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Coanda 3 (coanda3-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Coanda 3 (coanda3-il)
Reynolds number: 50,000
Max Cl/Cd: 37.07 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-coanda3-il-50000.txt
Download as CSV file: xf-coanda3-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Coanda 3                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4252   0.10230   0.09560  -0.0209   1.0000   0.1490
  -8.500  -0.4356   0.10053   0.09395  -0.0214   1.0000   0.1529
  -8.250  -0.4553   0.09964   0.09323  -0.0223   1.0000   0.1543
  -8.000  -0.4478   0.09502   0.08867  -0.0208   1.0000   0.1569
  -7.750  -0.4425   0.09150   0.08519  -0.0193   1.0000   0.1618
  -7.500  -0.4530   0.08958   0.08336  -0.0206   1.0000   0.1670
  -7.250  -0.4565   0.08637   0.08024  -0.0209   1.0000   0.1700
  -7.000  -0.4498   0.08274   0.07665  -0.0186   1.0000   0.1765
  -6.750  -0.4601   0.08100   0.07493  -0.0215   1.0000   0.1827
  -6.500  -0.4507   0.07687   0.07086  -0.0177   1.0000   0.1918
  -6.250  -0.4498   0.07378   0.06781  -0.0170   1.0000   0.2010
  -6.000  -0.4476   0.07087   0.06493  -0.0154   1.0000   0.2170
  -4.500  -0.3611   0.04453   0.03680  -0.0229   1.0000   0.1114
  -4.250  -0.3444   0.04086   0.03278  -0.0217   1.0000   0.1089
  -4.000  -0.3259   0.03746   0.02887  -0.0203   1.0000   0.1090
  -3.750  -0.3052   0.03419   0.02480  -0.0186   1.0000   0.1132
  -3.500  -0.2853   0.03150   0.02169  -0.0170   1.0000   0.1255
  -3.250  -0.2665   0.02901   0.01897  -0.0152   1.0000   0.1616
  -3.000  -0.2492   0.02781   0.01763  -0.0136   1.0000   0.2026
  -2.750  -0.2279   0.02694   0.01645  -0.0124   1.0000   0.2197
  -2.500  -0.2081   0.02643   0.01575  -0.0113   1.0000   0.2396
  -2.250  -0.1890   0.02596   0.01524  -0.0101   1.0000   0.2624
  -2.000  -0.1655   0.02539   0.01437  -0.0095   1.0000   0.2669
  -1.750  -0.1410   0.02483   0.01351  -0.0089   1.0000   0.2675
  -1.500  -0.1136   0.02436   0.01282  -0.0089   1.0000   0.2695
  -1.250  -0.0846   0.02399   0.01225  -0.0093   1.0000   0.2731
  -1.000  -0.0571   0.02372   0.01178  -0.0094   1.0000   0.2786
  -0.750  -0.0306   0.02338   0.01138  -0.0095   1.0000   0.2866
  -0.500  -0.0068   0.02313   0.01116  -0.0092   1.0000   0.3017
  -0.250   0.0158   0.02288   0.01102  -0.0087   1.0000   0.3232
   0.000   0.0885   0.02057   0.01093  -0.0177   1.0000   1.0000
   0.250   0.1079   0.02102   0.01088  -0.0164   1.0000   1.0000
   0.500   0.1256   0.02147   0.01099  -0.0151   1.0000   1.0000
   0.750   0.1426   0.02196   0.01126  -0.0139   1.0000   1.0000
   1.000   0.1593   0.02249   0.01165  -0.0128   1.0000   1.0000
   1.250   0.1757   0.02306   0.01211  -0.0118   1.0000   1.0000
   1.500   0.1918   0.02369   0.01266  -0.0109   1.0000   1.0000
   1.750   0.2076   0.02437   0.01331  -0.0101   1.0000   1.0000
   2.000   0.2229   0.02512   0.01404  -0.0094   1.0000   1.0000
   2.250   0.2840   0.02659   0.01556  -0.0178   0.9794   1.0000
   2.500   0.3535   0.02772   0.01682  -0.0271   0.9500   1.0000
   2.750   0.4279   0.02831   0.01767  -0.0363   0.9178   1.0000
   3.000   0.4988   0.02812   0.01777  -0.0436   0.8801   1.0000
   3.250   0.5770   0.02695   0.01707  -0.0505   0.8390   1.0000
   3.500   0.6653   0.02458   0.01522  -0.0575   0.7943   1.0000
   3.750   0.7345   0.02244   0.01349  -0.0605   0.7363   1.0000
   4.000   0.7834   0.02169   0.01273  -0.0610   0.6663   1.0000
   4.250   0.8134   0.02206   0.01298  -0.0596   0.6066   1.0000
   4.500   0.8404   0.02267   0.01349  -0.0583   0.5597   1.0000
   4.750   0.8546   0.02307   0.01369  -0.0545   0.5088   1.0000
   5.000   0.8644   0.02346   0.01386  -0.0501   0.4569   1.0000
   5.250   0.8846   0.02425   0.01462  -0.0482   0.4231   1.0000
   5.500   0.8976   0.02490   0.01526  -0.0451   0.3859   1.0000
   5.750   0.9073   0.02546   0.01583  -0.0414   0.3482   1.0000
   6.000   0.9078   0.02590   0.01621  -0.0363   0.3003   1.0000
   6.250   0.9061   0.02645   0.01666  -0.0311   0.2320   1.0000
   6.500   0.9083   0.02849   0.01793  -0.0269   0.1290   1.0000
   6.750   0.9214   0.03070   0.01980  -0.0243   0.0991   1.0000
   7.000   0.9378   0.03272   0.02180  -0.0221   0.0879   1.0000
   7.250   0.9584   0.03499   0.02406  -0.0205   0.0813   1.0000
   7.500   0.9827   0.03730   0.02668  -0.0193   0.0745   1.0000
   7.750   1.0075   0.04027   0.02967  -0.0187   0.0695   1.0000
   8.000   1.0311   0.04345   0.03333  -0.0175   0.0681   1.0000
   8.250   1.0486   0.04710   0.03745  -0.0158   0.0679   1.0000
   8.500   1.0594   0.05095   0.04176  -0.0135   0.0682   1.0000
   8.750   1.0654   0.05498   0.04621  -0.0110   0.0690   1.0000
   9.000   1.0671   0.05926   0.05084  -0.0083   0.0697   1.0000
   9.250   1.0690   0.06385   0.05568  -0.0061   0.0705   1.0000
   9.500   1.0532   0.06708   0.05946  -0.0021   0.0717   1.0000
   9.750   1.0228   0.07069   0.06348   0.0022   0.0730   1.0000
  10.000   0.9914   0.07484   0.06787   0.0051   0.0738   1.0000
  10.250   0.9615   0.07958   0.07279   0.0057   0.0747   1.0000
  10.500   0.9302   0.08565   0.07898   0.0038   0.0757   1.0000
  10.750   0.8995   0.09337   0.08675  -0.0007   0.0770   1.0000
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