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Coanda 2 (coanda2-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Coanda 2 (coanda2-il)
Reynolds number: 50,000
Max Cl/Cd: 37.53 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-coanda2-il-50000.txt
Download as CSV file: xf-coanda2-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4289   0.10733   0.10049  -0.0142   1.0000   0.1225
  -8.750  -0.4346   0.10571   0.09897  -0.0155   1.0000   0.1243
  -8.500  -0.4485   0.10487   0.09829  -0.0170   1.0000   0.1252
  -8.250  -0.4332   0.09888   0.09232  -0.0153   1.0000   0.1284
  -8.000  -0.4300   0.09566   0.08909  -0.0144   1.0000   0.1333
  -7.750  -0.4351   0.09357   0.08710  -0.0157   1.0000   0.1371
  -7.500  -0.4439   0.09256   0.08623  -0.0207   1.0000   0.1391
  -7.250  -0.4320   0.08728   0.08095  -0.0161   1.0000   0.1505
  -7.000  -0.4312   0.08405   0.07779  -0.0171   1.0000   0.1557
  -6.750  -0.4276   0.08132   0.07509  -0.0175   1.0000   0.1653
  -6.000  -0.0793   0.04497   0.03746  -0.0209   1.0000   1.0000
  -5.750  -0.0693   0.04299   0.03546  -0.0215   1.0000   1.0000
  -5.500  -0.0592   0.04113   0.03359  -0.0220   1.0000   1.0000
  -5.250  -0.0490   0.03935   0.03179  -0.0224   1.0000   1.0000
  -5.000  -0.0454   0.03802   0.03050  -0.0211   1.0000   0.9971
  -4.750  -0.1131   0.04000   0.03284  -0.0036   1.0000   0.9520
  -4.500  -0.1756   0.04099   0.03420   0.0105   1.0000   0.9084
  -4.250  -0.2291   0.04102   0.03457   0.0209   1.0000   0.8599
  -4.000  -0.2835   0.04087   0.03478   0.0312   1.0000   0.8269
  -3.250  -0.2773   0.03439   0.02655  -0.0107   1.0000   0.3308
  -3.000  -0.2451   0.03233   0.02363  -0.0123   1.0000   0.2911
  -2.750  -0.2222   0.03063   0.02157  -0.0116   1.0000   0.2828
  -2.500  -0.1982   0.02952   0.01996  -0.0109   1.0000   0.2769
  -2.250  -0.1743   0.02826   0.01836  -0.0101   1.0000   0.2679
  -2.000  -0.1497   0.02734   0.01707  -0.0094   1.0000   0.2605
  -1.750  -0.1249   0.02646   0.01582  -0.0088   1.0000   0.2546
  -1.500  -0.0999   0.02593   0.01490  -0.0082   1.0000   0.2497
  -1.250  -0.0751   0.02520   0.01400  -0.0077   1.0000   0.2474
  -1.000  -0.0503   0.02463   0.01325  -0.0072   1.0000   0.2457
  -0.750  -0.0243   0.02421   0.01265  -0.0071   1.0000   0.2471
  -0.500   0.0050   0.02390   0.01210  -0.0077   1.0000   0.2513
  -0.250   0.0376   0.02355   0.01167  -0.0091   1.0000   0.2539
   0.000   0.0684   0.02336   0.01140  -0.0102   1.0000   0.2549
   0.250   0.0968   0.02328   0.01131  -0.0111   1.0000   0.2568
   0.500   0.1224   0.02333   0.01139  -0.0117   1.0000   0.2598
   0.750   0.1452   0.02358   0.01163  -0.0120   1.0000   0.2639
   1.000   0.1668   0.02391   0.01210  -0.0126   1.0000   0.2695
   1.250   0.1893   0.02456   0.01285  -0.0140   0.9982   0.2775
   1.500   0.2886   0.02463   0.01396  -0.0298   0.9699   0.3705
   1.750   0.4104   0.02395   0.01429  -0.0484   0.9393   1.0000
   2.000   0.4934   0.02375   0.01411  -0.0584   0.9021   1.0000
   2.250   0.5687   0.02296   0.01345  -0.0661   0.8637   1.0000
   2.500   0.6321   0.02193   0.01257  -0.0706   0.8236   1.0000
   2.750   0.6827   0.02110   0.01190  -0.0724   0.7808   1.0000
   3.000   0.7222   0.02070   0.01150  -0.0723   0.7375   1.0000
   3.250   0.7549   0.02074   0.01147  -0.0714   0.6949   1.0000
   3.500   0.7829   0.02106   0.01167  -0.0698   0.6514   1.0000
   3.750   0.8023   0.02138   0.01180  -0.0663   0.5976   1.0000
   4.000   0.8229   0.02193   0.01221  -0.0638   0.5542   1.0000
   4.250   0.8409   0.02241   0.01258  -0.0610   0.5115   1.0000
   4.500   0.8616   0.02305   0.01326  -0.0591   0.4776   1.0000
   4.750   0.8786   0.02348   0.01360  -0.0564   0.4384   1.0000
   5.000   0.8992   0.02411   0.01432  -0.0546   0.4087   1.0000
   5.250   0.9191   0.02469   0.01513  -0.0526   0.3800   1.0000
   5.500   0.9282   0.02478   0.01519  -0.0487   0.3328   1.0000
   5.750   0.9367   0.02504   0.01539  -0.0449   0.2689   1.0000
   6.000   0.9452   0.02663   0.01627  -0.0417   0.1470   1.0000
   6.250   0.9579   0.02919   0.01828  -0.0393   0.0961   1.0000
   6.500   0.9725   0.03121   0.02026  -0.0369   0.0838   1.0000
   6.750   0.9882   0.03313   0.02225  -0.0346   0.0775   1.0000
   7.000   1.0052   0.03533   0.02448  -0.0325   0.0737   1.0000
   7.250   1.0270   0.03762   0.02703  -0.0308   0.0701   1.0000
   7.500   1.0474   0.04007   0.02964  -0.0293   0.0659   1.0000
   7.750   1.0689   0.04315   0.03291  -0.0283   0.0636   1.0000
   8.000   1.0891   0.04686   0.03695  -0.0270   0.0631   1.0000
   8.250   1.1032   0.05051   0.04112  -0.0249   0.0636   1.0000
   8.500   1.1102   0.05438   0.04561  -0.0222   0.0646   1.0000
   8.750   1.1067   0.05889   0.05078  -0.0192   0.0660   1.0000
   9.000   1.0956   0.06371   0.05615  -0.0163   0.0675   1.0000
   9.250   1.0809   0.06840   0.06122  -0.0138   0.0687   1.0000
   9.500   1.0620   0.07302   0.06609  -0.0116   0.0697   1.0000
   9.750   1.0394   0.07732   0.07057  -0.0098   0.0705   1.0000
  10.000   1.0158   0.08230   0.07568  -0.0099   0.0711   1.0000
  10.250   0.9913   0.08840   0.08188  -0.0123   0.0719   1.0000
  10.500   0.9683   0.09556   0.08908  -0.0166   0.0726   1.0000
  10.750   0.9524   0.10306   0.09657  -0.0206   0.0737   1.0000
  11.000   0.9066   0.11981   0.11316  -0.0337   0.0791   1.0000
  11.250   0.8936   0.12825   0.12150  -0.0379   0.0828   1.0000
  11.500   0.8930   0.13386   0.12708  -0.0392   0.0854   1.0000
  11.750   0.9004   0.13818   0.13141  -0.0387   0.0869   1.0000
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