Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH 116 9.84% (mh116-il)
Reynolds number: 1,000,000
Max Cl/Cd: 150.79 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh116-il-1000000.txt
Download as CSV file: xf-mh116-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3354   0.11235   0.11072  -0.0377   1.0000   0.0086
 -10.250  -0.3345   0.10926   0.10765  -0.0380   1.0000   0.0088
 -10.000  -0.3336   0.10640   0.10481  -0.0380   1.0000   0.0090
  -9.750  -0.3328   0.10343   0.10187  -0.0383   0.9999   0.0090
  -9.500  -0.3205   0.09878   0.09722  -0.0424   0.9989   0.0091
  -9.250  -0.3079   0.09412   0.09257  -0.0467   0.9975   0.0091
  -9.000  -0.2953   0.08924   0.08768  -0.0515   0.9956   0.0091
  -8.750  -0.2971   0.08141   0.07988  -0.0579   0.9924   0.0096
  -8.500  -0.2834   0.07803   0.07651  -0.0618   0.9888   0.0099
  -8.250  -0.2685   0.07385   0.07233  -0.0670   0.9851   0.0102
  -8.000  -0.2550   0.06939   0.06787  -0.0726   0.9796   0.0105
  -7.750  -0.2419   0.06440   0.06289  -0.0793   0.9711   0.0108
  -7.500  -0.2198   0.05690   0.05537  -0.0924   0.9612   0.0110
  -7.250  -0.1919   0.04492   0.04326  -0.1124   0.9467   0.0113
  -7.000  -0.1830   0.03409   0.03203  -0.1214   0.9263   0.0116
  -6.750  -0.1724   0.02912   0.02668  -0.1229   0.9109   0.0123
  -6.000  -0.1272   0.01478   0.01055  -0.1216   0.8778   0.0076
  -5.750  -0.1035   0.01231   0.00758  -0.1207   0.8700   0.0060
  -5.500  -0.0772   0.01171   0.00684  -0.1204   0.8624   0.0059
  -5.250  -0.0506   0.01113   0.00616  -0.1201   0.8553   0.0058
  -5.000  -0.0247   0.01030   0.00517  -0.1198   0.8480   0.0057
  -4.750   0.0016   0.00953   0.00426  -0.1196   0.8409   0.0057
  -4.500   0.0285   0.00899   0.00359  -0.1194   0.8338   0.0057
  -4.250   0.0558   0.00853   0.00301  -0.1193   0.8269   0.0058
  -4.000   0.0832   0.00810   0.00242  -0.1191   0.8201   0.0064
  -3.750   0.1110   0.00782   0.00208  -0.1190   0.8133   0.0085
  -3.500   0.1380   0.00733   0.00176  -0.1189   0.8065   0.0534
  -3.250   0.1656   0.00712   0.00163  -0.1189   0.7998   0.0789
  -3.000   0.1932   0.00696   0.00151  -0.1189   0.7930   0.1042
  -2.750   0.2209   0.00679   0.00141  -0.1190   0.7863   0.1359
  -2.500   0.2484   0.00661   0.00133  -0.1190   0.7794   0.1767
  -2.250   0.2761   0.00646   0.00127  -0.1191   0.7728   0.2140
  -2.000   0.3038   0.00632   0.00121  -0.1191   0.7657   0.2521
  -1.750   0.3316   0.00622   0.00116  -0.1191   0.7589   0.2853
  -1.500   0.3592   0.00611   0.00112  -0.1191   0.7515   0.3265
  -1.250   0.3869   0.00600   0.00110  -0.1191   0.7441   0.3686
  -1.000   0.4144   0.00591   0.00108  -0.1191   0.7364   0.4147
  -0.750   0.4420   0.00578   0.00108  -0.1191   0.7286   0.4732
  -0.500   0.4692   0.00567   0.00109  -0.1190   0.7210   0.5367
  -0.250   0.4967   0.00553   0.00111  -0.1190   0.7130   0.6010
   0.000   0.5236   0.00542   0.00114  -0.1189   0.7054   0.6694
   0.250   0.5503   0.00529   0.00119  -0.1186   0.6971   0.7395
   0.500   0.5761   0.00519   0.00124  -0.1181   0.6891   0.8072
   0.750   0.5996   0.00509   0.00130  -0.1169   0.6806   0.8769
   1.000   0.6216   0.00499   0.00132  -0.1153   0.6723   0.9479
   1.250   0.6569   0.00501   0.00130  -0.1170   0.6635   1.0000
   1.500   0.6843   0.00509   0.00134  -0.1169   0.6540   1.0000
   1.750   0.7118   0.00516   0.00138  -0.1168   0.6442   1.0000
   2.000   0.7389   0.00526   0.00143  -0.1167   0.6343   1.0000
   2.250   0.7659   0.00537   0.00148  -0.1165   0.6235   1.0000
   2.500   0.7930   0.00546   0.00154  -0.1164   0.6119   1.0000
   2.750   0.8200   0.00557   0.00162  -0.1163   0.5994   1.0000
   3.000   0.8467   0.00569   0.00170  -0.1161   0.5860   1.0000
   3.250   0.8732   0.00582   0.00179  -0.1158   0.5722   1.0000
   3.500   0.8995   0.00597   0.00188  -0.1156   0.5567   1.0000
   3.750   0.9254   0.00614   0.00201  -0.1152   0.5401   1.0000
   4.000   0.9515   0.00631   0.00213  -0.1149   0.5218   1.0000
   4.250   0.9764   0.00655   0.00227  -0.1145   0.4983   1.0000
   4.500   1.0011   0.00681   0.00244  -0.1139   0.4716   1.0000
   4.750   1.0253   0.00710   0.00264  -0.1133   0.4432   1.0000
   5.000   1.0487   0.00747   0.00286  -0.1126   0.4084   1.0000
   5.250   1.0715   0.00787   0.00312  -0.1118   0.3744   1.0000
   5.500   1.0938   0.00832   0.00340  -0.1109   0.3374   1.0000
   5.750   1.1163   0.00874   0.00369  -0.1101   0.3063   1.0000
   6.000   1.1384   0.00920   0.00402  -0.1092   0.2747   1.0000
   6.250   1.1572   0.00989   0.00444  -0.1078   0.2236   1.0000
   6.500   1.1754   0.01061   0.00490  -0.1063   0.1757   1.0000
   6.750   1.1945   0.01126   0.00534  -0.1050   0.1401   1.0000
   7.000   1.2150   0.01177   0.00575  -0.1039   0.1163   1.0000
   7.250   1.2355   0.01227   0.00615  -0.1028   0.0972   1.0000
   7.500   1.2546   0.01286   0.00661  -0.1015   0.0762   1.0000
   7.750   1.2731   0.01347   0.00712  -0.1000   0.0562   1.0000
   8.000   1.2914   0.01406   0.00763  -0.0986   0.0418   1.0000
   8.250   1.3087   0.01469   0.00818  -0.0970   0.0279   1.0000
   8.500   1.3231   0.01548   0.00886  -0.0949   0.0140   1.0000
   8.750   1.3300   0.01659   0.00990  -0.0913   0.0028   1.0000
   9.000   1.3454   0.01713   0.01051  -0.0893   0.0025   1.0000
   9.250   1.3586   0.01783   0.01127  -0.0869   0.0021   1.0000
   9.500   1.3692   0.01871   0.01225  -0.0842   0.0019   1.0000
   9.750   1.3794   0.01962   0.01329  -0.0815   0.0018   1.0000
  10.000   1.3875   0.02069   0.01447  -0.0787   0.0017   1.0000
  10.250   1.3956   0.02178   0.01566  -0.0760   0.0017   1.0000
  10.500   1.4040   0.02287   0.01684  -0.0735   0.0017   1.0000
  10.750   1.4107   0.02411   0.01819  -0.0709   0.0017   1.0000
  11.000   1.4160   0.02550   0.01969  -0.0684   0.0017   1.0000
  11.250   1.4211   0.02697   0.02126  -0.0660   0.0017   1.0000
  11.500   1.4240   0.02867   0.02308  -0.0636   0.0017   1.0000
  11.750   1.4256   0.03056   0.02509  -0.0612   0.0017   1.0000
  12.000   1.4264   0.03263   0.02729  -0.0591   0.0017   1.0000
  12.250   1.4270   0.03481   0.02959  -0.0572   0.0017   1.0000
  12.500   1.4248   0.03739   0.03230  -0.0553   0.0017   1.0000
  12.750   1.4220   0.04016   0.03521  -0.0537   0.0017   1.0000
  13.000   1.4183   0.04317   0.03838  -0.0523   0.0017   1.0000
  13.250   1.4129   0.04652   0.04188  -0.0511   0.0017   1.0000
  13.500   1.4016   0.05084   0.04639  -0.0500   0.0017   1.0000
  13.750   1.3997   0.05403   0.04970  -0.0496   0.0017   1.0000
  14.000   1.3971   0.05742   0.05323  -0.0495   0.0017   1.0000
  14.250   1.3935   0.06111   0.05705  -0.0496   0.0017   1.0000
  14.500   1.3898   0.06494   0.06102  -0.0501   0.0018   1.0000
  14.750   1.3845   0.06919   0.06540  -0.0508   0.0018   1.0000
  15.000   1.3788   0.07369   0.07003  -0.0519   0.0018   1.0000
  15.250   1.3718   0.07861   0.07509  -0.0534   0.0018   1.0000
  15.500   1.3642   0.08382   0.08044  -0.0553   0.0018   1.0000
  15.750   1.3557   0.08942   0.08619  -0.0575   0.0018   1.0000
  16.000   1.3464   0.09541   0.09232  -0.0602   0.0018   1.0000
  16.250   1.3366   0.10176   0.09880  -0.0632   0.0019   1.0000
  16.500   1.3254   0.10861   0.10581  -0.0667   0.0019   1.0000
  16.750   1.3140   0.11577   0.11312  -0.0706   0.0019   1.0000
  17.000   1.3013   0.12348   0.12098  -0.0749   0.0019   1.0000
  17.250   1.2874   0.13174   0.12939  -0.0797   0.0020   1.0000
  17.500   1.2721   0.14056   0.13838  -0.0850   0.0020   1.0000
  17.750   1.0546   0.15632   0.15464  -0.0940   0.0019   1.0000
<< Back to MH 116 9.84% (mh116-il)

Polar data table (+)

Polar graphs


<< Back to MH 116 9.84% (mh116-il)