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S6061 9% (s6061-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S6061 9% (s6061-il)
Reynolds number: 50,000
Max Cl/Cd: 35.89 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s6061-il-50000-n5.txt
Download as CSV file: xf-s6061-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6061 9%                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4950   0.09452   0.08767  -0.0199   1.0000   0.0405
  -8.750  -0.4950   0.09010   0.08334  -0.0222   1.0000   0.0398
  -8.500  -0.4965   0.08550   0.07880  -0.0250   1.0000   0.0391
  -8.250  -0.4999   0.08060   0.07398  -0.0285   1.0000   0.0385
  -8.000  -0.5055   0.07560   0.06905  -0.0322   1.0000   0.0377
  -7.750  -0.5098   0.07047   0.06391  -0.0353   1.0000   0.0370
  -7.500  -0.5135   0.06548   0.05884  -0.0377   1.0000   0.0363
  -7.250  -0.5154   0.06062   0.05384  -0.0393   1.0000   0.0357
  -7.000  -0.5147   0.05591   0.04890  -0.0402   1.0000   0.0352
  -6.750  -0.5109   0.05149   0.04418  -0.0404   1.0000   0.0349
  -6.500  -0.5041   0.04742   0.03975  -0.0400   1.0000   0.0347
  -6.250  -0.4947   0.04376   0.03569  -0.0392   1.0000   0.0347
  -6.000  -0.4828   0.04064   0.03219  -0.0380   1.0000   0.0354
  -5.750  -0.4690   0.03795   0.02914  -0.0367   1.0000   0.0368
  -5.500  -0.4535   0.03540   0.02616  -0.0353   1.0000   0.0392
  -5.250  -0.4361   0.03296   0.02322  -0.0338   1.0000   0.0414
  -5.000  -0.4169   0.03074   0.02052  -0.0322   1.0000   0.0430
  -4.750  -0.3977   0.02860   0.01817  -0.0307   1.0000   0.0448
  -4.500  -0.3788   0.02695   0.01635  -0.0291   1.0000   0.0479
  -4.250  -0.3591   0.02561   0.01476  -0.0275   1.0000   0.0547
  -4.000  -0.3405   0.02438   0.01350  -0.0260   1.0000   0.0647
  -3.750  -0.3211   0.02316   0.01217  -0.0245   1.0000   0.0809
  -3.500  -0.3012   0.02180   0.01100  -0.0235   1.0000   0.1180
  -3.250  -0.2828   0.02036   0.01002  -0.0226   1.0000   0.1947
  -2.750  -0.2527   0.01786   0.00916  -0.0188   1.0000   0.5201
  -2.500  -0.2425   0.01737   0.00931  -0.0141   1.0000   0.6965
  -2.250  -0.2252   0.01728   0.00936  -0.0104   1.0000   0.8326
  -2.000  -0.1556   0.01731   0.00903  -0.0171   0.9995   0.9682
  -1.750  -0.1009   0.01737   0.00859  -0.0233   0.9920   1.0000
  -1.500  -0.0616   0.01752   0.00838  -0.0266   0.9807   1.0000
  -1.250  -0.0213   0.01770   0.00825  -0.0300   0.9702   1.0000
  -1.000   0.0164   0.01786   0.00811  -0.0327   0.9587   1.0000
  -0.750   0.0538   0.01803   0.00806  -0.0352   0.9474   1.0000
  -0.500   0.0917   0.01820   0.00805  -0.0378   0.9363   1.0000
  -0.250   0.1316   0.01836   0.00804  -0.0406   0.9261   1.0000
   0.000   0.1706   0.01851   0.00807  -0.0431   0.9155   1.0000
   0.250   0.2038   0.01867   0.00813  -0.0445   0.9030   1.0000
   0.500   0.2361   0.01883   0.00821  -0.0455   0.8904   1.0000
   0.750   0.2675   0.01898   0.00831  -0.0464   0.8775   1.0000
   1.000   0.2980   0.01913   0.00842  -0.0469   0.8643   1.0000
   1.250   0.3276   0.01926   0.00854  -0.0472   0.8508   1.0000
   1.500   0.3562   0.01940   0.00868  -0.0472   0.8370   1.0000
   1.750   0.3841   0.01953   0.00881  -0.0469   0.8228   1.0000
   2.000   0.4112   0.01965   0.00895  -0.0465   0.8083   1.0000
   2.250   0.4380   0.01976   0.00910  -0.0460   0.7935   1.0000
   2.500   0.4646   0.01987   0.00928  -0.0453   0.7783   1.0000
   2.750   0.4910   0.01996   0.00942  -0.0446   0.7628   1.0000
   3.000   0.5174   0.02002   0.00955  -0.0437   0.7469   1.0000
   3.250   0.5417   0.02015   0.00979  -0.0426   0.7290   1.0000
   3.500   0.5661   0.02027   0.01000  -0.0415   0.7104   1.0000
   3.750   0.5916   0.02033   0.01014  -0.0404   0.6921   1.0000
   4.000   0.6158   0.02045   0.01037  -0.0391   0.6717   1.0000
   4.250   0.6404   0.02054   0.01061  -0.0379   0.6504   1.0000
   4.500   0.6641   0.02069   0.01086  -0.0365   0.6268   1.0000
   4.750   0.6880   0.02082   0.01108  -0.0351   0.6019   1.0000
   5.000   0.7114   0.02098   0.01135  -0.0337   0.5747   1.0000
   5.250   0.7342   0.02121   0.01167  -0.0322   0.5447   1.0000
   5.500   0.7566   0.02148   0.01208  -0.0307   0.5121   1.0000
   5.750   0.7781   0.02182   0.01247  -0.0291   0.4764   1.0000
   6.000   0.7988   0.02226   0.01291  -0.0274   0.4377   1.0000
   6.250   0.8181   0.02283   0.01347  -0.0257   0.3952   1.0000
   6.500   0.8357   0.02357   0.01415  -0.0240   0.3484   1.0000
   6.750   0.8511   0.02452   0.01494  -0.0222   0.2977   1.0000
   7.000   0.8645   0.02571   0.01593  -0.0204   0.2430   1.0000
   7.250   0.8747   0.02726   0.01721  -0.0187   0.1773   1.0000
   7.500   0.8839   0.02920   0.01869  -0.0172   0.1207   1.0000
   7.750   0.8945   0.03132   0.02065  -0.0155   0.0893   1.0000
   8.000   0.9059   0.03337   0.02264  -0.0139   0.0724   1.0000
   8.250   0.9189   0.03526   0.02460  -0.0124   0.0618   1.0000
   8.500   0.9321   0.03724   0.02663  -0.0109   0.0557   1.0000
   8.750   0.9505   0.03928   0.02895  -0.0096   0.0515   1.0000
   9.000   0.9688   0.04146   0.03131  -0.0085   0.0483   1.0000
   9.250   0.9881   0.04406   0.03398  -0.0076   0.0460   1.0000
   9.500   1.0068   0.04705   0.03742  -0.0066   0.0444   1.0000
   9.750   1.0182   0.05010   0.04096  -0.0053   0.0425   1.0000
  10.000   1.0237   0.05315   0.04442  -0.0040   0.0404   1.0000
  10.250   1.0256   0.05620   0.04778  -0.0026   0.0387   1.0000
  10.500   1.0222   0.05930   0.05116  -0.0010   0.0377   1.0000
  10.750   1.0148   0.06286   0.05499   0.0003   0.0373   1.0000
  11.000   1.0036   0.06676   0.05916   0.0009   0.0371   1.0000
  11.250   0.9887   0.07119   0.06384   0.0005   0.0371   1.0000
  11.500   0.9701   0.07642   0.06931  -0.0011   0.0372   1.0000
  11.750   0.9479   0.08271   0.07581  -0.0042   0.0375   1.0000
  12.000   0.9205   0.09083   0.08411  -0.0095   0.0382   1.0000
  12.250   0.8904   0.10125   0.09464  -0.0168   0.0395   1.0000
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