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MILEY M06-13-128 (miley-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MILEY M06-13-128 (miley-il)
Reynolds number: 200,000
Max Cl/Cd: 61.24 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-miley-il-200000.txt
Download as CSV file: xf-miley-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MILEY M06-13-128                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2988   0.12341   0.11921  -0.0068   0.6256   0.0246
  -9.750  -0.2951   0.12084   0.11665  -0.0095   0.6254   0.0249
  -9.500  -0.2919   0.11824   0.11411  -0.0125   0.6252   0.0252
  -9.250  -0.2873   0.11539   0.11129  -0.0150   0.6250   0.0253
  -9.000  -0.2831   0.11244   0.10839  -0.0176   0.6248   0.0255
  -8.750  -0.2775   0.10945   0.10543  -0.0199   0.6246   0.0255
  -8.500  -0.2723   0.10635   0.10238  -0.0222   0.6243   0.0256
  -8.250  -0.2677   0.10316   0.09924  -0.0248   0.6239   0.0256
  -8.000  -0.2596   0.09702   0.09312  -0.0230   0.6233   0.0267
  -7.750  -0.2510   0.09401   0.09014  -0.0236   0.6226   0.0273
  -7.500  -0.2440   0.09114   0.08730  -0.0248   0.6223   0.0279
  -7.250  -0.2390   0.08816   0.08438  -0.0265   0.6221   0.0288
  -7.000  -0.2364   0.08537   0.08164  -0.0284   0.6219   0.0293
  -6.750  -0.2368   0.08268   0.07899  -0.0306   0.6217   0.0298
  -6.500  -0.2312   0.07953   0.07587  -0.0339   0.6215   0.0305
  -6.250  -0.2235   0.07619   0.07253  -0.0374   0.6212   0.0314
  -6.000  -0.2136   0.07268   0.06898  -0.0411   0.6205   0.0326
  -5.750  -0.2001   0.06910   0.06532  -0.0450   0.6198   0.0340
  -5.500  -0.1790   0.06634   0.06223  -0.0496   0.6192   0.0357
  -5.250  -0.1619   0.06396   0.05961  -0.0511   0.6189   0.0360
  -5.000  -0.1546   0.05766   0.05339  -0.0524   0.6186   0.0373
  -4.750  -0.1391   0.05524   0.05099  -0.0528   0.6183   0.0389
  -4.500  -0.1210   0.05300   0.04865  -0.0533   0.6176   0.0411
  -4.250  -0.1006   0.05061   0.04604  -0.0537   0.6167   0.0448
  -4.000  -0.0793   0.04799   0.04281  -0.0535   0.6158   0.0496
  -3.750  -0.0616   0.04548   0.04038  -0.0536   0.6152   0.0519
  -3.500  -0.0386   0.04397   0.03878  -0.0543   0.6147   0.0571
  -3.250  -0.0155   0.04203   0.03654  -0.0549   0.6140   0.0651
  -3.000   0.0091   0.04158   0.03575  -0.0555   0.6126   0.0774
  -2.750   0.0309   0.03959   0.03391  -0.0565   0.6120   0.0830
  -2.500   0.0537   0.03879   0.03300  -0.0572   0.6111   0.0992
  -2.250   0.0743   0.03807   0.03226  -0.0578   0.6094   0.1259
  -1.750   0.1395   0.03336   0.02612  -0.0549   0.6076   0.0406
  -1.500   0.1666   0.03313   0.02556  -0.0539   0.6056   0.0363
  -1.250   0.1921   0.03195   0.02419  -0.0523   0.6035   0.0358
  -1.000   0.2167   0.03076   0.02285  -0.0499   0.6017   0.0362
  -0.750   0.2372   0.03118   0.02344  -0.0517   0.5992   0.0414
  -0.500   0.2567   0.03217   0.02449  -0.0531   0.5964   0.0450
  -0.250   0.2758   0.03278   0.02509  -0.0533   0.5942   0.0494
   0.000   0.2995   0.03231   0.02456  -0.0517   0.5908   0.0654
   0.250   0.4080   0.02806   0.02276  -0.0637   0.5883   1.0000
   0.500   0.4242   0.03028   0.02499  -0.0662   0.5820   1.0000
   0.750   0.4448   0.03088   0.02547  -0.0655   0.5782   1.0000
   1.000   0.4686   0.03080   0.02522  -0.0637   0.5758   1.0000
   1.250   0.4932   0.03060   0.02485  -0.0616   0.5743   1.0000
   1.500   0.5179   0.03047   0.02455  -0.0594   0.5733   1.0000
   1.750   0.5289   0.03284   0.02702  -0.0620   0.5625   1.0000
   2.000   0.5550   0.03257   0.02662  -0.0602   0.5609   1.0000
   2.250   0.5813   0.03230   0.02623  -0.0583   0.5598   1.0000
   2.500   0.5909   0.03438   0.02836  -0.0596   0.5487   1.0000
   2.750   0.6182   0.03404   0.02793  -0.0580   0.5473   1.0000
   3.000   0.6455   0.03372   0.02752  -0.0565   0.5462   1.0000
   3.250   0.6732   0.03337   0.02708  -0.0549   0.5454   1.0000
   3.500   0.6820   0.03532   0.02911  -0.0559   0.5336   1.0000
   3.750   0.7044   0.03560   0.02935  -0.0550   0.5299   1.0000
   4.000   0.7402   0.03422   0.02787  -0.0530   0.5319   1.0000
   4.250   0.7483   0.03610   0.02983  -0.0537   0.5200   1.0000
   4.500   0.7781   0.03547   0.02917  -0.0524   0.5191   1.0000
   4.750   0.8082   0.03478   0.02843  -0.0512   0.5184   1.0000
   5.000   0.8141   0.03687   0.03061  -0.0518   0.5066   1.0000
   5.250   0.8304   0.03776   0.03153  -0.0515   0.5005   1.0000
   5.500   0.8741   0.03556   0.02931  -0.0497   0.5050   1.0000
   5.750   0.9044   0.03487   0.02860  -0.0487   0.5044   1.0000
   6.000   0.8930   0.03868   0.03254  -0.0499   0.4866   1.0000
   6.250   0.9332   0.03691   0.03078  -0.0485   0.4891   1.0000
   6.500   0.9691   0.03554   0.02945  -0.0474   0.4901   1.0000
   6.750   1.0042   0.03424   0.02816  -0.0464   0.4909   1.0000
   7.000   0.9813   0.03901   0.03306  -0.0478   0.4692   1.0000
   7.250   1.0140   0.03798   0.03209  -0.0470   0.4680   1.0000
   7.500   1.0475   0.03681   0.03100  -0.0461   0.4671   1.0000
   7.750   1.0814   0.03553   0.02980  -0.0453   0.4664   1.0000
   8.000   1.1159   0.03415   0.02849  -0.0444   0.4658   1.0000
   8.250   1.1501   0.03271   0.02717  -0.0436   0.4650   1.0000
   8.500   1.1461   0.03547   0.03002  -0.0442   0.4502   1.0000
   8.750   1.1886   0.03317   0.02785  -0.0433   0.4512   1.0000
   9.000   1.2291   0.03092   0.02572  -0.0423   0.4519   1.0000
   9.250   1.2383   0.03229   0.02719  -0.0428   0.4409   1.0000
   9.500   1.2798   0.02998   0.02505  -0.0420   0.4402   1.0000
   9.750   1.3239   0.02734   0.02256  -0.0410   0.4394   1.0000
  10.000   1.3404   0.02797   0.02331  -0.0412   0.4277   1.0000
  10.250   1.3689   0.02714   0.02259  -0.0407   0.4172   1.0000
  10.500   1.4227   0.02323   0.01864  -0.0393   0.4001   1.0000
  10.750   1.4296   0.02401   0.01914  -0.0380   0.3636   1.0000
  11.000   1.4140   0.02701   0.02193  -0.0365   0.3380   1.0000
  11.250   1.4055   0.02963   0.02441  -0.0353   0.3183   1.0000
  11.500   1.3942   0.03259   0.02725  -0.0343   0.2978   1.0000
  11.750   1.3867   0.03526   0.02984  -0.0333   0.2808   1.0000
  12.000   1.3744   0.03835   0.03278  -0.0323   0.2606   1.0000
  12.250   1.3672   0.04111   0.03551  -0.0315   0.2435   1.0000
  12.500   1.3585   0.04404   0.03839  -0.0308   0.2249   1.0000
  12.750   1.3426   0.04780   0.04200  -0.0302   0.1980   1.0000
  13.000   1.3225   0.05231   0.04626  -0.0299   0.1592   1.0000
  13.250   1.2977   0.05752   0.05108  -0.0297   0.1125   1.0000
  13.500   1.2702   0.06321   0.05635  -0.0295   0.0687   1.0000
  13.750   1.2511   0.06823   0.06112  -0.0296   0.0406   1.0000
  14.000   1.2307   0.07373   0.06649  -0.0298   0.0264   1.0000
  14.250   1.2205   0.07821   0.07106  -0.0301   0.0214   1.0000
  14.500   1.2044   0.08366   0.07659  -0.0307   0.0184   1.0000
  14.750   1.1995   0.08765   0.08073  -0.0312   0.0173   1.0000
  15.000   1.1939   0.09185   0.08505  -0.0319   0.0162   1.0000
  15.250   1.1895   0.09588   0.08920  -0.0326   0.0157   1.0000
  15.500   1.1841   0.10008   0.09349  -0.0333   0.0149   1.0000
  15.750   1.1753   0.10476   0.09820  -0.0343   0.0133   1.0000
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