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Coanda 2 (coanda2-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Coanda 2 (coanda2-il)
Reynolds number: 200,000
Max Cl/Cd: 64.09 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-coanda2-il-200000.txt
Download as CSV file: xf-coanda2-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4287   0.09760   0.09421  -0.0187   1.0000   0.0497
  -8.500  -0.4410   0.09602   0.09271  -0.0203   1.0000   0.0500
  -8.250  -0.4455   0.09357   0.09031  -0.0230   1.0000   0.0502
  -8.000  -0.4444   0.09034   0.08710  -0.0259   1.0000   0.0503
  -7.750  -0.4436   0.08545   0.08226  -0.0258   1.0000   0.0506
  -7.500  -0.4402   0.08127   0.07810  -0.0234   1.0000   0.0510
  -7.250  -0.4364   0.07776   0.07462  -0.0222   1.0000   0.0514
  -7.000  -0.4327   0.07445   0.07131  -0.0218   1.0000   0.0517
  -6.750  -0.4285   0.07112   0.06796  -0.0219   1.0000   0.0520
  -6.500  -0.4237   0.06744   0.06426  -0.0226   1.0000   0.0521
  -6.250  -0.4203   0.05987   0.05658  -0.0257   1.0000   0.0394
  -6.000  -0.4179   0.05100   0.04754  -0.0270   1.0000   0.0303
  -5.750  -0.4129   0.04683   0.04324  -0.0259   1.0000   0.0290
  -5.500  -0.4054   0.04176   0.03796  -0.0250   1.0000   0.0280
  -5.250  -0.4010   0.03437   0.03014  -0.0232   1.0000   0.0264
  -5.000  -0.4093   0.02100   0.01519  -0.0177   1.0000   0.0243
  -4.750  -0.3919   0.01890   0.01260  -0.0153   1.0000   0.0249
  -4.500  -0.3725   0.01767   0.01106  -0.0135   1.0000   0.0281
  -4.250  -0.3517   0.01653   0.00958  -0.0116   1.0000   0.0297
  -4.000  -0.3302   0.01581   0.00862  -0.0099   1.0000   0.0319
  -3.750  -0.3084   0.01567   0.00860  -0.0083   1.0000   0.0392
  -3.500  -0.2861   0.01689   0.00984  -0.0068   1.0000   0.0620
  -3.250  -0.2660   0.01942   0.01255  -0.0054   1.0000   0.0761
  -3.000  -0.2459   0.02067   0.01370  -0.0041   0.9999   0.0875
  -2.750  -0.2051   0.02161   0.01496  -0.0082   0.9942   0.1062
  -1.750  -0.0499   0.02024   0.01304  -0.0185   0.9698   0.1523
  -1.500  -0.0141   0.01922   0.01169  -0.0195   0.9621   0.1397
  -1.250   0.0294   0.01787   0.01031  -0.0226   0.9572   0.1352
  -1.000   0.0667   0.01697   0.00924  -0.0241   0.9492   0.1305
  -0.750   0.1125   0.01626   0.00837  -0.0274   0.9436   0.1282
  -0.500   0.1500   0.01562   0.00770  -0.0290   0.9345   0.1279
  -0.250   0.1986   0.01490   0.00699  -0.0330   0.9293   0.1279
   0.000   0.2367   0.01426   0.00637  -0.0346   0.9189   0.1283
   0.250   0.2797   0.01356   0.00576  -0.0373   0.9097   0.1295
   0.500   0.3274   0.01287   0.00518  -0.0410   0.9000   0.1327
   0.750   0.3645   0.01231   0.00470  -0.0424   0.8818   0.1338
   1.000   0.4062   0.01175   0.00420  -0.0447   0.8584   0.1348
   1.250   0.4418   0.01135   0.00382  -0.0457   0.8223   0.1367
   1.500   0.4771   0.01109   0.00347  -0.0466   0.7676   0.1388
   1.750   0.5061   0.01104   0.00321  -0.0463   0.6971   0.1420
   2.000   0.5289   0.01128   0.00316  -0.0449   0.6397   0.1460
   2.250   0.5508   0.01156   0.00323  -0.0435   0.5969   0.1505
   2.500   0.5718   0.01183   0.00333  -0.0419   0.5538   0.1566
   2.750   0.5905   0.01211   0.00340  -0.0399   0.4957   0.1698
   3.000   0.7390   0.01153   0.00409  -0.0684   0.3814   1.0000
   3.250   0.7605   0.01194   0.00426  -0.0672   0.3317   1.0000
   3.500   0.7812   0.01248   0.00445  -0.0659   0.2632   1.0000
   3.750   0.8023   0.01308   0.00475  -0.0647   0.2043   1.0000
   4.000   0.8239   0.01371   0.00514  -0.0635   0.1565   1.0000
   4.250   0.8390   0.01522   0.00594  -0.0614   0.0382   1.0000
   4.500   0.8601   0.01599   0.00667  -0.0600   0.0261   1.0000
   4.750   0.8827   0.01657   0.00739  -0.0588   0.0245   1.0000
   5.000   0.9050   0.01720   0.00818  -0.0575   0.0238   1.0000
   5.250   0.9266   0.01792   0.00912  -0.0561   0.0236   1.0000
   5.500   0.9467   0.01878   0.01016  -0.0544   0.0236   1.0000
   5.750   0.9657   0.01974   0.01126  -0.0525   0.0241   1.0000
   6.000   0.9831   0.02091   0.01255  -0.0503   0.0248   1.0000
   6.250   1.0002   0.02234   0.01406  -0.0480   0.0259   1.0000
   6.500   1.0185   0.02393   0.01573  -0.0460   0.0260   1.0000
   6.750   1.0380   0.02557   0.01745  -0.0444   0.0251   1.0000
   7.000   1.0599   0.02788   0.01995  -0.0428   0.0269   1.0000
   7.250   1.0834   0.03205   0.02426  -0.0417   0.0295   1.0000
   7.500   1.1059   0.03393   0.02684  -0.0388   0.0360   1.0000
   7.750   1.1243   0.03848   0.03212  -0.0355   0.0472   1.0000
  14.000   0.8998   0.18048   0.17701  -0.0572   0.0506   1.0000
  14.250   0.8953   0.18577   0.18226  -0.0624   0.0498   1.0000
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