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S6063 7.05% (s6063-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S6063 7.05% (s6063-il)
Reynolds number: 100,000
Max Cl/Cd: 48.6 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s6063-il-100000.txt
Download as CSV file: xf-s6063-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6063 7.05%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5449   0.10606   0.10120   0.0006   1.0000   0.0855
  -8.750  -0.5598   0.10357   0.09884  -0.0064   1.0000   0.0871
  -8.500  -0.5731   0.10038   0.09575  -0.0133   1.0000   0.0874
  -8.250  -0.5350   0.09449   0.08975  -0.0036   1.0000   0.0922
  -8.000  -0.5320   0.09110   0.08641  -0.0051   1.0000   0.0958
  -7.750  -0.5426   0.08773   0.08315  -0.0107   1.0000   0.0995
  -7.500  -0.5544   0.08239   0.07780  -0.0229   1.0000   0.1014
  -7.250  -0.5330   0.07918   0.07464  -0.0145   1.0000   0.1049
  -7.000  -0.5263   0.07539   0.07085  -0.0171   1.0000   0.1102
  -6.750  -0.5264   0.06989   0.06528  -0.0250   1.0000   0.1163
  -6.500  -0.5125   0.06690   0.06234  -0.0229   1.0000   0.1213
  -6.250  -0.5059   0.06210   0.05740  -0.0281   1.0000   0.1305
  -6.000  -0.4918   0.05892   0.05422  -0.0279   1.0000   0.1381
  -5.750  -0.4797   0.05503   0.05026  -0.0292   1.0000   0.1473
  -5.500  -0.4661   0.05154   0.04668  -0.0302   1.0000   0.1606
  -5.250  -0.4514   0.04866   0.04375  -0.0300   1.0000   0.1774
  -5.000  -0.4127   0.03389   0.02681  -0.0358   1.0000   0.0598
  -4.750  -0.3925   0.03046   0.02305  -0.0351   1.0000   0.0585
  -4.500  -0.3709   0.02745   0.01963  -0.0341   1.0000   0.0568
  -4.250  -0.3477   0.02456   0.01625  -0.0328   1.0000   0.0537
  -4.000  -0.3236   0.02219   0.01340  -0.0314   1.0000   0.0521
  -3.750  -0.2997   0.02032   0.01127  -0.0301   1.0000   0.0524
  -3.500  -0.2765   0.01878   0.00962  -0.0288   1.0000   0.0542
  -3.250  -0.2538   0.01748   0.00825  -0.0275   1.0000   0.0577
  -3.000  -0.2322   0.01624   0.00705  -0.0262   1.0000   0.0657
  -2.750  -0.2105   0.01503   0.00595  -0.0249   1.0000   0.0910
  -2.500  -0.1954   0.01181   0.00508  -0.0232   1.0000   0.5252
  -2.250  -0.1847   0.01083   0.00532  -0.0167   1.0000   0.8794
  -2.000  -0.1137   0.01068   0.00472  -0.0246   1.0000   1.0000
  -1.750  -0.0986   0.01068   0.00448  -0.0229   1.0000   1.0000
  -1.500  -0.0812   0.01073   0.00430  -0.0215   1.0000   1.0000
  -1.250  -0.0625   0.01081   0.00418  -0.0203   1.0000   1.0000
  -1.000  -0.0431   0.01092   0.00408  -0.0193   1.0000   1.0000
  -0.750  -0.0233   0.01106   0.00407  -0.0184   1.0000   1.0000
  -0.500  -0.0034   0.01123   0.00411  -0.0176   1.0000   1.0000
  -0.250   0.0166   0.01143   0.00420  -0.0169   1.0000   1.0000
   0.000   0.0365   0.01168   0.00434  -0.0162   1.0000   1.0000
   0.250   0.0562   0.01196   0.00454  -0.0156   1.0000   1.0000
   0.500   0.0925   0.01236   0.00488  -0.0183   0.9940   1.0000
   0.750   0.1458   0.01278   0.00527  -0.0241   0.9809   1.0000
   1.000   0.1988   0.01310   0.00560  -0.0295   0.9670   1.0000
   1.250   0.2514   0.01331   0.00585  -0.0347   0.9525   1.0000
   1.500   0.3050   0.01340   0.00603  -0.0398   0.9376   1.0000
   1.750   0.3563   0.01337   0.00612  -0.0441   0.9218   1.0000
   2.000   0.4021   0.01328   0.00614  -0.0470   0.9044   1.0000
   2.250   0.4390   0.01318   0.00614  -0.0478   0.8843   1.0000
   2.500   0.4695   0.01306   0.00616  -0.0472   0.8618   1.0000
   2.750   0.4950   0.01299   0.00616  -0.0455   0.8368   1.0000
   3.000   0.5189   0.01291   0.00615  -0.0435   0.8103   1.0000
   3.250   0.5419   0.01286   0.00614  -0.0412   0.7813   1.0000
   3.500   0.5646   0.01282   0.00618  -0.0389   0.7496   1.0000
   3.750   0.5871   0.01285   0.00624  -0.0368   0.7126   1.0000
   4.000   0.6097   0.01293   0.00633  -0.0347   0.6718   1.0000
   4.250   0.6304   0.01304   0.00629  -0.0321   0.6113   1.0000
   4.500   0.6493   0.01336   0.00626  -0.0294   0.5234   1.0000
   4.750   0.6684   0.01400   0.00653  -0.0274   0.4197   1.0000
   5.000   0.6853   0.01527   0.00704  -0.0257   0.2630   1.0000
   5.250   0.6961   0.01868   0.00901  -0.0235   0.0747   1.0000
   5.500   0.7162   0.02027   0.01051  -0.0223   0.0598   1.0000
   5.750   0.7382   0.02170   0.01204  -0.0210   0.0543   1.0000
   6.000   0.7612   0.02335   0.01375  -0.0199   0.0509   1.0000
   6.250   0.7854   0.02534   0.01575  -0.0190   0.0490   1.0000
   6.500   0.8109   0.02789   0.01841  -0.0182   0.0481   1.0000
   6.750   0.8363   0.03054   0.02133  -0.0174   0.0481   1.0000
   7.000   0.8607   0.03314   0.02441  -0.0162   0.0491   1.0000
   7.250   0.8815   0.03651   0.02842  -0.0147   0.0504   1.0000
   7.500   0.8985   0.04018   0.03270  -0.0133   0.0510   1.0000
   7.750   0.9110   0.04460   0.03775  -0.0118   0.0525   1.0000
   8.000   0.9205   0.04982   0.04343  -0.0107   0.0562   1.0000
   8.250   0.8659   0.04638   0.04125  -0.0064   0.0662   1.0000
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