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MILEY M06-13-128 (miley-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MILEY M06-13-128 (miley-il)
Reynolds number: 200,000
Max Cl/Cd: 62.75 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-miley-il-200000-n5.txt
Download as CSV file: xf-miley-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2597   0.09652   0.09171  -0.0155   0.5616   0.0160
  -7.750  -0.2554   0.09336   0.08858  -0.0174   0.5612   0.0160
  -7.500  -0.2530   0.09007   0.08532  -0.0200   0.5607   0.0162
  -7.250  -0.2505   0.08683   0.08212  -0.0222   0.5603   0.0163
  -7.000  -0.2511   0.08379   0.07910  -0.0245   0.5598   0.0163
  -6.750  -0.2456   0.08013   0.07543  -0.0281   0.5594   0.0164
  -6.500  -0.2374   0.07634   0.07161  -0.0314   0.5590   0.0164
  -6.250  -0.2272   0.07258   0.06779  -0.0342   0.5587   0.0164
  -6.000  -0.2153   0.06877   0.06393  -0.0367   0.5583   0.0165
  -5.750  -0.2019   0.06496   0.06002  -0.0388   0.5578   0.0165
  -5.500  -0.1872   0.06116   0.05613  -0.0406   0.5573   0.0165
  -5.250  -0.1713   0.05756   0.05241  -0.0418   0.5567   0.0165
  -5.000  -0.1543   0.05393   0.04862  -0.0428   0.5562   0.0165
  -4.750  -0.1364   0.05051   0.04503  -0.0434   0.5555   0.0165
  -4.500  -0.1254   0.04500   0.03945  -0.0438   0.5547   0.0108
  -4.250  -0.1056   0.04181   0.03605  -0.0440   0.5538   0.0104
  -4.000  -0.0841   0.03866   0.03262  -0.0439   0.5529   0.0102
  -3.750  -0.0606   0.03546   0.02907  -0.0433   0.5522   0.0106
  -3.500  -0.0374   0.03278   0.02602  -0.0427   0.5515   0.0120
  -3.250  -0.0136   0.03183   0.02495  -0.0428   0.5508   0.0140
  -3.000   0.0114   0.02948   0.02219  -0.0420   0.5501   0.0137
  -2.750   0.0372   0.02735   0.01966  -0.0411   0.5494   0.0131
  -2.500   0.0638   0.02557   0.01750  -0.0403   0.5486   0.0127
  -2.250   0.0908   0.02417   0.01577  -0.0396   0.5478   0.0126
  -2.000   0.1179   0.02308   0.01445  -0.0391   0.5470   0.0128
  -1.750   0.1449   0.02217   0.01337  -0.0386   0.5463   0.0132
  -1.500   0.1716   0.02143   0.01250  -0.0382   0.5457   0.0139
  -1.250   0.1978   0.02083   0.01181  -0.0377   0.5452   0.0150
  -1.000   0.2235   0.02030   0.01121  -0.0372   0.5446   0.0177
  -0.750   0.2494   0.02013   0.01110  -0.0371   0.5428   0.0224
  -0.500   0.2751   0.01995   0.01092  -0.0370   0.5411   0.0284
  -0.250   0.3015   0.01995   0.01085  -0.0369   0.5397   0.0335
   0.000   0.3276   0.01983   0.01079  -0.0367   0.5382   0.0538
   0.250   0.3445   0.01850   0.01084  -0.0355   0.5368   0.4632
   0.750   0.4672   0.01753   0.01093  -0.0491   0.5345   1.0000
   1.000   0.4927   0.01770   0.01097  -0.0487   0.5335   1.0000
   1.250   0.5182   0.01787   0.01103  -0.0483   0.5325   1.0000
   1.500   0.5438   0.01803   0.01109  -0.0480   0.5317   1.0000
   1.750   0.5695   0.01819   0.01114  -0.0476   0.5308   1.0000
   2.000   0.5936   0.01890   0.01192  -0.0479   0.5273   1.0000
   2.250   0.6183   0.01934   0.01237  -0.0478   0.5246   1.0000
   2.500   0.6436   0.01961   0.01260  -0.0476   0.5227   1.0000
   2.750   0.6692   0.01975   0.01270  -0.0473   0.5211   1.0000
   3.000   0.6951   0.01983   0.01272  -0.0470   0.5198   1.0000
   3.250   0.7213   0.01985   0.01269  -0.0466   0.5186   1.0000
   3.500   0.7477   0.01981   0.01259  -0.0462   0.5176   1.0000
   4.000   0.7954   0.02076   0.01368  -0.0463   0.5093   1.0000
   4.250   0.8219   0.02065   0.01354  -0.0459   0.5072   1.0000
   4.500   0.8491   0.02038   0.01324  -0.0455   0.5057   1.0000
   4.750   0.8768   0.02007   0.01290  -0.0451   0.5044   1.0000
   5.250   0.9234   0.02103   0.01407  -0.0452   0.4951   1.0000
   5.500   0.9501   0.02090   0.01396  -0.0449   0.4933   1.0000
   5.750   0.9773   0.02069   0.01378  -0.0447   0.4920   1.0000
   6.250   1.0226   0.02172   0.01506  -0.0447   0.4819   1.0000
   6.500   1.0498   0.02147   0.01488  -0.0445   0.4801   1.0000
   6.750   1.0769   0.02124   0.01470  -0.0443   0.4783   1.0000
   7.250   1.1220   0.02208   0.01580  -0.0443   0.4669   1.0000
   7.750   1.1576   0.02430   0.01836  -0.0449   0.4493   1.0000
   8.000   1.1804   0.02462   0.01879  -0.0449   0.4430   1.0000
   8.500   1.2279   0.02489   0.01925  -0.0448   0.4292   1.0000
   8.750   1.2494   0.02529   0.01976  -0.0449   0.4199   1.0000
   9.000   1.2824   0.02389   0.01842  -0.0440   0.4154   1.0000
   9.250   1.3095   0.02332   0.01790  -0.0434   0.4063   1.0000
   9.500   1.3408   0.02219   0.01678  -0.0425   0.3968   1.0000
   9.750   1.3661   0.02177   0.01636  -0.0417   0.3852   1.0000
  10.000   1.3836   0.02215   0.01672  -0.0408   0.3692   1.0000
  10.250   1.3914   0.02351   0.01805  -0.0401   0.3517   1.0000
  10.500   1.3850   0.02605   0.02054  -0.0391   0.3368   1.0000
  10.750   1.3817   0.02825   0.02270  -0.0380   0.3232   1.0000
  11.000   1.3767   0.03061   0.02497  -0.0368   0.3074   1.0000
  11.250   1.3680   0.03327   0.02750  -0.0356   0.2890   1.0000
  11.500   1.3576   0.03621   0.03034  -0.0346   0.2688   1.0000
  11.750   1.3456   0.03926   0.03323  -0.0336   0.2483   1.0000
  12.000   1.3355   0.04228   0.03614  -0.0328   0.2270   1.0000
  12.250   1.3236   0.04548   0.03920  -0.0320   0.2049   1.0000
  12.500   1.3197   0.04820   0.04186  -0.0316   0.1859   1.0000
  12.750   1.3080   0.05185   0.04532  -0.0312   0.1555   1.0000
  13.000   1.2922   0.05604   0.04924  -0.0310   0.1191   1.0000
  13.250   1.2766   0.06035   0.05329  -0.0308   0.0876   1.0000
  13.500   1.2625   0.06465   0.05740  -0.0307   0.0601   1.0000
  13.750   1.2568   0.06814   0.06083  -0.0307   0.0445   1.0000
  14.000   1.2424   0.07280   0.06533  -0.0310   0.0247   1.0000
  14.250   1.2306   0.07735   0.06982  -0.0314   0.0142   1.0000
  14.500   1.2250   0.08124   0.07379  -0.0318   0.0102   1.0000
  14.750   1.2198   0.08518   0.07783  -0.0322   0.0078   1.0000
  15.000   1.2145   0.08922   0.08196  -0.0328   0.0067   1.0000
  15.250   1.2087   0.09345   0.08632  -0.0336   0.0059   1.0000
  15.500   1.2055   0.09734   0.09035  -0.0344   0.0055   1.0000
  15.750   1.2018   0.10139   0.09454  -0.0352   0.0052   1.0000
  16.000   1.1963   0.10577   0.09903  -0.0363   0.0045   1.0000
  16.250   1.1925   0.10998   0.10338  -0.0374   0.0046   1.0000
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