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Coanda 2 (coanda2-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Coanda 2 (coanda2-il)
Reynolds number: 50,000
Max Cl/Cd: 37.05 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-coanda2-il-50000-n5.txt
Download as CSV file: xf-coanda2-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4231   0.09627   0.08955  -0.0184   1.0000   0.0387
  -8.250  -0.4259   0.09323   0.08661  -0.0190   1.0000   0.0378
  -8.000  -0.4309   0.08996   0.08345  -0.0196   1.0000   0.0370
  -7.750  -0.4356   0.08577   0.07940  -0.0229   1.0000   0.0355
  -7.500  -0.4329   0.08230   0.07592  -0.0236   1.0000   0.0353
  -7.250  -0.4296   0.07871   0.07238  -0.0245   1.0000   0.0351
  -7.000  -0.4253   0.07506   0.06876  -0.0255   1.0000   0.0349
  -6.750  -0.4204   0.07111   0.06481  -0.0266   1.0000   0.0347
  -6.500  -0.4140   0.06714   0.06082  -0.0277   1.0000   0.0346
  -6.250  -0.4063   0.06304   0.05668  -0.0286   1.0000   0.0346
  -6.000  -0.3974   0.05875   0.05229  -0.0294   1.0000   0.0346
  -5.750  -0.3872   0.05442   0.04783  -0.0298   1.0000   0.0348
  -5.500  -0.3760   0.04975   0.04294  -0.0301   1.0000   0.0354
  -5.250  -0.3618   0.04813   0.04125  -0.0290   1.0000   0.0387
  -5.000  -0.3478   0.04451   0.03736  -0.0283   1.0000   0.0412
  -4.750  -0.3335   0.04006   0.03250  -0.0274   1.0000   0.0435
  -4.500  -0.3174   0.03789   0.03012  -0.0259   1.0000   0.0470
  -4.250  -0.3002   0.03464   0.02639  -0.0242   1.0000   0.0534
  -4.000  -0.2808   0.03182   0.02285  -0.0223   1.0000   0.0703
  -3.750  -0.2629   0.03124   0.02169  -0.0203   1.0000   0.0962
  -3.500  -0.2487   0.03138   0.02192  -0.0189   1.0000   0.1294
  -3.250  -0.2294   0.03031   0.02038  -0.0174   1.0000   0.1401
  -3.000  -0.2085   0.02917   0.01890  -0.0161   1.0000   0.1419
  -2.750  -0.1874   0.02825   0.01767  -0.0149   1.0000   0.1448
  -2.500  -0.1651   0.02734   0.01638  -0.0138   1.0000   0.1450
  -2.250  -0.1422   0.02653   0.01525  -0.0129   1.0000   0.1442
  -2.000  -0.1187   0.02581   0.01423  -0.0121   1.0000   0.1437
  -1.750  -0.0948   0.02518   0.01334  -0.0114   1.0000   0.1434
  -1.500  -0.0710   0.02465   0.01255  -0.0108   1.0000   0.1434
  -1.250  -0.0462   0.02417   0.01190  -0.0104   1.0000   0.1439
  -1.000  -0.0188   0.02380   0.01134  -0.0105   1.0000   0.1447
  -0.750   0.0110   0.02350   0.01087  -0.0112   0.9997   0.1457
  -0.500   0.0625   0.02331   0.01048  -0.0164   0.9886   0.1505
  -0.250   0.1130   0.02302   0.01019  -0.0214   0.9771   0.1565
   0.000   0.1604   0.02272   0.00986  -0.0256   0.9633   0.1597
   0.250   0.2063   0.02243   0.00958  -0.0294   0.9479   0.1621
   0.500   0.2520   0.02213   0.00932  -0.0331   0.9314   0.1651
   0.750   0.2989   0.02177   0.00906  -0.0368   0.9143   0.1693
   1.000   0.3422   0.02138   0.00882  -0.0397   0.8942   0.1757
   1.250   0.3878   0.02093   0.00859  -0.0429   0.8731   0.1861
   1.500   0.4308   0.02045   0.00841  -0.0455   0.8475   0.2080
   1.750   0.5239   0.01836   0.00834  -0.0589   0.8183   1.0000
   2.000   0.5622   0.01820   0.00816  -0.0600   0.7772   1.0000
   2.250   0.6014   0.01808   0.00796  -0.0611   0.7304   1.0000
   2.500   0.6366   0.01813   0.00792  -0.0615   0.6815   1.0000
   2.750   0.6666   0.01842   0.00802  -0.0611   0.6368   1.0000
   3.000   0.6927   0.01886   0.00833  -0.0602   0.5981   1.0000
   3.250   0.7168   0.01935   0.00883  -0.0591   0.5634   1.0000
   3.500   0.7370   0.01989   0.00919  -0.0571   0.5157   1.0000
   3.750   0.7492   0.02059   0.00933  -0.0537   0.4317   1.0000
   4.000   0.7702   0.02117   0.00986  -0.0523   0.3928   1.0000
   4.250   0.7900   0.02180   0.01040  -0.0507   0.3451   1.0000
   4.500   0.8117   0.02238   0.01110  -0.0494   0.3062   1.0000
   4.750   0.8312   0.02318   0.01169  -0.0480   0.2424   1.0000
   5.000   0.8519   0.02412   0.01244  -0.0467   0.1806   1.0000
   5.500   0.8870   0.02815   0.01548  -0.0443   0.0331   1.0000
   5.750   0.9060   0.02962   0.01715  -0.0427   0.0306   1.0000
   6.000   0.9238   0.03108   0.01888  -0.0411   0.0285   1.0000
   6.250   0.9390   0.03274   0.02078  -0.0392   0.0264   1.0000
   6.500   0.9508   0.03469   0.02307  -0.0370   0.0249   1.0000
   6.750   0.9613   0.03670   0.02526  -0.0346   0.0242   1.0000
   7.000   0.9730   0.03857   0.02738  -0.0322   0.0240   1.0000
   7.250   0.9852   0.04053   0.02957  -0.0299   0.0239   1.0000
   7.500   0.9988   0.04261   0.03187  -0.0278   0.0238   1.0000
   7.750   1.0139   0.04491   0.03442  -0.0258   0.0238   1.0000
   8.000   1.0298   0.04757   0.03736  -0.0241   0.0238   1.0000
   8.250   1.0439   0.05036   0.04044  -0.0223   0.0238   1.0000
   8.500   1.0542   0.05344   0.04388  -0.0204   0.0238   1.0000
   8.750   1.0602   0.05658   0.04738  -0.0183   0.0237   1.0000
   9.000   1.0607   0.05993   0.05111  -0.0160   0.0236   1.0000
   9.250   1.0582   0.06325   0.05474  -0.0138   0.0237   1.0000
   9.500   1.0470   0.06662   0.05842  -0.0111   0.0235   1.0000
   9.750   1.0363   0.07016   0.06218  -0.0092   0.0237   1.0000
  10.000   1.0223   0.07396   0.06622  -0.0083   0.0237   1.0000
  10.250   1.0075   0.07834   0.07080  -0.0087   0.0237   1.0000
  10.500   0.9941   0.08319   0.07581  -0.0101   0.0239   1.0000
  10.750   0.9793   0.08876   0.08152  -0.0127   0.0240   1.0000
  11.000   0.9665   0.09467   0.08754  -0.0158   0.0242   1.0000
  11.250   0.9497   0.10193   0.09501  -0.0208   0.0246   1.0000
  11.500   0.9233   0.11330   0.10661  -0.0295   0.0258   1.0000
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