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MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MH 25 9.98% (mh25-il)
Reynolds number: 100,000
Max Cl/Cd: 51.87 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh25-il-100000.txt
Download as CSV file: xf-mh25-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 25  9.98%                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4942   0.09455   0.08992  -0.0325   1.0000   0.0889
  -8.500  -0.5098   0.09132   0.08677  -0.0331   1.0000   0.0913
  -8.250  -0.5305   0.08834   0.08385  -0.0336   1.0000   0.0922
  -8.000  -0.5580   0.08611   0.08167  -0.0315   1.0000   0.0929
  -7.750  -0.5866   0.08375   0.07926  -0.0299   1.0000   0.0939
  -7.500  -0.6201   0.08227   0.07756  -0.0272   1.0000   0.0947
  -7.250  -0.6001   0.07650   0.07204  -0.0257   1.0000   0.0974
  -7.000  -0.5989   0.07365   0.06921  -0.0231   1.0000   0.1007
  -6.750  -0.6075   0.07084   0.06631  -0.0211   1.0000   0.1050
  -6.250  -0.6152   0.06435   0.05969  -0.0166   1.0000   0.1137
  -4.750  -0.5760   0.03954   0.03244  -0.0009   1.0000   0.0576
  -4.500  -0.5546   0.03688   0.02894   0.0028   1.0000   0.0428
  -4.250  -0.5377   0.03290   0.02478   0.0044   1.0000   0.0400
  -4.000  -0.5182   0.03025   0.02173   0.0064   1.0000   0.0378
  -3.750  -0.4968   0.02813   0.01919   0.0083   1.0000   0.0378
  -3.500  -0.4745   0.02644   0.01710   0.0099   1.0000   0.0388
  -3.250  -0.4520   0.02551   0.01580   0.0116   1.0000   0.0424
  -3.000  -0.4284   0.02328   0.01350   0.0129   1.0000   0.0446
  -2.750  -0.1534   0.01915   0.01276  -0.0273   1.0000   1.0000
  -2.500  -0.1446   0.01897   0.01237  -0.0246   1.0000   1.0000
  -2.250  -0.1350   0.01883   0.01204  -0.0219   1.0000   1.0000
  -2.000  -0.1250   0.01874   0.01178  -0.0193   1.0000   1.0000
  -1.750  -0.1147   0.01869   0.01157  -0.0167   1.0000   1.0000
  -1.500  -0.1041   0.01867   0.01141  -0.0142   1.0000   1.0000
  -1.250  -0.0933   0.01868   0.01129  -0.0116   1.0000   1.0000
  -1.000  -0.0824   0.01872   0.01122  -0.0091   1.0000   1.0000
  -0.750  -0.0715   0.01879   0.01116  -0.0067   1.0000   1.0000
  -0.500  -0.0607   0.01889   0.01117  -0.0042   1.0000   1.0000
  -0.250  -0.0497   0.01902   0.01121  -0.0018   1.0000   1.0000
   0.000  -0.0389   0.01918   0.01130   0.0006   1.0000   1.0000
   0.250  -0.0281   0.01938   0.01143   0.0029   1.0000   1.0000
   0.500  -0.0172   0.01961   0.01160   0.0051   1.0000   1.0000
   0.750  -0.0051   0.01988   0.01181   0.0070   0.9997   1.0000
   1.000   0.0498   0.02062   0.01250   0.0005   0.9885   1.0000
   1.250   0.1006   0.02127   0.01313  -0.0051   0.9769   1.0000
   1.500   0.1494   0.02179   0.01365  -0.0102   0.9646   1.0000
   1.750   0.1969   0.02220   0.01408  -0.0148   0.9520   1.0000
   2.000   0.2442   0.02249   0.01441  -0.0191   0.9391   1.0000
   2.250   0.2911   0.02264   0.01465  -0.0232   0.9260   1.0000
   2.500   0.3378   0.02264   0.01474  -0.0271   0.9125   1.0000
   2.750   0.3840   0.02250   0.01471  -0.0306   0.8988   1.0000
   3.000   0.4299   0.02218   0.01452  -0.0338   0.8842   1.0000
   3.250   0.4766   0.02168   0.01423  -0.0369   0.8693   1.0000
   3.500   0.5260   0.02093   0.01369  -0.0402   0.8542   1.0000
   3.750   0.5793   0.01990   0.01293  -0.0438   0.8390   1.0000
   4.000   0.6275   0.01869   0.01196  -0.0461   0.8208   1.0000
   4.250   0.6744   0.01737   0.01089  -0.0478   0.7971   1.0000
   4.500   0.7163   0.01630   0.01000  -0.0487   0.7590   1.0000
   4.750   0.7668   0.01543   0.00921  -0.0512   0.6938   1.0000
   5.000   0.7998   0.01542   0.00892  -0.0508   0.6076   1.0000
   5.250   0.8154   0.01597   0.00910  -0.0477   0.5253   1.0000
   5.500   0.8244   0.01672   0.00948  -0.0438   0.4477   1.0000
   5.750   0.8308   0.01758   0.00997  -0.0396   0.3765   1.0000
   6.000   0.8357   0.01853   0.01056  -0.0353   0.3094   1.0000
   6.250   0.8401   0.01959   0.01125  -0.0310   0.2481   1.0000
   6.500   0.8443   0.02079   0.01210  -0.0269   0.1945   1.0000
   6.750   0.8495   0.02209   0.01310  -0.0228   0.1504   1.0000
   7.000   0.8558   0.02344   0.01421  -0.0191   0.1187   1.0000
   7.250   0.8683   0.02509   0.01578  -0.0161   0.0973   1.0000
   7.500   0.8817   0.02652   0.01724  -0.0136   0.0816   1.0000
   7.750   0.9020   0.02839   0.01918  -0.0122   0.0706   1.0000
   8.000   0.9309   0.03128   0.02215  -0.0122   0.0633   1.0000
   8.250   0.9476   0.03312   0.02427  -0.0100   0.0570   1.0000
   8.500   0.9631   0.03605   0.02739  -0.0080   0.0515   1.0000
   8.750   0.9722   0.03884   0.03073  -0.0043   0.0489   1.0000
   9.000   0.9794   0.04056   0.03256  -0.0012   0.0437   1.0000
   9.250   0.9786   0.04435   0.03662   0.0026   0.0406   1.0000
   9.500   0.9754   0.04723   0.03993   0.0074   0.0402   1.0000
   9.750   0.9689   0.05039   0.04348   0.0122   0.0401   1.0000
  10.000   0.9588   0.05366   0.04709   0.0170   0.0401   1.0000
  10.250   0.9439   0.05694   0.05068   0.0220   0.0401   1.0000
  10.500   0.9313   0.06032   0.05424   0.0261   0.0406   1.0000
  10.750   0.9143   0.06385   0.05794   0.0302   0.0409   1.0000
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