.00750  -0.1111   0.8625   0.3433
  -2.000   0.2329   0.01562   0.00733  -0.1113   0.8568   0.4069
  -1.750   0.2598   0.01535   0.00723  -0.1110   0.8503   0.4793
  -1.500   0.2910   0.01496   0.00704  -0.1113   0.8461   0.5688
  -1.250   0.3121   0.01477   0.00709  -0.1097   0.8381   0.6575
  -1.000   0.3373   0.01443   0.00698  -0.1083   0.8331   0.7619
  -0.750   0.3604   0.01423   0.00693  -0.1065   0.8259   0.8820
  -0.500   0.4038   0.01405   0.00663  -0.1094   0.8209   1.0000
  -0.250   0.4319   0.01413   0.00656  -0.1095   0.8141   1.0000
   0.000   0.4608   0.01419   0.00648  -0.1097   0.8074   1.0000
   0.250   0.4891   0.01428   0.00644  -0.1098   0.8007   1.0000
   0.500   0.5173   0.01435   0.00641  -0.1099   0.7936   1.0000
   0.750   0.5451   0.01445   0.00642  -0.1098   0.7864   1.0000
   1.000   0.5735   0.01452   0.00643  -0.1098   0.7792   1.0000
   1.250   0.6002   0.01464   0.00648  -0.1096   0.7712   1.0000
   1.500   0.6296   0.01468   0.00646  -0.1097   0.7641   1.0000
   1.750   0.6550   0.01482   0.00658  -0.1093   0.7550   1.0000
   2.000   0.6846   0.01485   0.00658  -0.1094   0.7477   1.0000
   2.250   0.7101   0.01499   0.00671  -0.1089   0.7381   1.0000
   2.500   0.7365   0.01511   0.00682  -0.1085   0.7289   1.0000
   2.750   0.7659   0.01514   0.00682  -0.1086   0.7208   1.0000
   3.000   0.7907   0.01529   0.00700  -0.1079   0.7100   1.0000
   3.250   0.8164   0.01542   0.00719  -0.1074   0.6994   1.0000
   3.500   0.8430   0.01552   0.00730  -0.1070   0.6889   1.0000
   3.750   0.8701   0.01561   0.00740  -0.1067   0.6781   1.0000
   4.000   0.8961   0.01572   0.00758  -0.1061   0.6660   1.0000
   4.250   0.9210   0.01586   0.00777  -0.1054   0.6527   1.0000
   4.500   0.9461   0.01599   0.00794  -0.1047   0.6385   1.0000
   4.750   0.9709   0.01612   0.00813  -0.1040   0.6232   1.0000
   5.000   0.9943   0.01631   0.00837  -0.1030   0.6057   1.0000
   5.250   1.0179   0.01648   0.00864  -0.1020   0.5870   1.0000
   5.500   1.0414   0.01667   0.00886  -0.1009   0.5668   1.0000
   5.750   1.0633   0.01692   0.00915  -0.0997   0.5438   1.0000
   6.000   1.0847   0.01721   0.00946  -0.0984   0.5182   1.0000
   6.250   1.1053   0.01755   0.00979  -0.0969   0.4895   1.0000
   6.500   1.1245   0.01798   0.01021  -0.0953   0.4573   1.0000
   6.750   1.1422   0.01851   0.01068  -0.0934   0.4217   1.0000
   7.000   1.1580   0.01917   0.01121  -0.0914   0.3844   1.0000
   7.250   1.1724   0.01993   0.01186  -0.0892   0.3475   1.0000
   7.500   1.1856   0.02078   0.01260  -0.0869   0.3113   1.0000
   7.750   1.1976   0.02171   0.01342  -0.0845   0.2774   1.0000
   8.000   1.2085   0.02270   0.01431  -0.0821   0.2447   1.0000
   8.250   1.2180   0.02371   0.01530  -0.0795   0.2157   1.0000
   8.500   1.2263   0.02480   0.01632  -0.0768   0.1887   1.0000
   8.750   1.2342   0.02597   0.01742  -0.0741   0.1647   1.0000
   9.000   1.2418   0.02722   0.01861  -0.0716   0.1413   1.0000
   9.250   1.2494   0.02852   0.01988  -0.0693   0.1201   1.0000
   9.500   1.2553   0.02998   0.02127  -0.0669   0.1008   1.0000
   9.750   1.2623   0.03145   0.02274  -0.0647   0.0838   1.0000
  10.000   1.2680   0.03306   0.02438  -0.0626   0.0691   1.0000
  10.250   1.2721   0.03487   0.02619  -0.0604   0.0558   1.0000
  10.500   1.2744   0.03691   0.02826  -0.0583   0.0461   1.0000
  10.750   1.2749   0.03918   0.03054  -0.0562   0.0383   1.0000
  11.000   1.2767   0.04142   0.03293  -0.0545   0.0313   1.0000
  11.250   1.2762   0.04397   0.03560  -0.0527   0.0270   1.0000
  11.500   1.2773   0.04643   0.03819  -0.0513   0.0229   1.0000
  11.750   1.2717   0.04970   0.04153  -0.0499   0.0207   1.0000
  12.000   1.2723   0.05250   0.04457  -0.0488   0.0184   1.0000
  12.250   1.2721   0.05539   0.04763  -0.0480   0.0165   1.0000
  12.500   1.2689   0.05868   0.05104  -0.0476   0.0149   1.0000
  12.750   1.2616   0.06265   0.05512  -0.0472   0.0139   1.0000
  13.000   1.2604   0.06613   0.05886  -0.0469   0.0131   1.0000
  13.250   1.2575   0.06994   0.06291  -0.0467   0.0125   1.0000
  13.500   1.2536   0.07403   0.06723  -0.0469   0.0119   1.0000
  13.750   1.2483   0.07843   0.07187  -0.0473   0.0115   1.0000
  14.000   1.2422   0.08308   0.07675  -0.0482   0.0112   1.0000
  14.250   1.2345   0.08814   0.08204  -0.0496   0.0109   1.0000
  14.500   1.2258   0.09355   0.08767  -0.0514   0.0106   1.0000
  14.750   1.2157   0.09939   0.09373  -0.0538   0.0104   1.0000
  15.000   1.2045   0.10572   0.10027  -0.0567   0.0103   1.0000
  15.250   1.1926   0.11246   0.10721  -0.0602   0.0101   1.0000
  15.500   1.1792   0.11997   0.11495  -0.0643   0.0102   1.0000
  15.750   1.1642   0.12828   0.12348  -0.0692   0.0103   1.0000
  16.000   1.1471   0.13772   0.13314  -0.0750   0.0105   1.0000
  16.250   1.1283   0.14836   0.14398  -0.0818   0.0109   1.0000
  16.500   1.1086   0.16016   0.15593  -0.0893   0.0113   1.0000
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