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Coanda 3 (coanda3-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Coanda 3 (coanda3-il)
Reynolds number: 100,000
Max Cl/Cd: 52.65 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-coanda3-il-100000-n5.txt
Download as CSV file: xf-coanda3-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4252   0.08880   0.08428  -0.0263   1.0000   0.0321
  -8.000  -0.4347   0.08623   0.08179  -0.0254   1.0000   0.0312
  -7.750  -0.4458   0.08188   0.07751  -0.0267   1.0000   0.0262
  -7.500  -0.4492   0.07871   0.07438  -0.0266   1.0000   0.0259
  -7.250  -0.4513   0.07543   0.07113  -0.0265   1.0000   0.0256
  -7.000  -0.4514   0.07228   0.06799  -0.0263   1.0000   0.0245
  -6.750  -0.4509   0.06854   0.06424  -0.0265   1.0000   0.0238
  -6.500  -0.4483   0.06459   0.06021  -0.0268   1.0000   0.0230
  -6.250  -0.4439   0.06015   0.05570  -0.0273   1.0000   0.0222
  -6.000  -0.4376   0.05494   0.05036  -0.0279   1.0000   0.0209
  -5.750  -0.4290   0.04789   0.04309  -0.0285   1.0000   0.0193
  -5.500  -0.4154   0.04271   0.03759  -0.0280   1.0000   0.0183
  -5.250  -0.4024   0.03860   0.03305  -0.0268   1.0000   0.0177
  -5.000  -0.3864   0.03363   0.02751  -0.0262   0.9990   0.0173
  -4.750  -0.3589   0.02938   0.02253  -0.0271   0.9954   0.0170
  -4.500  -0.3305   0.02630   0.01877  -0.0274   0.9918   0.0169
  -4.250  -0.2998   0.02426   0.01620  -0.0279   0.9884   0.0168
  -4.000  -0.2693   0.02268   0.01419  -0.0282   0.9846   0.0171
  -3.750  -0.2378   0.02150   0.01267  -0.0287   0.9806   0.0176
  -3.500  -0.2058   0.02024   0.01109  -0.0294   0.9770   0.0202
  -3.250  -0.1748   0.01951   0.01010  -0.0299   0.9720   0.0216
  -3.000  -0.1406   0.01882   0.00921  -0.0309   0.9683   0.0239
  -2.750  -0.1113   0.01812   0.00847  -0.0311   0.9628   0.0296
  -2.500  -0.0769   0.01816   0.00855  -0.0323   0.9577   0.0818
  -2.250  -0.0442   0.01833   0.00855  -0.0333   0.9520   0.0953
  -2.000  -0.0119   0.01862   0.00870  -0.0344   0.9455   0.1109
  -1.750   0.0240   0.01874   0.00876  -0.0365   0.9412   0.1277
  -1.500   0.0519   0.01842   0.00840  -0.0366   0.9331   0.1311
  -1.250   0.0909   0.01807   0.00798  -0.0388   0.9280   0.1369
  -1.000   0.1210   0.01776   0.00757  -0.0392   0.9184   0.1404
  -0.750   0.1567   0.01731   0.00716  -0.0407   0.9105   0.1448
  -0.500   0.1934   0.01696   0.00678  -0.0423   0.9027   0.1511
  -0.250   0.2273   0.01663   0.00645  -0.0434   0.8934   0.1585
   0.000   0.2706   0.01618   0.00604  -0.0463   0.8866   0.1734
   0.250   0.3036   0.01570   0.00581  -0.0472   0.8747   0.2146
   0.750   0.4527   0.01370   0.00578  -0.0670   0.8633   1.0000
   1.000   0.4823   0.01360   0.00568  -0.0671   0.8488   1.0000
   1.250   0.5139   0.01345   0.00551  -0.0675   0.8313   1.0000
   1.500   0.5409   0.01333   0.00539  -0.0669   0.8066   1.0000
   1.750   0.5737   0.01315   0.00521  -0.0674   0.7778   1.0000
   2.000   0.6092   0.01301   0.00503  -0.0684   0.7468   1.0000
   2.250   0.6414   0.01300   0.00496  -0.0689   0.7133   1.0000
   2.500   0.6708   0.01311   0.00503  -0.0688   0.6751   1.0000
   2.750   0.6956   0.01333   0.00517  -0.0679   0.6315   1.0000
   3.000   0.7176   0.01363   0.00536  -0.0664   0.5776   1.0000
   3.250   0.7374   0.01404   0.00561  -0.0646   0.5142   1.0000
   3.500   0.7555   0.01457   0.00592  -0.0625   0.4557   1.0000
   3.750   0.7693   0.01541   0.00632  -0.0598   0.3851   1.0000
   4.000   0.7820   0.01635   0.00679  -0.0571   0.3125   1.0000
   4.250   0.7986   0.01703   0.00724  -0.0551   0.2550   1.0000
   4.500   0.8136   0.01793   0.00773  -0.0529   0.1741   1.0000
   4.750   0.8208   0.02005   0.00879  -0.0498   0.0288   1.0000
   5.000   0.8388   0.02101   0.00983  -0.0477   0.0234   1.0000
   5.250   0.8572   0.02190   0.01095  -0.0458   0.0204   1.0000
   5.500   0.8731   0.02309   0.01237  -0.0436   0.0176   1.0000
   5.750   0.8868   0.02442   0.01395  -0.0411   0.0166   1.0000
   6.000   0.8990   0.02572   0.01544  -0.0383   0.0161   1.0000
   6.250   0.9114   0.02692   0.01682  -0.0356   0.0158   1.0000
   6.500   0.9231   0.02830   0.01840  -0.0328   0.0154   1.0000
   6.750   0.9368   0.02965   0.01988  -0.0304   0.0148   1.0000
   7.000   0.9521   0.03115   0.02152  -0.0283   0.0137   1.0000
   7.250   0.9691   0.03294   0.02345  -0.0264   0.0130   1.0000
   7.500   0.9878   0.03495   0.02564  -0.0249   0.0129   1.0000
   7.750   1.0063   0.03733   0.02827  -0.0233   0.0128   1.0000
   8.000   1.0221   0.03976   0.03101  -0.0214   0.0129   1.0000
   8.250   1.0343   0.04247   0.03407  -0.0190   0.0130   1.0000
   8.500   1.0429   0.04501   0.03695  -0.0164   0.0132   1.0000
   8.750   1.0465   0.04793   0.04024  -0.0133   0.0134   1.0000
   9.000   1.0469   0.05063   0.04326  -0.0101   0.0136   1.0000
   9.250   1.0421   0.05348   0.04642  -0.0064   0.0139   1.0000
   9.500   1.0324   0.05625   0.04946  -0.0025   0.0140   1.0000
   9.750   1.0201   0.05914   0.05260   0.0011   0.0142   1.0000
  10.000   1.0076   0.06218   0.05587   0.0038   0.0144   1.0000
  10.250   0.9920   0.06564   0.05955   0.0057   0.0145   1.0000
  10.500   0.9763   0.06942   0.06354   0.0066   0.0146   1.0000
  10.750   0.9601   0.07357   0.06788   0.0063   0.0147   1.0000
  11.000   0.9418   0.07861   0.07310   0.0048   0.0148   1.0000
  11.250   0.9237   0.08431   0.07894   0.0021   0.0148   1.0000
  11.500   0.9059   0.09083   0.08561  -0.0019   0.0148   1.0000
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