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NACA M8 AIRFOIL (m8-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA M8 AIRFOIL (m8-il)
Reynolds number: 100,000
Max Cl/Cd: 46.31 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m8-il-100000-n5.txt
Download as CSV file: xf-m8-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M8 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1751   0.11238   0.10729  -0.0147   0.7316   0.0565
  -9.000  -0.1727   0.11052   0.10546  -0.0171   0.7232   0.0567
  -8.750  -0.1702   0.10849   0.10340  -0.0189   0.7156   0.0569
  -8.500  -0.1515   0.10344   0.09832  -0.0179   0.7069   0.0575
  -8.250  -0.1390   0.10034   0.09517  -0.0177   0.6979   0.0586
  -8.000  -0.1288   0.09786   0.09266  -0.0181   0.6889   0.0603
  -7.750  -0.1212   0.09566   0.09044  -0.0190   0.6802   0.0632
  -7.500  -0.1260   0.09492   0.08972  -0.0220   0.6730   0.0657
  -7.250  -0.1253   0.09349   0.08830  -0.0254   0.6655   0.0661
  -7.000  -0.1167   0.09100   0.08575  -0.0286   0.6594   0.0662
  -6.750  -0.1031   0.08701   0.08179  -0.0288   0.6517   0.0666
  -6.500  -0.0880   0.08341   0.07815  -0.0272   0.6450   0.0675
  -6.250  -0.0739   0.08080   0.07551  -0.0271   0.6390   0.0690
  -6.000  -0.0596   0.07863   0.07334  -0.0285   0.6319   0.0731
  -5.750  -0.0428   0.07694   0.07154  -0.0373   0.6265   0.0768
  -5.500  -0.0299   0.07179   0.06633  -0.0373   0.6218   0.0653
  -5.250  -0.0145   0.06802   0.06255  -0.0386   0.6154   0.0592
  -5.000   0.0056   0.06448   0.05891  -0.0427   0.6099   0.0584
  -4.500   0.0555   0.05608   0.05020  -0.0527   0.5994   0.0567
  -4.250   0.0806   0.05257   0.04655  -0.0558   0.5935   0.0567
  -4.000   0.1008   0.05159   0.04552  -0.0552   0.5881   0.0585
  -3.750   0.1258   0.04962   0.04349  -0.0568   0.5813   0.0602
  -3.500   0.1539   0.04644   0.04014  -0.0597   0.5751   0.0606
  -3.250   0.1828   0.04302   0.03646  -0.0625   0.5701   0.0607
  -3.000   0.2128   0.03968   0.03291  -0.0653   0.5638   0.0620
  -2.750   0.2475   0.03288   0.02552  -0.0703   0.5584   0.0649
  -2.500   0.2794   0.02610   0.01769  -0.0737   0.5537   0.0671
  -2.250   0.3059   0.02545   0.01691  -0.0733   0.5480   0.0693
  -2.000   0.3337   0.02435   0.01557  -0.0734   0.5411   0.0730
  -1.750   0.3619   0.02313   0.01392  -0.0734   0.5353   0.0764
  -1.500   0.3888   0.02258   0.01322  -0.0729   0.5300   0.0792
  -1.250   0.4161   0.02227   0.01290  -0.0726   0.5228   0.0834
  -1.000   0.4441   0.02174   0.01212  -0.0723   0.5168   0.0897
  -0.750   0.4709   0.02163   0.01197  -0.0718   0.5118   0.0959
  -0.500   0.4984   0.02149   0.01185  -0.0715   0.5046   0.1044
  -0.250   0.5253   0.02169   0.01212  -0.0710   0.4981   0.1144
   0.000   0.5513   0.02248   0.01305  -0.0701   0.4927   0.1226
   0.250   0.5774   0.02319   0.01391  -0.0695   0.4842   0.1311
   0.500   0.6044   0.02346   0.01410  -0.0689   0.4774   0.1466
   0.750   0.6341   0.02358   0.01384  -0.0686   0.4706   0.1784
   1.000   0.6604   0.02381   0.01401  -0.0682   0.4630   0.1909
   1.250   0.6872   0.02389   0.01384  -0.0676   0.4572   0.2047
   1.500   0.7133   0.02397   0.01388  -0.0673   0.4495   0.2149
   1.750   0.7389   0.02384   0.01372  -0.0669   0.4426   0.2234
   2.000   0.7647   0.02374   0.01356  -0.0664   0.4361   0.2323
   2.250   0.7911   0.02384   0.01355  -0.0661   0.4286   0.2404
   2.500   0.8166   0.02366   0.01335  -0.0656   0.4230   0.2479
   2.750   0.8427   0.02379   0.01341  -0.0653   0.4170   0.2557
   3.000   0.8683   0.02372   0.01336  -0.0650   0.4109   0.2598
   3.250   0.8947   0.02370   0.01322  -0.0646   0.4056   0.2604
   3.500   0.9207   0.02381   0.01330  -0.0643   0.3994   0.2595
   3.750   0.9467   0.02390   0.01335  -0.0640   0.3930   0.2586
   4.000   0.9728   0.02395   0.01327  -0.0636   0.3879   0.2577
   4.250   0.9981   0.02415   0.01348  -0.0633   0.3816   0.2574
   4.500   1.0233   0.02431   0.01364  -0.0629   0.3757   0.2573
   4.750   1.0486   0.02443   0.01366  -0.0624   0.3707   0.2571
   5.000   1.0727   0.02470   0.01396  -0.0620   0.3644   0.2566
   5.250   1.0971   0.02497   0.01422  -0.0615   0.3579   0.2557
   5.500   1.1225   0.02518   0.01431  -0.0611   0.3522   0.2550
   5.750   1.1465   0.02556   0.01475  -0.0608   0.3452   0.2544
   6.000   1.1710   0.02585   0.01506  -0.0606   0.3385   0.2541
   6.250   1.1961   0.02611   0.01520  -0.0602   0.3328   0.2537
   6.500   1.2185   0.02657   0.01580  -0.0598   0.3257   0.2533
   6.750   1.2411   0.02695   0.01619  -0.0593   0.3193   0.2530
   7.000   1.2642   0.02730   0.01647  -0.0587   0.3138   0.2527
   7.250   1.2837   0.02787   0.01720  -0.0580   0.3068   0.2525
   7.500   1.3037   0.02835   0.01770  -0.0572   0.3007   0.2523
   7.750   1.3240   0.02880   0.01811  -0.0564   0.2955   0.2522
   8.000   1.3402   0.02951   0.01897  -0.0553   0.2888   0.2523
   8.250   1.3568   0.03011   0.01960  -0.0542   0.2832   0.2526
   8.500   1.3740   0.03066   0.02012  -0.0531   0.2786   0.2531
   8.750   1.3867   0.03153   0.02115  -0.0517   0.2731   0.2536
   9.000   1.3994   0.03231   0.02199  -0.0503   0.2684   0.2541
   9.250   1.4116   0.03301   0.02268  -0.0488   0.2650   0.2545
   9.500   1.4218   0.03391   0.02362  -0.0471   0.2616   0.2546
   9.750   1.4289   0.03510   0.02493  -0.0456   0.2579   0.2549
  10.000   1.4373   0.03627   0.02619  -0.0444   0.2545   0.2550
  10.250   1.4473   0.03739   0.02735  -0.0433   0.2517   0.2552
  10.500   1.4600   0.03834   0.02829  -0.0423   0.2492   0.2554
  10.750   1.4701   0.03961   0.02962  -0.0414   0.2468   0.2556
  11.000   1.4740   0.04143   0.03158  -0.0406   0.2441   0.2558
  11.250   1.4787   0.04325   0.03351  -0.0399   0.2414   0.2561
  11.500   1.4848   0.04496   0.03532  -0.0392   0.2389   0.2565
  11.750   1.4935   0.04645   0.03685  -0.0386   0.2366   0.2569
  12.000   1.5064   0.04760   0.03802  -0.0380   0.2345   0.2575
  12.250   1.5237   0.04840   0.03881  -0.0373   0.2327   0.2582
  12.500   1.5147   0.05178   0.04241  -0.0371   0.2305   0.2586
  12.750   1.5049   0.05543   0.04627  -0.0371   0.2284   0.2587
  13.000   1.4932   0.05946   0.05048  -0.0374   0.2262   0.2590
  13.250   1.4810   0.06372   0.05489  -0.0379   0.2241   0.2591
  13.500   1.4732   0.06761   0.05891  -0.0384   0.2221   0.2596
  13.750   1.4743   0.07046   0.06185  -0.0386   0.2204   0.2602
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