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Coanda 2 (coanda2-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Coanda 2 (coanda2-il)
Reynolds number: 500,000
Max Cl/Cd: 62.7 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-coanda2-il-500000.txt
Download as CSV file: xf-coanda2-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4375   0.09931   0.09707  -0.0141   1.0000   0.0160
  -9.250  -0.4360   0.09620   0.09398  -0.0148   1.0000   0.0165
  -9.000  -0.4356   0.09303   0.09084  -0.0155   1.0000   0.0176
  -8.750  -0.3653   0.07548   0.07348  -0.0225   1.0000   0.0216
  -8.500  -0.3591   0.07373   0.07175  -0.0210   1.0000   0.0229
  -8.250  -0.3602   0.07108   0.06912  -0.0206   1.0000   0.0236
  -8.000  -0.3647   0.06836   0.06644  -0.0199   1.0000   0.0243
  -7.750  -0.3746   0.06578   0.06390  -0.0188   1.0000   0.0247
  -7.500  -0.3887   0.06370   0.06185  -0.0166   1.0000   0.0251
  -7.250  -0.3970   0.06098   0.05917  -0.0159   1.0000   0.0259
  -7.000  -0.4043   0.05797   0.05618  -0.0157   1.0000   0.0265
  -6.750  -0.4097   0.05463   0.05284  -0.0161   1.0000   0.0275
  -5.750  -0.4304   0.02190   0.01804  -0.0294   0.9909   0.0141
  -5.500  -0.4002   0.01980   0.01551  -0.0298   0.9876   0.0131
  -5.250  -0.3646   0.01849   0.01394  -0.0313   0.9846   0.0126
  -5.000  -0.3315   0.01622   0.01121  -0.0322   0.9825   0.0126
  -4.750  -0.3079   0.01426   0.00885  -0.0310   0.9771   0.0129
  -4.500  -0.2753   0.01278   0.00705  -0.0315   0.9735   0.0144
  -4.250  -0.2380   0.01217   0.00629  -0.0332   0.9712   0.0159
  -4.000  -0.2005   0.01161   0.00556  -0.0350   0.9696   0.0184
  -3.750  -0.1748   0.01114   0.00493  -0.0342   0.9646   0.0202
  -3.500  -0.1419   0.01084   0.00483  -0.0349   0.9613   0.0578
  -3.250  -0.1005   0.01257   0.00666  -0.0374   0.9584   0.0690
  -3.000  -0.0604   0.01354   0.00761  -0.0398   0.9565   0.0731
  -2.750  -0.0344   0.01294   0.00701  -0.0395   0.9508   0.0765
  -2.500   0.0004   0.01344   0.00760  -0.0410   0.9470   0.0823
  -2.250   0.0369   0.01362   0.00789  -0.0431   0.9446   0.0928
  -2.000   0.0753   0.01255   0.00661  -0.0450   0.9427   0.0901
  -1.750   0.1027   0.01208   0.00613  -0.0447   0.9353   0.0917
  -1.500   0.1410   0.01141   0.00539  -0.0468   0.9309   0.0919
  -1.250   0.1735   0.01091   0.00485  -0.0475   0.9233   0.0927
  -1.000   0.2114   0.01044   0.00436  -0.0495   0.9158   0.0938
  -0.750   0.2438   0.01007   0.00397  -0.0503   0.9039   0.0945
  -0.500   0.2778   0.00973   0.00359  -0.0514   0.8891   0.0950
  -0.250   0.3084   0.00945   0.00327  -0.0518   0.8688   0.0954
   0.000   0.3376   0.00923   0.00299  -0.0518   0.8389   0.0957
   0.250   0.3640   0.00910   0.00272  -0.0512   0.7945   0.0959
   0.500   0.3855   0.00916   0.00252  -0.0495   0.7248   0.0962
   0.750   0.4029   0.00940   0.00243  -0.0470   0.6512   0.0967
   1.000   0.4229   0.00958   0.00241  -0.0453   0.6041   0.0977
   1.250   0.4443   0.00972   0.00240  -0.0438   0.5653   0.0985
   1.500   0.4663   0.00980   0.00237  -0.0425   0.5291   0.0989
   1.750   0.4888   0.00989   0.00237  -0.0414   0.4985   0.0995
   2.000   0.5084   0.00995   0.00223  -0.0397   0.4468   0.1016
   2.250   0.5293   0.01015   0.00224  -0.0383   0.4018   0.1036
   2.500   0.5523   0.01028   0.00227  -0.0374   0.3700   0.1056
   2.750   0.5747   0.01049   0.00231  -0.0363   0.3262   0.1080
   3.000   0.5954   0.01089   0.00242  -0.0350   0.2585   0.1097
   3.250   0.6137   0.01158   0.00266  -0.0334   0.1670   0.1112
   3.500   0.6344   0.01210   0.00293  -0.0321   0.1120   0.1127
   3.750   0.6519   0.01296   0.00341  -0.0303   0.0222   0.1160
   4.000   0.6758   0.01318   0.00373  -0.0294   0.0183   0.1205
   4.250   0.6993   0.01348   0.00416  -0.0284   0.0157   0.1272
   4.500   0.8810   0.01405   0.00690  -0.0645   0.0140   1.0000
   4.750   0.9033   0.01459   0.00749  -0.0633   0.0148   1.0000
   5.000   0.9265   0.01505   0.00806  -0.0621   0.0163   1.0000
   5.250   0.9458   0.01595   0.00904  -0.0603   0.0159   1.0000
   5.500   0.9660   0.01683   0.01004  -0.0585   0.0169   1.0000
   5.750   0.9851   0.01804   0.01138  -0.0563   0.0192   1.0000
   6.000   1.0034   0.01966   0.01308  -0.0541   0.0197   1.0000
   6.250   1.0236   0.02101   0.01453  -0.0525   0.0184   1.0000
   6.500   1.0429   0.02256   0.01619  -0.0509   0.0167   1.0000
   6.750   1.0619   0.02438   0.01806  -0.0494   0.0155   1.0000
   7.000   1.0798   0.02674   0.02051  -0.0479   0.0144   1.0000
   7.250   1.0871   0.03374   0.02794  -0.0452   0.0130   1.0000
   7.500   1.0995   0.03573   0.03021  -0.0427   0.0129   1.0000
   7.750   1.1115   0.03704   0.03179  -0.0401   0.0128   1.0000
   8.000   1.1272   0.03683   0.03180  -0.0379   0.0120   1.0000
   8.250   1.1391   0.03832   0.03350  -0.0354   0.0112   1.0000
   8.500   1.1466   0.04046   0.03589  -0.0326   0.0106   1.0000
   8.750   1.1506   0.04290   0.03856  -0.0296   0.0102   1.0000
   9.000   1.1511   0.04550   0.04140  -0.0264   0.0099   1.0000
   9.250   1.1486   0.04815   0.04427  -0.0231   0.0098   1.0000
   9.500   1.1418   0.05095   0.04727  -0.0196   0.0096   1.0000
   9.750   1.1271   0.05319   0.04968  -0.0148   0.0095   1.0000
  10.000   1.1110   0.05582   0.05247  -0.0112   0.0095   1.0000
  10.250   1.0938   0.05907   0.05589  -0.0090   0.0095   1.0000
  10.500   1.0769   0.06288   0.05986  -0.0085   0.0095   1.0000
  10.750   1.0580   0.06773   0.06487  -0.0098   0.0094   1.0000
  11.000   1.0388   0.07381   0.07111  -0.0133   0.0095   1.0000
  11.250   1.0196   0.08118   0.07863  -0.0184   0.0096   1.0000
  11.500   0.9999   0.08976   0.08736  -0.0246   0.0099   1.0000
  11.750   0.9779   0.09981   0.09753  -0.0314   0.0101   1.0000
  12.000   0.9533   0.11141   0.10922  -0.0384   0.0105   1.0000
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