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

MH 104 15.28% (mh104-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MH 104 15.28% (mh104-il)
Reynolds number: 50,000
Max Cl/Cd: 21.25 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh104-il-50000-n5.txt
Download as CSV file: xf-mh104-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 104  15.28%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5731   0.10065   0.09391  -0.0176   1.0000   0.0412
 -12.000  -0.5964   0.09110   0.08431  -0.0237   1.0000   0.0405
 -11.750  -0.6208   0.08233   0.07542  -0.0297   1.0000   0.0397
 -11.500  -0.6472   0.07433   0.06724  -0.0353   1.0000   0.0389
 -11.250  -0.6691   0.06813   0.06088  -0.0392   1.0000   0.0386
 -11.000  -0.6862   0.06328   0.05583  -0.0414   1.0000   0.0387
 -10.750  -0.6995   0.05922   0.05155  -0.0421   1.0000   0.0389
 -10.500  -0.7079   0.05588   0.04798  -0.0419   1.0000   0.0392
 -10.250  -0.7136   0.05277   0.04463  -0.0408   1.0000   0.0398
 -10.000  -0.7146   0.05001   0.04164  -0.0393   1.0000   0.0404
  -9.750  -0.7117   0.04737   0.03873  -0.0376   1.0000   0.0415
  -9.500  -0.7046   0.04498   0.03599  -0.0361   1.0000   0.0430
  -9.250  -0.6938   0.04292   0.03398  -0.0350   1.0000   0.0453
  -9.000  -0.6824   0.04108   0.03205  -0.0338   1.0000   0.0480
  -8.750  -0.6685   0.03915   0.02991  -0.0324   1.0000   0.0514
  -8.500  -0.6559   0.03732   0.02807  -0.0309   1.0000   0.0547
  -8.250  -0.6450   0.03573   0.02644  -0.0293   1.0000   0.0597
  -8.000  -0.6341   0.03412   0.02478  -0.0275   1.0000   0.0654
  -7.750  -0.6250   0.03265   0.02333  -0.0255   1.0000   0.0727
  -7.500  -0.6189   0.03120   0.02199  -0.0232   1.0000   0.0819
  -7.250  -0.6171   0.02994   0.02086  -0.0201   1.0000   0.0938
  -7.000  -0.5995   0.02811   0.01931  -0.0204   0.9765   0.1232
  -6.750  -0.5703   0.02637   0.01804  -0.0226   0.9462   0.1948
  -6.500  -0.5392   0.02570   0.01740  -0.0242   0.9205   0.2623
  -6.250  -0.5117   0.02545   0.01710  -0.0245   0.8968   0.3092
  -6.000  -0.4870   0.02534   0.01691  -0.0239   0.8749   0.3448
  -5.750  -0.4636   0.02516   0.01657  -0.0229   0.8542   0.3727
  -5.500  -0.4395   0.02493   0.01617  -0.0218   0.8355   0.3948
  -5.250  -0.4160   0.02465   0.01567  -0.0206   0.8181   0.4152
  -5.000  -0.3924   0.02437   0.01522  -0.0194   0.8018   0.4340
  -4.750  -0.3683   0.02410   0.01480  -0.0183   0.7863   0.4521
  -4.500  -0.3441   0.02385   0.01441  -0.0173   0.7715   0.4704
  -4.250  -0.3197   0.02360   0.01404  -0.0163   0.7573   0.4895
  -4.000  -0.2954   0.02338   0.01368  -0.0154   0.7438   0.5095
  -3.750  -0.2706   0.02317   0.01336  -0.0145   0.7312   0.5300
  -3.500  -0.2453   0.02298   0.01309  -0.0136   0.7199   0.5511
  -3.250  -0.2206   0.02281   0.01283  -0.0127   0.7082   0.5744
  -3.000  -0.1952   0.02269   0.01269  -0.0119   0.6966   0.5977
  -2.750  -0.1705   0.02259   0.01252  -0.0109   0.6865   0.6238
  -2.500  -0.1444   0.02252   0.01243  -0.0100   0.6767   0.6500
  -2.250  -0.1179   0.02251   0.01242  -0.0093   0.6663   0.6780
  -2.000  -0.0900   0.02251   0.01236  -0.0086   0.6579   0.7076
  -1.750  -0.0607   0.02261   0.01245  -0.0083   0.6480   0.7378
  -1.500  -0.0292   0.02273   0.01252  -0.0084   0.6395   0.7682
  -1.250   0.0046   0.02291   0.01263  -0.0088   0.6308   0.7981
  -1.000   0.0429   0.02317   0.01280  -0.0102   0.6223   0.8249
  -0.750   0.0819   0.02341   0.01292  -0.0117   0.6144   0.8504
  -0.500   0.1209   0.02371   0.01311  -0.0136   0.6062   0.8749
  -0.250   0.1641   0.02396   0.01321  -0.0162   0.5987   0.8958
   0.000   0.2089   0.02425   0.01339  -0.0194   0.5907   0.9153
   0.250   0.2521   0.02446   0.01348  -0.0224   0.5836   0.9349
   0.500   0.2940   0.02468   0.01361  -0.0254   0.5765   0.9544
   0.750   0.3401   0.02484   0.01369  -0.0295   0.5691   0.9714
   1.000   0.3866   0.02490   0.01364  -0.0336   0.5630   0.9877
   1.250   0.4273   0.02511   0.01385  -0.0372   0.5555   1.0000
   1.500   0.4452   0.02527   0.01391  -0.0360   0.5507   1.0000
   1.750   0.4624   0.02569   0.01434  -0.0351   0.5445   1.0000
   2.000   0.4801   0.02607   0.01469  -0.0340   0.5387   1.0000
   2.250   0.4993   0.02630   0.01485  -0.0328   0.5344   1.0000
   2.500   0.5159   0.02695   0.01554  -0.0319   0.5279   1.0000
   2.750   0.5340   0.02739   0.01597  -0.0307   0.5224   1.0000
   3.000   0.5544   0.02764   0.01614  -0.0295   0.5184   1.0000
   3.250   0.5692   0.02853   0.01714  -0.0285   0.5115   1.0000
   3.500   0.5878   0.02901   0.01761  -0.0273   0.5063   1.0000
   3.750   0.6094   0.02924   0.01777  -0.0261   0.5024   1.0000
   4.000   0.6212   0.03041   0.01908  -0.0249   0.4949   1.0000
   4.250   0.6407   0.03086   0.01953  -0.0236   0.4899   1.0000
   4.500   0.6592   0.03144   0.02013  -0.0224   0.4850   1.0000
   4.750   0.6711   0.03257   0.02136  -0.0210   0.4779   1.0000
   5.000   0.6925   0.03290   0.02169  -0.0199   0.4734   1.0000
   5.250   0.7037   0.03409   0.02298  -0.0184   0.4667   1.0000
   5.500   0.7188   0.03493   0.02388  -0.0170   0.4606   1.0000
   5.750   0.7439   0.03500   0.02394  -0.0160   0.4566   1.0000
   6.000   0.7439   0.03699   0.02611  -0.0139   0.4479   1.0000
   6.250   0.7657   0.03730   0.02644  -0.0128   0.4430   1.0000
   6.500   0.7697   0.03895   0.02820  -0.0109   0.4354   1.0000
   6.750   0.7839   0.03981   0.02913  -0.0094   0.4291   1.0000
   7.000   0.8154   0.03944   0.02878  -0.0087   0.4254   1.0000
   7.250   0.7981   0.04255   0.03204  -0.0059   0.4148   1.0000
   7.500   0.8304   0.04208   0.03162  -0.0052   0.4108   1.0000
   7.750   0.8061   0.04568   0.03532  -0.0023   0.3998   1.0000
   8.000   0.8405   0.04500   0.03472  -0.0016   0.3958   1.0000
   8.250   0.8029   0.04955   0.03929   0.0015   0.3840   1.0000
   8.500   0.7953   0.05203   0.04181   0.0031   0.3756   1.0000
   8.750   0.7960   0.05408   0.04393   0.0042   0.3673   1.0000
   9.000   0.8330   0.05276   0.04271   0.0056   0.3639   1.0000
   9.250   0.8011   0.05821   0.04817   0.0058   0.3509   1.0000
   9.750   0.7673   0.06732   0.05733   0.0050   0.3276   1.0000
  10.250   0.7723   0.07217   0.06230   0.0054   0.3106   1.0000
  10.500   0.8008   0.07128   0.06155   0.0070   0.3062   1.0000
  10.750   0.7824   0.07650   0.06678   0.0059   0.2945   1.0000
  11.000   0.7996   0.07709   0.06749   0.0067   0.2888   1.0000
  11.250   0.7944   0.08067   0.07112   0.0062   0.2788   1.0000
  11.750   0.8052   0.08514   0.07575   0.0063   0.2636   1.0000
  12.250   0.8166   0.08955   0.08034   0.0062   0.2485   1.0000
  12.750   0.8265   0.09428   0.08525   0.0060   0.2337   1.0000
  13.000   0.8027   0.10152   0.09250   0.0033   0.2228   1.0000
  13.250   0.8332   0.09963   0.09077   0.0052   0.2191   1.0000
  13.500   0.8061   0.10779   0.09892   0.0020   0.2081   1.0000
  13.750   0.8347   0.10607   0.09735   0.0038   0.2042   1.0000
<< Back to MH 104 15.28% (mh104-il)

Polar data table (+)

Polar graphs


<< Back to MH 104 15.28% (mh104-il)