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Coanda 2 (coanda2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: Coanda 2 (coanda2-il)
Reynolds number: 1,000,000
Max Cl/Cd: 58.34 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-coanda2-il-1000000.txt
Download as CSV file: xf-coanda2-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Coanda 2                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4446   0.09932   0.09772  -0.0132   1.0000   0.0072
  -9.500  -0.4598   0.09277   0.09121  -0.0150   1.0000   0.0077
  -9.250  -0.4612   0.08938   0.08784  -0.0157   1.0000   0.0078
  -9.000  -0.4595   0.08737   0.08585  -0.0158   1.0000   0.0082
  -8.750  -0.4682   0.08327   0.08178  -0.0164   1.0000   0.0080
  -8.500  -0.4637   0.08289   0.08142  -0.0155   1.0000   0.0087
  -8.250  -0.4807   0.07950   0.07807  -0.0141   1.0000   0.0084
  -8.000  -0.4759   0.07820   0.07677  -0.0139   1.0000   0.0095
  -7.750  -0.4775   0.07523   0.07382  -0.0144   1.0000   0.0101
  -7.500  -0.4800   0.07185   0.07045  -0.0150   1.0000   0.0104
  -7.250  -0.4682   0.06652   0.06510  -0.0201   0.9989   0.0106
  -6.750  -0.4408   0.02546   0.02277  -0.0467   0.9864   0.0076
  -6.500  -0.4109   0.02264   0.01963  -0.0480   0.9845   0.0074
  -6.250  -0.3858   0.01882   0.01531  -0.0486   0.9827   0.0075
  -6.000  -0.3679   0.01666   0.01284  -0.0468   0.9773   0.0076
  -5.750  -0.3404   0.01520   0.01114  -0.0467   0.9745   0.0075
  -5.500  -0.3108   0.01383   0.00955  -0.0470   0.9725   0.0074
  -5.250  -0.2797   0.01232   0.00779  -0.0476   0.9708   0.0074
  -5.000  -0.2493   0.01054   0.00571  -0.0480   0.9694   0.0086
  -4.750  -0.2273   0.00992   0.00497  -0.0464   0.9636   0.0095
  -4.500  -0.1964   0.00938   0.00435  -0.0468   0.9611   0.0105
  -4.250  -0.1639   0.00889   0.00376  -0.0476   0.9592   0.0112
  -4.000  -0.1295   0.00846   0.00326  -0.0488   0.9574   0.0122
  -3.750  -0.0940   0.00805   0.00271  -0.0503   0.9559   0.0147
  -3.500  -0.0704   0.00770   0.00230  -0.0491   0.9495   0.0197
  -3.250  -0.0357   0.00778   0.00264  -0.0504   0.9457   0.0617
  -3.000   0.0041   0.00843   0.00338  -0.0529   0.9426   0.0675
  -2.750   0.0327   0.00865   0.00358  -0.0528   0.9349   0.0700
  -2.500   0.0692   0.00867   0.00357  -0.0546   0.9291   0.0716
  -2.250   0.0996   0.00929   0.00419  -0.0549   0.9190   0.0731
  -2.000   0.1299   0.00851   0.00336  -0.0555   0.9091   0.0765
  -1.750   0.1599   0.00834   0.00315  -0.0559   0.8970   0.0776
  -1.500   0.1880   0.00816   0.00293  -0.0558   0.8823   0.0784
  -1.250   0.2148   0.00801   0.00272  -0.0554   0.8636   0.0790
  -1.000   0.2402   0.00789   0.00252  -0.0547   0.8400   0.0796
  -0.750   0.2632   0.00783   0.00233  -0.0534   0.8017   0.0800
  -0.500   0.2818   0.00792   0.00217  -0.0512   0.7346   0.0803
  -0.250   0.2978   0.00815   0.00207  -0.0484   0.6532   0.0806
   0.000   0.3183   0.00826   0.00199  -0.0468   0.6051   0.0808
   0.250   0.3401   0.00833   0.00191  -0.0454   0.5640   0.0811
   0.500   0.3625   0.00839   0.00183  -0.0442   0.5248   0.0814
   0.750   0.3857   0.00842   0.00176  -0.0432   0.4919   0.0817
   1.000   0.4092   0.00846   0.00171  -0.0422   0.4650   0.0822
   1.500   0.4556   0.00869   0.00172  -0.0403   0.4025   0.0840
   1.750   0.4788   0.00881   0.00172  -0.0393   0.3679   0.0847
   2.000   0.5019   0.00898   0.00175  -0.0384   0.3309   0.0856
   2.250   0.5244   0.00924   0.00181  -0.0373   0.2822   0.0863
   2.500   0.5432   0.00971   0.00188  -0.0357   0.1960   0.0880
   2.750   0.5571   0.01073   0.00224  -0.0332   0.0546   0.0903
   3.000   0.5795   0.01108   0.00244  -0.0321   0.0176   0.0918
   3.250   0.6045   0.01118   0.00262  -0.0315   0.0148   0.0934
   3.500   0.6292   0.01131   0.00284  -0.0308   0.0129   0.0947
   3.750   0.6536   0.01148   0.00306  -0.0301   0.0121   0.0962
   4.000   0.6775   0.01170   0.00337  -0.0292   0.0111   0.0975
   4.250   0.7007   0.01201   0.00378  -0.0282   0.0100   0.0987
   4.500   0.7226   0.01246   0.00430  -0.0270   0.0090   0.1001
   4.750   0.7436   0.01297   0.00491  -0.0255   0.0085   0.1053
   5.000   0.7654   0.01340   0.00543  -0.0243   0.0088   0.1122
   7.250   1.1031   0.03163   0.02671  -0.0491   0.0073   1.0000
   7.500   1.1192   0.03196   0.02723  -0.0469   0.0071   1.0000
   7.750   1.1374   0.03193   0.02736  -0.0451   0.0066   1.0000
   8.000   1.1514   0.03319   0.02882  -0.0428   0.0062   1.0000
   8.250   1.1617   0.03505   0.03091  -0.0401   0.0058   1.0000
   8.500   1.1698   0.03708   0.03314  -0.0374   0.0055   1.0000
   8.750   1.1751   0.03936   0.03562  -0.0344   0.0053   1.0000
   9.000   1.1780   0.04170   0.03816  -0.0314   0.0052   1.0000
   9.250   1.1776   0.04415   0.04079  -0.0281   0.0051   1.0000
   9.500   1.1747   0.04672   0.04353  -0.0247   0.0050   1.0000
   9.750   1.1651   0.04912   0.04610  -0.0204   0.0050   1.0000
  10.000   1.1515   0.05101   0.04809  -0.0158   0.0049   1.0000
  10.250   1.1355   0.05358   0.05080  -0.0123   0.0048   1.0000
  10.500   1.1182   0.05677   0.05415  -0.0102   0.0049   1.0000
  10.750   1.1000   0.06077   0.05830  -0.0097   0.0048   1.0000
  11.000   1.0828   0.06544   0.06310  -0.0110   0.0048   1.0000
  11.250   1.0616   0.07195   0.06979  -0.0148   0.0049   1.0000
  11.500   1.0459   0.07858   0.07654  -0.0194   0.0049   1.0000
  11.750   1.0225   0.08810   0.08622  -0.0263   0.0050   1.0000
  12.000   0.9986   0.09864   0.09690  -0.0334   0.0051   1.0000
  12.250   0.9747   0.10998   0.10835  -0.0403   0.0053   1.0000
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