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

MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 32 8.7% (mh32-il)
Reynolds number: 100,000
Max Cl/Cd: 53.89 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh32-il-100000.txt
Download as CSV file: xf-mh32-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 32  8.7%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3364   0.09505   0.09051  -0.0266   1.0000   0.0849
  -8.750  -0.3509   0.09205   0.08759  -0.0304   1.0000   0.0876
  -8.500  -0.3616   0.08880   0.08442  -0.0334   1.0000   0.0880
  -8.250  -0.3348   0.08395   0.07955  -0.0287   1.0000   0.0951
  -8.000  -0.3411   0.08064   0.07631  -0.0304   1.0000   0.0993
  -7.750  -0.3552   0.07743   0.07320  -0.0330   1.0000   0.1007
  -7.500  -0.4474   0.08273   0.07831  -0.0398   1.0000   0.0889
  -7.250  -0.4236   0.08041   0.07602  -0.0304   1.0000   0.0960
  -7.000  -0.4283   0.07709   0.07277  -0.0326   1.0000   0.0977
  -6.750  -0.4508   0.07344   0.06901  -0.0414   1.0000   0.1015
  -6.500  -0.4388   0.07007   0.06584  -0.0354   1.0000   0.1051
  -6.250  -0.4052   0.05782   0.05401  -0.0307   1.0000   0.1180
  -6.000  -0.4064   0.05538   0.05161  -0.0287   1.0000   0.1251
  -5.750  -0.4388   0.06151   0.05728  -0.0339   1.0000   0.1243
  -5.500  -0.4375   0.05822   0.05394  -0.0338   1.0000   0.1330
  -5.250  -0.4334   0.05520   0.05084  -0.0337   1.0000   0.1455
  -5.000  -0.4264   0.05230   0.04784  -0.0334   1.0000   0.1584
  -4.750  -0.4170   0.04951   0.04491  -0.0328   1.0000   0.1719
  -4.500  -0.3757   0.03525   0.02887  -0.0380   1.0000   0.0594
  -4.250  -0.3519   0.03153   0.02418  -0.0365   1.0000   0.0493
  -4.000  -0.3307   0.02804   0.02038  -0.0358   1.0000   0.0473
  -3.750  -0.3072   0.02540   0.01724  -0.0348   1.0000   0.0467
  -3.500  -0.2826   0.02340   0.01484  -0.0338   1.0000   0.0472
  -3.250  -0.2580   0.02138   0.01257  -0.0329   1.0000   0.0515
  -3.000  -0.2349   0.02038   0.01143  -0.0319   1.0000   0.0611
  -2.750  -0.2118   0.01891   0.00999  -0.0309   1.0000   0.0743
  -2.500  -0.1893   0.01740   0.00878  -0.0300   1.0000   0.1181
  -2.250  -0.1677   0.01508   0.00805  -0.0295   1.0000   0.3875
  -2.000  -0.1539   0.01410   0.00823  -0.0263   1.0000   0.6685
  -1.750  -0.1162   0.01348   0.00805  -0.0269   1.0000   1.0000
  -1.500  -0.0957   0.01371   0.00794  -0.0265   1.0000   1.0000
  -1.250  -0.0529   0.01419   0.00804  -0.0302   0.9932   1.0000
  -1.000  -0.0047   0.01466   0.00819  -0.0349   0.9835   1.0000
  -0.750   0.0407   0.01506   0.00832  -0.0390   0.9732   1.0000
  -0.500   0.0860   0.01543   0.00848  -0.0429   0.9628   1.0000
  -0.250   0.1331   0.01576   0.00863  -0.0471   0.9529   1.0000
   0.000   0.1797   0.01601   0.00873  -0.0511   0.9425   1.0000
   0.250   0.2216   0.01618   0.00880  -0.0541   0.9306   1.0000
   0.500   0.2642   0.01630   0.00885  -0.0570   0.9188   1.0000
   0.750   0.3084   0.01634   0.00884  -0.0601   0.9072   1.0000
   1.000   0.3559   0.01627   0.00875  -0.0637   0.8965   1.0000
   1.250   0.4038   0.01607   0.00854  -0.0670   0.8864   1.0000
   1.500   0.4432   0.01588   0.00835  -0.0686   0.8739   1.0000
   1.750   0.4783   0.01568   0.00818  -0.0692   0.8603   1.0000
   2.000   0.5095   0.01551   0.00802  -0.0691   0.8453   1.0000
   2.250   0.5374   0.01537   0.00790  -0.0683   0.8285   1.0000
   2.500   0.5660   0.01517   0.00773  -0.0675   0.8119   1.0000
   2.750   0.5947   0.01495   0.00757  -0.0666   0.7951   1.0000
   3.000   0.6224   0.01474   0.00737  -0.0655   0.7773   1.0000
   3.250   0.6474   0.01464   0.00729  -0.0641   0.7560   1.0000
   3.500   0.6735   0.01452   0.00717  -0.0628   0.7346   1.0000
   3.750   0.6994   0.01444   0.00713  -0.0615   0.7115   1.0000
   4.000   0.7240   0.01447   0.00715  -0.0601   0.6855   1.0000
   4.250   0.7486   0.01456   0.00721  -0.0588   0.6582   1.0000
   4.500   0.7730   0.01472   0.00731  -0.0574   0.6294   1.0000
   4.750   0.7963   0.01497   0.00753  -0.0561   0.5979   1.0000
   5.000   0.8194   0.01527   0.00784  -0.0547   0.5652   1.0000
   5.250   0.8421   0.01563   0.00812  -0.0533   0.5317   1.0000
   5.500   0.8639   0.01603   0.00848  -0.0519   0.4956   1.0000
   5.750   0.8853   0.01650   0.00888  -0.0505   0.4585   1.0000
   6.000   0.9060   0.01704   0.00933  -0.0490   0.4208   1.0000
   6.250   0.9260   0.01767   0.00984  -0.0475   0.3823   1.0000
   6.500   0.9452   0.01837   0.01052  -0.0459   0.3427   1.0000
   6.750   0.9636   0.01916   0.01121  -0.0444   0.3025   1.0000
   7.000   0.9810   0.02006   0.01200  -0.0428   0.2625   1.0000
   7.250   0.9973   0.02108   0.01290  -0.0411   0.2226   1.0000
   7.500   1.0125   0.02221   0.01390  -0.0393   0.1834   1.0000
   7.750   1.0264   0.02357   0.01512  -0.0374   0.1458   1.0000
   8.000   1.0395   0.02534   0.01668  -0.0354   0.1152   1.0000
   8.250   1.0536   0.02729   0.01855  -0.0334   0.0907   1.0000
   8.500   1.0689   0.02955   0.02076  -0.0317   0.0731   1.0000
   8.750   1.0832   0.03156   0.02288  -0.0299   0.0583   1.0000
   9.000   1.0992   0.03433   0.02581  -0.0283   0.0478   1.0000
   9.250   1.1146   0.03720   0.02870  -0.0270   0.0401   1.0000
   9.500   1.1300   0.04095   0.03295  -0.0251   0.0372   1.0000
   9.750   1.1392   0.04391   0.03636  -0.0228   0.0342   1.0000
  10.000   1.1463   0.04615   0.03876  -0.0210   0.0309   1.0000
  10.250   1.1497   0.05044   0.04325  -0.0194   0.0292   1.0000
  10.500   1.1453   0.05501   0.04821  -0.0170   0.0289   1.0000
  10.750   1.1357   0.05896   0.05251  -0.0143   0.0288   1.0000
  11.000   1.1231   0.06228   0.05612  -0.0115   0.0289   1.0000
  11.250   1.1090   0.06555   0.05964  -0.0094   0.0290   1.0000
  11.500   1.0932   0.06909   0.06344  -0.0082   0.0291   1.0000
  11.750   1.0757   0.07301   0.06761  -0.0081   0.0293   1.0000
  12.000   1.0561   0.07765   0.07248  -0.0093   0.0296   1.0000
  12.250   1.0321   0.08349   0.07860  -0.0123   0.0302   1.0000
  12.500   0.9739   0.09754   0.09306  -0.0232   0.0343   1.0000
  12.750   0.9484   0.10803   0.10362  -0.0302   0.0367   1.0000
<< Back to MH 32 8.7% (mh32-il)

Polar data table (+)

Polar graphs


<< Back to MH 32 8.7% (mh32-il)