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MH 78 14.47% (mh78-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MH 78 14.47% (mh78-il)
Reynolds number: 200,000
Max Cl/Cd: 42.34 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh78-il-200000.txt
Download as CSV file: xf-mh78-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 78  14.47%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5655   0.08711   0.08429   0.0110   1.0000   0.0641
  -9.000  -0.5534   0.08510   0.08234   0.0120   1.0000   0.0648
  -8.750  -0.5540   0.08068   0.07797   0.0091   1.0000   0.0657
  -8.500  -0.5705   0.07457   0.07186   0.0042   1.0000   0.0666
  -8.250  -0.5901   0.06967   0.06692   0.0024   1.0000   0.0677
  -8.000  -0.6547   0.06181   0.05833   0.0013   0.8968   0.0718
  -7.750  -0.6417   0.05959   0.05604   0.0037   0.8219   0.0725
  -7.500  -0.6961   0.04042   0.03485   0.0098   0.8220   0.0393
  -7.250  -0.6888   0.03540   0.02917   0.0130   0.7898   0.0347
  -7.000  -0.6726   0.03319   0.02655   0.0152   0.7598   0.0338
  -6.750  -0.6540   0.03105   0.02408   0.0169   0.7330   0.0334
  -6.500  -0.6337   0.02908   0.02173   0.0185   0.7095   0.0332
  -6.250  -0.6118   0.02731   0.01959   0.0200   0.6876   0.0331
  -6.000  -0.5882   0.02579   0.01772   0.0212   0.6670   0.0333
  -5.750  -0.5633   0.02448   0.01610   0.0223   0.6472   0.0336
  -5.500  -0.5380   0.02337   0.01470   0.0232   0.6281   0.0345
  -5.250  -0.5120   0.02238   0.01371   0.0237   0.6096   0.0359
  -5.000  -0.4857   0.02158   0.01280   0.0244   0.5920   0.0376
  -4.750  -0.4590   0.02075   0.01176   0.0252   0.5755   0.0388
  -4.500  -0.4332   0.01971   0.01073   0.0260   0.5604   0.0401
  -4.000  -0.3826   0.01825   0.00914   0.0277   0.5309   0.0447
  -3.750  -0.3580   0.01760   0.00849   0.0286   0.5172   0.0487
  -3.500  -0.3336   0.01705   0.00788   0.0295   0.5051   0.0551
  -3.250  -0.3094   0.01633   0.00724   0.0304   0.4920   0.0665
  -3.000  -0.2870   0.01543   0.00653   0.0317   0.4808   0.1036
  -2.750  -0.2672   0.01426   0.00608   0.0329   0.4694   0.2377
  -2.500  -0.2456   0.01362   0.00584   0.0341   0.4585   0.3384
  -2.250  -0.2262   0.01290   0.00562   0.0357   0.4485   0.4593
  -2.000  -0.2095   0.01208   0.00553   0.0383   0.4392   0.6174
  -1.750  -0.1819   0.01183   0.00593   0.0402   0.4287   0.7874
  -1.500  -0.1491   0.01230   0.00640   0.0409   0.4179   0.8564
  -1.250  -0.1172   0.01289   0.00683   0.0419   0.4081   0.8932
  -1.000  -0.0702   0.01361   0.00741   0.0400   0.3969   0.9155
  -0.750  -0.0225   0.01412   0.00765   0.0372   0.3871   0.9289
  -0.500   0.0249   0.01441   0.00783   0.0342   0.3765   0.9395
  -0.250   0.0747   0.01473   0.00788   0.0306   0.3675   0.9475
   0.000   0.1157   0.01490   0.00799   0.0285   0.3591   0.9579
   0.250   0.1665   0.01506   0.00793   0.0244   0.3512   0.9651
   0.500   0.2140   0.01518   0.00796   0.0209   0.3430   0.9744
   0.750   0.2639   0.01519   0.00783   0.0168   0.3354   0.9842
   1.000   0.3158   0.01523   0.00771   0.0122   0.3289   0.9932
   1.250   0.3647   0.01503   0.00747   0.0080   0.3219   1.0000
   1.500   0.3882   0.01509   0.00743   0.0087   0.3172   1.0000
   1.750   0.4118   0.01534   0.00751   0.0092   0.3128   1.0000
   2.000   0.4360   0.01540   0.00763   0.0098   0.3085   1.0000
   2.250   0.4601   0.01552   0.00773   0.0104   0.3041   1.0000
   2.500   0.4841   0.01564   0.00777   0.0110   0.3000   1.0000
   2.750   0.5081   0.01589   0.00789   0.0116   0.2963   1.0000
   3.000   0.5324   0.01610   0.00813   0.0121   0.2924   1.0000
   3.250   0.5567   0.01627   0.00833   0.0126   0.2883   1.0000
   3.500   0.5810   0.01645   0.00848   0.0132   0.2846   1.0000
   3.750   0.6051   0.01666   0.00861   0.0139   0.2814   1.0000
   4.000   0.6291   0.01711   0.00894   0.0144   0.2780   1.0000
   4.250   0.6532   0.01730   0.00925   0.0150   0.2746   1.0000
   4.500   0.6770   0.01754   0.00953   0.0156   0.2709   1.0000
   4.750   0.7007   0.01780   0.00978   0.0162   0.2676   1.0000
   5.000   0.7242   0.01807   0.01000   0.0169   0.2648   1.0000
   5.250   0.7476   0.01857   0.01039   0.0176   0.2620   1.0000
   5.500   0.7705   0.01897   0.01090   0.0183   0.2590   1.0000
   5.750   0.7932   0.01933   0.01135   0.0190   0.2557   1.0000
   6.000   0.8159   0.01966   0.01171   0.0197   0.2525   1.0000
   6.250   0.8386   0.01998   0.01201   0.0205   0.2499   1.0000
   6.500   0.8613   0.02037   0.01235   0.0214   0.2475   1.0000
   6.750   0.8832   0.02112   0.01305   0.0221   0.2449   1.0000
   7.000   0.9040   0.02158   0.01368   0.0230   0.2423   1.0000
   7.250   0.9246   0.02207   0.01428   0.0239   0.2393   1.0000
   7.500   0.9454   0.02251   0.01478   0.0249   0.2365   1.0000
   7.750   0.9666   0.02290   0.01517   0.0259   0.2341   1.0000
   8.000   0.9881   0.02334   0.01556   0.0268   0.2320   1.0000
   8.250   1.0091   0.02414   0.01629   0.0277   0.2298   1.0000
   8.500   1.0262   0.02490   0.01724   0.0289   0.2276   1.0000
   8.750   1.0429   0.02560   0.01810   0.0302   0.2250   1.0000
   9.000   1.0602   0.02623   0.01884   0.0314   0.2223   1.0000
   9.250   1.0783   0.02678   0.01944   0.0327   0.2201   1.0000
   9.500   1.0978   0.02727   0.01993   0.0338   0.2181   1.0000
   9.750   1.1186   0.02779   0.02041   0.0348   0.2163   1.0000
  10.000   1.1377   0.02888   0.02146   0.0357   0.2143   1.0000
  10.250   1.1471   0.02993   0.02278   0.0374   0.2122   1.0000
  10.500   1.1577   0.03100   0.02404   0.0389   0.2096   1.0000
  10.750   1.1706   0.03195   0.02511   0.0402   0.2074   1.0000
  11.000   1.1856   0.03279   0.02602   0.0413   0.2054   1.0000
  11.250   1.2039   0.03339   0.02663   0.0421   0.2035   1.0000
  11.500   1.2274   0.03379   0.02697   0.0426   0.2018   1.0000
  11.750   1.2470   0.03495   0.02811   0.0431   0.1998   1.0000
  12.000   1.2380   0.03714   0.03064   0.0451   0.1978   1.0000
  12.250   1.2212   0.03984   0.03361   0.0470   0.1957   1.0000
  12.500   1.1709   0.04450   0.03852   0.0486   0.1939   1.0000
  13.000   0.6996   0.12521   0.11982   0.0063   0.1733   1.0000
  13.250   0.6872   0.13265   0.12731   0.0031   0.1732   1.0000
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