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Coanda 2 (coanda2-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: Coanda 2 (coanda2-il)
Reynolds number: 500,000
Max Cl/Cd: 52.92 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-coanda2-il-500000-n5.txt
Download as CSV file: xf-coanda2-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4394   0.08842   0.08629  -0.0161   1.0000   0.0036
  -8.500  -0.4452   0.08491   0.08283  -0.0164   1.0000   0.0033
  -8.250  -0.4527   0.08220   0.08016  -0.0159   1.0000   0.0035
  -8.000  -0.4598   0.07974   0.07774  -0.0150   1.0000   0.0038
  -7.750  -0.4640   0.07598   0.07402  -0.0159   1.0000   0.0037
  -7.500  -0.4653   0.07257   0.07062  -0.0167   1.0000   0.0040
  -7.250  -0.4628   0.06808   0.06613  -0.0192   0.9995   0.0040
  -7.000  -0.4393   0.05982   0.05780  -0.0289   0.9959   0.0039
  -6.750  -0.4150   0.05242   0.05028  -0.0363   0.9919   0.0048
  -6.500  -0.3915   0.04045   0.03796  -0.0455   0.9868   0.0046
  -6.250  -0.3801   0.02744   0.02418  -0.0483   0.9793   0.0042
  -6.000  -0.3562   0.02219   0.01837  -0.0489   0.9766   0.0045
  -5.750  -0.3382   0.01918   0.01487  -0.0472   0.9706   0.0044
  -5.500  -0.3114   0.01694   0.01219  -0.0470   0.9671   0.0044
  -5.250  -0.2853   0.01534   0.01029  -0.0465   0.9629   0.0044
  -5.000  -0.2605   0.01391   0.00858  -0.0455   0.9575   0.0045
  -4.750  -0.2304   0.01289   0.00733  -0.0457   0.9544   0.0044
  -4.500  -0.2031   0.01219   0.00647  -0.0452   0.9491   0.0046
  -4.250  -0.1730   0.01177   0.00588  -0.0452   0.9431   0.0050
  -4.000  -0.1388   0.01102   0.00492  -0.0463   0.9399   0.0058
  -3.750  -0.1106   0.01042   0.00421  -0.0462   0.9331   0.0115
  -3.500  -0.0773   0.00977   0.00344  -0.0474   0.9286   0.0176
  -3.250  -0.0445   0.00938   0.00293  -0.0484   0.9235   0.0212
  -3.000  -0.0120   0.00913   0.00262  -0.0493   0.9166   0.0244
  -2.750   0.0210   0.00875   0.00231  -0.0504   0.9096   0.0471
  -2.500   0.0557   0.00872   0.00229  -0.0518   0.9004   0.0577
  -2.250   0.0874   0.00867   0.00218  -0.0525   0.8893   0.0613
  -2.000   0.1189   0.00865   0.00215  -0.0532   0.8761   0.0636
  -1.750   0.1494   0.00865   0.00212  -0.0536   0.8597   0.0655
  -1.500   0.1778   0.00865   0.00202  -0.0535   0.8379   0.0673
  -1.250   0.2047   0.00865   0.00192  -0.0532   0.8083   0.0688
  -1.000   0.2292   0.00874   0.00184  -0.0522   0.7641   0.0704
  -0.750   0.2494   0.00907   0.00187  -0.0503   0.6932   0.0722
  -0.500   0.2693   0.00939   0.00195  -0.0485   0.6373   0.0740
  -0.250   0.2904   0.00947   0.00188  -0.0470   0.5986   0.0760
   0.000   0.3127   0.00958   0.00187  -0.0458   0.5613   0.0772
   0.250   0.3351   0.00970   0.00186  -0.0446   0.5228   0.0784
   0.500   0.3575   0.00981   0.00183  -0.0435   0.4860   0.0794
   0.750   0.3804   0.00991   0.00182  -0.0424   0.4537   0.0801
   1.000   0.4032   0.01005   0.00183  -0.0414   0.4205   0.0813
   1.500   0.4494   0.01036   0.00189  -0.0395   0.3530   0.0836
   1.750   0.4737   0.01045   0.00193  -0.0388   0.3323   0.0847
   2.000   0.4976   0.01059   0.00198  -0.0381   0.3048   0.0857
   2.250   0.5209   0.01080   0.00206  -0.0373   0.2696   0.0864
   2.500   0.5441   0.01099   0.00214  -0.0364   0.2359   0.0876
   2.750   0.5668   0.01125   0.00232  -0.0355   0.1974   0.0892
   3.000   0.5873   0.01177   0.00256  -0.0343   0.1347   0.0906
   3.250   0.6068   0.01242   0.00290  -0.0329   0.0628   0.0924
   3.500   0.6281   0.01292   0.00328  -0.0317   0.0176   0.0944
   3.750   0.6515   0.01322   0.00370  -0.0308   0.0114   0.0963
   4.000   0.6737   0.01369   0.00434  -0.0295   0.0075   0.0984
   4.250   0.6980   0.01386   0.00454  -0.0289   0.0055   0.1022
   4.500   0.7215   0.01412   0.00488  -0.0281   0.0039   0.1085
   4.750   0.7403   0.01497   0.00589  -0.0262   0.0027   0.1174
   5.000   0.9108   0.01721   0.01028  -0.0604   0.0022   1.0000
   5.250   0.9294   0.01838   0.01151  -0.0586   0.0022   1.0000
   5.500   0.9482   0.01982   0.01301  -0.0567   0.0022   1.0000
   5.750   0.9680   0.02119   0.01447  -0.0551   0.0023   1.0000
   6.000   0.9879   0.02292   0.01632  -0.0535   0.0023   1.0000
   6.250   1.0074   0.02465   0.01820  -0.0519   0.0023   1.0000
   6.500   1.0258   0.02674   0.02048  -0.0501   0.0024   1.0000
   6.750   1.0425   0.02895   0.02291  -0.0481   0.0024   1.0000
   7.000   1.0570   0.03135   0.02556  -0.0459   0.0025   1.0000
   8.500   1.1175   0.04475   0.04032  -0.0309   0.0032   1.0000
   8.750   1.1165   0.04740   0.04326  -0.0273   0.0033   1.0000
   9.000   1.1124   0.05019   0.04627  -0.0240   0.0033   1.0000
   9.250   1.1031   0.05307   0.04935  -0.0201   0.0033   1.0000
   9.500   1.0884   0.05518   0.05163  -0.0155   0.0033   1.0000
   9.750   1.0722   0.05789   0.05450  -0.0122   0.0033   1.0000
  10.000   1.0542   0.06139   0.05816  -0.0104   0.0033   1.0000
  10.250   1.0382   0.06524   0.06219  -0.0103   0.0034   1.0000
  10.500   1.0193   0.07039   0.06752  -0.0123   0.0034   1.0000
  10.750   1.0030   0.07631   0.07359  -0.0160   0.0034   1.0000
  11.000   0.9810   0.08508   0.08259  -0.0229   0.0036   1.0000
  11.250   0.9626   0.09410   0.09174  -0.0293   0.0037   1.0000
  11.500   0.9404   0.10534   0.10312  -0.0367   0.0038   1.0000
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