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Coanda 1 (coanda1-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Coanda 1 (coanda1-il)
Reynolds number: 50,000
Max Cl/Cd: 37.68 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-coanda1-il-50000-n5.txt
Download as CSV file: xf-coanda1-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Coanda 1                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4221   0.10007   0.09329  -0.0169   1.0000   0.0432
  -8.000  -0.4224   0.09683   0.09014  -0.0173   1.0000   0.0419
  -7.500  -0.4316   0.09038   0.08389  -0.0208   1.0000   0.0369
  -7.250  -0.4285   0.08706   0.08062  -0.0212   1.0000   0.0367
  -7.000  -0.4256   0.08356   0.07716  -0.0222   1.0000   0.0367
  -6.750  -0.4210   0.08019   0.07382  -0.0227   1.0000   0.0364
  -6.500  -0.4160   0.07660   0.07026  -0.0235   1.0000   0.0364
  -6.250  -0.4099   0.07303   0.06669  -0.0242   1.0000   0.0362
  -6.000  -0.4029   0.06926   0.06291  -0.0248   1.0000   0.0360
  -5.750  -0.3944   0.06576   0.05937  -0.0251   1.0000   0.0357
  -5.500  -0.3852   0.06197   0.05551  -0.0253   1.0000   0.0354
  -5.250  -0.3747   0.05821   0.05165  -0.0253   1.0000   0.0351
  -5.000  -0.3632   0.05441   0.04772  -0.0252   1.0000   0.0349
  -4.750  -0.3508   0.05058   0.04371  -0.0246   1.0000   0.0348
  -4.500  -0.3374   0.04693   0.03983  -0.0238   1.0000   0.0349
  -4.250  -0.3232   0.04315   0.03577  -0.0226   1.0000   0.0353
  -4.000  -0.3080   0.03935   0.03159  -0.0212   1.0000   0.0362
  -3.750  -0.2915   0.03727   0.02928  -0.0196   1.0000   0.0397
  -3.500  -0.2736   0.03465   0.02623  -0.0179   1.0000   0.0440
  -3.250  -0.2545   0.03188   0.02303  -0.0161   1.0000   0.0477
  -3.000  -0.2338   0.02988   0.02061  -0.0143   1.0000   0.0558
  -2.750  -0.2122   0.02846   0.01864  -0.0125   1.0000   0.0787
  -2.500  -0.1939   0.02797   0.01750  -0.0106   1.0000   0.1130
  -2.250  -0.1768   0.02737   0.01675  -0.0094   1.0000   0.1408
  -2.000  -0.1538   0.02632   0.01533  -0.0085   1.0000   0.1435
  -1.750  -0.1310   0.02556   0.01431  -0.0077   1.0000   0.1464
  -1.500  -0.1079   0.02498   0.01345  -0.0070   1.0000   0.1489
  -1.250  -0.0844   0.02447   0.01267  -0.0063   1.0000   0.1490
  -1.000  -0.0578   0.02403   0.01193  -0.0062   1.0000   0.1487
  -0.750  -0.0289   0.02371   0.01135  -0.0067   1.0000   0.1486
  -0.500  -0.0008   0.02345   0.01089  -0.0071   1.0000   0.1490
  -0.250   0.0432   0.02323   0.01046  -0.0108   0.9927   0.1499
   0.000   0.0888   0.02304   0.01014  -0.0148   0.9835   0.1517
   0.250   0.1324   0.02289   0.00990  -0.0184   0.9732   0.1540
   0.500   0.1748   0.02272   0.00971  -0.0218   0.9619   0.1574
   0.750   0.2166   0.02254   0.00961  -0.0251   0.9496   0.1665
   1.000   0.2610   0.02231   0.00949  -0.0287   0.9344   0.1746
   1.250   0.3086   0.02199   0.00927  -0.0326   0.9168   0.1811
   1.500   0.3563   0.02156   0.00903  -0.0363   0.8985   0.1907
   2.000   0.5088   0.01904   0.00877  -0.0553   0.8597   1.0000
   2.250   0.5469   0.01875   0.00855  -0.0563   0.8240   1.0000
   2.500   0.5853   0.01851   0.00832  -0.0573   0.7860   1.0000
   2.750   0.6208   0.01839   0.00822  -0.0578   0.7476   1.0000
   3.000   0.6523   0.01843   0.00829  -0.0576   0.7073   1.0000
   3.250   0.6798   0.01861   0.00847  -0.0567   0.6650   1.0000
   3.500   0.7042   0.01889   0.00874  -0.0553   0.6203   1.0000
   3.750   0.7260   0.01927   0.00903  -0.0533   0.5679   1.0000
   4.000   0.7384   0.02000   0.00916  -0.0495   0.4558   1.0000
   4.250   0.7533   0.02091   0.00951  -0.0469   0.3613   1.0000
   4.500   0.7706   0.02188   0.01012  -0.0451   0.2976   1.0000
   4.750   0.7909   0.02266   0.01086  -0.0438   0.2590   1.0000
   5.000   0.8109   0.02349   0.01162  -0.0424   0.2148   1.0000
   5.250   0.8308   0.02439   0.01248  -0.0411   0.1658   1.0000
   5.750   0.8651   0.02789   0.01521  -0.0380   0.0328   1.0000
   6.000   0.8838   0.02925   0.01678  -0.0363   0.0296   1.0000
   6.250   0.9008   0.03075   0.01851  -0.0344   0.0268   1.0000
   6.500   0.9143   0.03259   0.02058  -0.0323   0.0250   1.0000
   6.750   0.9277   0.03424   0.02249  -0.0299   0.0244   1.0000
   7.000   0.9398   0.03599   0.02451  -0.0274   0.0241   1.0000
   7.250   0.9519   0.03772   0.02648  -0.0250   0.0240   1.0000
   7.500   0.9642   0.03965   0.02878  -0.0225   0.0238   1.0000
   7.750   0.9777   0.04178   0.03116  -0.0202   0.0238   1.0000
   8.000   0.9923   0.04415   0.03381  -0.0180   0.0237   1.0000
   8.250   1.0061   0.04663   0.03661  -0.0160   0.0235   1.0000
   8.500   1.0172   0.04942   0.03977  -0.0138   0.0233   1.0000
   8.750   1.0244   0.05235   0.04308  -0.0114   0.0230   1.0000
   9.000   1.0277   0.05539   0.04648  -0.0089   0.0229   1.0000
   9.250   1.0250   0.05872   0.05019  -0.0061   0.0227   1.0000
   9.500   1.0195   0.06185   0.05363  -0.0034   0.0227   1.0000
   9.750   1.0076   0.06500   0.05705  -0.0003   0.0228   1.0000
  10.000   0.9932   0.06843   0.06070   0.0019   0.0228   1.0000
  10.250   0.9782   0.07215   0.06463   0.0029   0.0229   1.0000
  10.500   0.9620   0.07656   0.06923   0.0026   0.0230   1.0000
  10.750   0.9475   0.08128   0.07410   0.0011   0.0233   1.0000
  11.000   0.9306   0.08708   0.08003  -0.0017   0.0234   1.0000
  11.250   0.9147   0.09353   0.08658  -0.0054   0.0236   1.0000
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