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E. Bambino (ebambino7-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E. Bambino (ebambino7-il)
Reynolds number: 100,000
Max Cl/Cd: 35 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ebambino7-il-100000.txt
Download as CSV file: xf-ebambino7-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E. Bambino                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.6020   0.11532   0.11099   0.0269   1.0000   0.0469
  -7.250  -0.6021   0.11229   0.10802   0.0222   1.0000   0.0474
  -7.000  -0.6031   0.10898   0.10477   0.0165   1.0000   0.0476
  -6.750  -0.6009   0.10571   0.10147   0.0111   1.0000   0.0478
  -6.500  -0.5959   0.10247   0.09816   0.0064   1.0000   0.0480
  -6.250  -0.5874   0.09426   0.09009   0.0170   1.0000   0.0526
  -6.000  -0.5814   0.09021   0.08605   0.0142   1.0000   0.0550
  -5.750  -0.5737   0.08611   0.08193   0.0104   1.0000   0.0575
  -5.500  -0.5610   0.08276   0.07843   0.0037   1.0000   0.0601
  -5.250  -0.5465   0.08144   0.07669  -0.0020   1.0000   0.0611
  -5.000  -0.5407   0.07294   0.06857   0.0007   1.0000   0.0634
  -4.750  -0.5285   0.06887   0.06450   0.0006   1.0000   0.0670
  -4.500  -0.5054   0.06649   0.06173  -0.0036   1.0000   0.0738
  -4.250  -0.4930   0.06089   0.05615  -0.0041   1.0000   0.0764
  -4.000  -0.4774   0.05698   0.05226  -0.0039   1.0000   0.0816
  -3.750  -0.4546   0.05367   0.04857  -0.0058   1.0000   0.0894
  -3.500  -0.4372   0.04973   0.04468  -0.0056   1.0000   0.0950
  -3.250  -0.4152   0.04635   0.04106  -0.0063   1.0000   0.1048
  -3.000  -0.3931   0.04329   0.03779  -0.0066   1.0000   0.1176
  -2.750  -0.3717   0.04016   0.03456  -0.0066   1.0000   0.1323
  -2.500  -0.3500   0.03751   0.03174  -0.0066   1.0000   0.1579
  -2.250  -0.3300   0.03453   0.02875  -0.0062   1.0000   0.1879
  -2.000  -0.3105   0.03190   0.02616  -0.0055   1.0000   0.2304
  -1.750  -0.2893   0.02929   0.02357  -0.0048   1.0000   0.2710
  -1.500  -0.2613   0.02693   0.02102  -0.0046   1.0000   0.2881
  -1.250  -0.1900   0.02471   0.01661  -0.0028   1.0000   0.0599
  -1.000  -0.1608   0.02214   0.01368  -0.0017   1.0000   0.0499
  -0.750  -0.1327   0.02054   0.01192  -0.0009   1.0000   0.0465
  -0.500  -0.1054   0.01940   0.01057   0.0000   1.0000   0.0479
  -0.250  -0.0806   0.01751   0.00884   0.0006   1.0000   0.0550
   0.000  -0.0559   0.01630   0.00766   0.0017   1.0000   0.0576
   0.250  -0.0173   0.01479   0.00614   0.0001   0.9771   0.0665
   0.500   0.0166   0.01210   0.00488  -0.0012   0.9491   0.4502
   0.750   0.0928   0.01115   0.00471  -0.0067   0.8602   1.0000
   1.000   0.1067   0.01136   0.00431  -0.0023   0.7416   1.0000
   1.250   0.1274   0.01159   0.00405  -0.0003   0.6770   1.0000
   1.500   0.1506   0.01180   0.00383   0.0009   0.6238   1.0000
   1.750   0.1747   0.01198   0.00370   0.0018   0.5668   1.0000
   2.000   0.1964   0.01290   0.00349   0.0028   0.3363   1.0000
   2.250   0.2212   0.01340   0.00359   0.0031   0.2489   1.0000
   2.500   0.2456   0.01416   0.00374   0.0033   0.1629   1.0000
   2.750   0.2707   0.01451   0.00395   0.0037   0.1367   1.0000
   3.000   0.2961   0.01477   0.00415   0.0041   0.1156   1.0000
   3.250   0.3215   0.01509   0.00433   0.0045   0.1054   1.0000
   3.500   0.3469   0.01542   0.00458   0.0049   0.1010   1.0000
   3.750   0.3724   0.01579   0.00489   0.0053   0.0983   1.0000
   4.000   0.3978   0.01621   0.00528   0.0056   0.0965   1.0000
   4.250   0.4231   0.01667   0.00573   0.0060   0.0955   1.0000
   4.500   0.4485   0.01714   0.00631   0.0063   0.0948   1.0000
   4.750   0.4739   0.01758   0.00679   0.0066   0.0924   1.0000
   5.000   0.4984   0.01810   0.00717   0.0066   0.0818   1.0000
   5.250   0.5237   0.01855   0.00768   0.0068   0.0792   1.0000
   5.500   0.5489   0.01902   0.00818   0.0069   0.0769   1.0000
   5.750   0.5724   0.01995   0.00906   0.0070   0.0701   1.0000
   6.000   0.5966   0.02062   0.00981   0.0070   0.0631   1.0000
   6.250   0.6203   0.02153   0.01076   0.0070   0.0569   1.0000
   6.500   0.6458   0.02193   0.01124   0.0071   0.0548   1.0000
   6.750   0.6711   0.02241   0.01180   0.0072   0.0535   1.0000
   7.000   0.6966   0.02285   0.01235   0.0074   0.0529   1.0000
   7.250   0.7222   0.02324   0.01289   0.0076   0.0521   1.0000
   7.500   0.7456   0.02411   0.01380   0.0076   0.0478   1.0000
   7.750   0.7729   0.02400   0.01409   0.0077   0.0470   1.0000
   8.000   0.8012   0.02372   0.01410   0.0078   0.0439   1.0000
   8.250   0.8279   0.02394   0.01455   0.0081   0.0423   1.0000
   8.500   0.8540   0.02440   0.01525   0.0085   0.0410   1.0000
   8.750   0.8791   0.02519   0.01635   0.0090   0.0398   1.0000
   9.000   0.9028   0.02646   0.01799   0.0097   0.0389   1.0000
   9.250   0.9251   0.02820   0.02009   0.0105   0.0373   1.0000
   9.500   0.9457   0.03065   0.02293   0.0116   0.0354   1.0000
   9.750   0.9647   0.03343   0.02612   0.0126   0.0327   1.0000
  10.000   0.9843   0.03518   0.02827   0.0132   0.0301   1.0000
  10.250   0.9994   0.03805   0.03148   0.0141   0.0296   1.0000
  10.500   1.0017   0.04407   0.03815   0.0152   0.0306   1.0000
  10.750   0.9953   0.05031   0.04499   0.0157   0.0313   1.0000
  11.000   0.9821   0.05626   0.05139   0.0155   0.0318   1.0000
  11.250   0.9629   0.06171   0.05714   0.0145   0.0319   1.0000
  11.500   0.9404   0.06768   0.06330   0.0109   0.0318   1.0000
  11.750   0.9059   0.07935   0.07498   0.0002   0.0334   1.0000
  12.000   0.8842   0.09035   0.08596  -0.0077   0.0353   1.0000
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