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MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 83 13.29% (mh83-il)
Reynolds number: 500,000
Max Cl/Cd: 94.11 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh83-il-500000.txt
Download as CSV file: xf-mh83-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 83  13.29%                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2339   0.08768   0.08453  -0.0143   0.6511   0.0239
  -7.750  -0.2280   0.08470   0.08153  -0.0157   0.6407   0.0243
  -7.500  -0.2238   0.08155   0.07834  -0.0174   0.6308   0.0249
  -7.250  -0.2463   0.07387   0.07074  -0.0244   0.6274   0.0264
  -7.000  -0.2465   0.06888   0.06574  -0.0287   0.6192   0.0266
  -6.750  -0.2348   0.06701   0.06383  -0.0292   0.6084   0.0269
  -6.500  -0.2219   0.06482   0.06160  -0.0307   0.5982   0.0272
  -6.250  -0.2092   0.06157   0.05831  -0.0342   0.5888   0.0276
  -6.000  -0.2048   0.04216   0.03842  -0.0569   0.5890   0.0311
  -5.750  -0.1837   0.04095   0.03718  -0.0570   0.5784   0.0314
  -5.500  -0.1614   0.03959   0.03579  -0.0578   0.5682   0.0319
  -5.250  -0.1436   0.02229   0.01661  -0.0651   0.5662   0.0223
  -5.000  -0.1167   0.02015   0.01415  -0.0654   0.5569   0.0220
  -4.750  -0.0886   0.01861   0.01226  -0.0656   0.5468   0.0221
  -4.500  -0.0603   0.01720   0.01059  -0.0656   0.5370   0.0220
  -4.250  -0.0318   0.01603   0.00917  -0.0655   0.5272   0.0219
  -4.000  -0.0030   0.01510   0.00806  -0.0654   0.5178   0.0220
  -3.750   0.0258   0.01443   0.00720  -0.0653   0.5087   0.0223
  -3.500   0.0549   0.01390   0.00654  -0.0652   0.4994   0.0226
  -3.250   0.0832   0.01310   0.00567  -0.0651   0.4905   0.0232
  -3.000   0.1120   0.01264   0.00519  -0.0651   0.4811   0.0240
  -2.750   0.1410   0.01231   0.00479  -0.0650   0.4724   0.0249
  -2.500   0.1701   0.01200   0.00442  -0.0650   0.4635   0.0259
  -2.250   0.1991   0.01168   0.00403  -0.0650   0.4555   0.0276
  -2.000   0.2284   0.01145   0.00377  -0.0650   0.4473   0.0298
  -1.750   0.2575   0.01122   0.00347  -0.0650   0.4395   0.0325
  -1.500   0.2869   0.01098   0.00322  -0.0650   0.4316   0.0379
  -1.250   0.3159   0.01060   0.00298  -0.0651   0.4238   0.0851
  -1.000   0.3450   0.01036   0.00291  -0.0652   0.4164   0.1369
  -0.750   0.3739   0.01022   0.00287  -0.0653   0.4091   0.1855
  -0.500   0.4028   0.01011   0.00287  -0.0653   0.4026   0.2361
  -0.250   0.4317   0.00998   0.00288  -0.0654   0.3958   0.2957
   0.000   0.4601   0.00985   0.00293  -0.0655   0.3895   0.3786
   0.250   0.4887   0.00962   0.00298  -0.0655   0.3834   0.4726
   0.500   0.5167   0.00945   0.00304  -0.0655   0.3772   0.5750
   0.750   0.5434   0.00923   0.00314  -0.0650   0.3716   0.6990
   1.000   0.5637   0.00872   0.00318  -0.0628   0.3666   0.8942
   1.250   0.5991   0.00878   0.00318  -0.0641   0.3610   1.0000
   1.500   0.6279   0.00897   0.00325  -0.0641   0.3560   1.0000
   1.750   0.6570   0.00907   0.00330  -0.0641   0.3515   1.0000
   2.000   0.6858   0.00922   0.00336  -0.0641   0.3466   1.0000
   2.250   0.7142   0.00944   0.00346  -0.0641   0.3417   1.0000
   2.500   0.7430   0.00957   0.00356  -0.0641   0.3377   1.0000
   2.750   0.7718   0.00971   0.00365  -0.0641   0.3338   1.0000
   3.000   0.8002   0.00988   0.00376  -0.0641   0.3298   1.0000
   3.250   0.8283   0.01013   0.00391  -0.0641   0.3258   1.0000
   3.500   0.8568   0.01029   0.00405  -0.0641   0.3225   1.0000
   3.750   0.8853   0.01043   0.00418  -0.0641   0.3190   1.0000
   4.000   0.9136   0.01060   0.00431  -0.0641   0.3154   1.0000
   4.250   0.9415   0.01083   0.00447  -0.0641   0.3120   1.0000
   4.500   0.9690   0.01113   0.00470  -0.0641   0.3086   1.0000
   4.750   0.9973   0.01127   0.00487  -0.0641   0.3061   1.0000
   5.000   1.0254   0.01144   0.00503  -0.0641   0.3030   1.0000
   5.250   1.0533   0.01163   0.00520  -0.0641   0.2999   1.0000
   5.500   1.0808   0.01186   0.00540  -0.0640   0.2969   1.0000
   5.750   1.1077   0.01222   0.00569  -0.0639   0.2937   1.0000
   6.000   1.1353   0.01241   0.00591  -0.0639   0.2915   1.0000
   6.250   1.1629   0.01259   0.00613  -0.0639   0.2890   1.0000
   6.500   1.1903   0.01279   0.00633  -0.0639   0.2862   1.0000
   6.750   1.2174   0.01302   0.00655  -0.0638   0.2835   1.0000
   7.000   1.2441   0.01331   0.00682  -0.0637   0.2809   1.0000
   7.250   1.2701   0.01375   0.00720  -0.0636   0.2778   1.0000
   7.500   1.2972   0.01393   0.00745  -0.0635   0.2759   1.0000
   7.750   1.3240   0.01414   0.00771  -0.0635   0.2735   1.0000
   8.000   1.3505   0.01437   0.00798  -0.0634   0.2709   1.0000
   8.250   1.3768   0.01463   0.00825  -0.0633   0.2685   1.0000
   8.500   1.4026   0.01495   0.00856  -0.0632   0.2662   1.0000
   8.750   1.4277   0.01541   0.00898  -0.0630   0.2633   1.0000
   9.000   1.4533   0.01569   0.00933  -0.0628   0.2611   1.0000
   9.250   1.4789   0.01594   0.00965  -0.0627   0.2588   1.0000
   9.500   1.5042   0.01622   0.00999  -0.0625   0.2565   1.0000
   9.750   1.5291   0.01651   0.01032  -0.0622   0.2541   1.0000
  10.000   1.5535   0.01685   0.01067  -0.0620   0.2515   1.0000
  10.250   1.5770   0.01734   0.01114  -0.0617   0.2487   1.0000
  10.500   1.6008   0.01773   0.01160  -0.0614   0.2465   1.0000
  10.750   1.6244   0.01803   0.01199  -0.0610   0.2442   1.0000
  11.000   1.6475   0.01835   0.01239  -0.0607   0.2416   1.0000
  11.250   1.6701   0.01870   0.01279  -0.0602   0.2391   1.0000
  11.500   1.6917   0.01912   0.01322  -0.0597   0.2365   1.0000
  11.750   1.7122   0.01976   0.01383  -0.0591   0.2333   1.0000
  12.000   1.7326   0.02011   0.01432  -0.0585   0.2312   1.0000
  12.250   1.7520   0.02052   0.01483  -0.0577   0.2286   1.0000
  12.500   1.7702   0.02096   0.01535  -0.0568   0.2258   1.0000
  12.750   1.7858   0.02147   0.01590  -0.0556   0.2232   1.0000
  13.000   1.7970   0.02215   0.01659  -0.0539   0.2205   1.0000
  13.250   1.8074   0.02291   0.01742  -0.0523   0.2180   1.0000
  13.500   1.8174   0.02366   0.01830  -0.0509   0.2156   1.0000
  13.750   1.8273   0.02454   0.01928  -0.0497   0.2129   1.0000
  14.000   1.8360   0.02558   0.02038  -0.0487   0.2098   1.0000
  14.250   1.8423   0.02690   0.02171  -0.0477   0.2064   1.0000
  14.500   1.8495   0.02826   0.02318  -0.0470   0.2034   1.0000
  14.750   1.8569   0.02971   0.02475  -0.0465   0.2000   1.0000
  15.000   1.8613   0.03147   0.02657  -0.0461   0.1961   1.0000
  15.250   1.8622   0.03363   0.02873  -0.0457   0.1924   1.0000
  15.500   1.8666   0.03562   0.03086  -0.0456   0.1892   1.0000
  15.750   1.8680   0.03796   0.03331  -0.0457   0.1848   1.0000
  16.000   1.8643   0.04087   0.03625  -0.0459   0.1809   1.0000
  16.250   1.8606   0.04389   0.03935  -0.0462   0.1770   1.0000
  16.500   1.8582   0.04693   0.04251  -0.0467   0.1729   1.0000
  16.750   1.8499   0.05064   0.04628  -0.0474   0.1690   1.0000
  17.000   1.8392   0.05480   0.05049  -0.0483   0.1653   1.0000
  17.250   1.8328   0.05866   0.05448  -0.0493   0.1613   1.0000
  17.500   1.8208   0.06332   0.05922  -0.0507   0.1572   1.0000
  17.750   1.8052   0.06858   0.06451  -0.0523   0.1531   1.0000
  18.000   1.7940   0.07345   0.06952  -0.0540   0.1488   1.0000
  18.250   1.7777   0.07910   0.07523  -0.0560   0.1447   1.0000
  18.500   1.7594   0.08521   0.08139  -0.0584   0.1406   1.0000
  18.750   1.7453   0.09085   0.08715  -0.0606   0.1363   1.0000
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