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S2060 8% (s2060-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S2060 8% (s2060-il)
Reynolds number: 100,000
Max Cl/Cd: 53.62 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2060-il-100000.txt
Download as CSV file: xf-s2060-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2060 8%                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4857   0.11096   0.10579  -0.0158   1.0000   0.0925
  -9.500  -0.5024   0.10868   0.10364  -0.0216   1.0000   0.0946
  -9.250  -0.5166   0.10581   0.10088  -0.0266   1.0000   0.0950
  -9.000  -0.4806   0.09973   0.09468  -0.0195   1.0000   0.0990
  -8.750  -0.4761   0.09647   0.09145  -0.0200   1.0000   0.1029
  -8.500  -0.4870   0.09337   0.08845  -0.0238   1.0000   0.1074
  -8.250  -0.5117   0.09051   0.08578  -0.0303   1.0000   0.1085
  -8.000  -0.5046   0.08575   0.08106  -0.0288   1.0000   0.1102
  -7.750  -0.4851   0.08264   0.07790  -0.0248   1.0000   0.1146
  -7.500  -0.4079   0.06753   0.06312  -0.0269   1.0000   0.1286
  -7.250  -0.5173   0.07377   0.06907  -0.0393   1.0000   0.1233
  -7.000  -0.4987   0.07045   0.06586  -0.0335   1.0000   0.1259
  -6.750  -0.4927   0.06727   0.06269  -0.0330   1.0000   0.1304
  -6.500  -0.4984   0.06232   0.05762  -0.0379   1.0000   0.1387
  -6.250  -0.4976   0.04482   0.03911  -0.0453   1.0000   0.0658
  -6.000  -0.4871   0.03994   0.03391  -0.0449   1.0000   0.0629
  -5.750  -0.4733   0.03565   0.02910  -0.0444   1.0000   0.0636
  -5.500  -0.4561   0.03190   0.02468  -0.0435   1.0000   0.0658
  -5.250  -0.4359   0.02858   0.02060  -0.0425   1.0000   0.0676
  -5.000  -0.4162   0.02605   0.01799  -0.0417   1.0000   0.0742
  -4.750  -0.3936   0.02389   0.01527  -0.0407   1.0000   0.0831
  -4.500  -0.3713   0.02278   0.01389  -0.0397   1.0000   0.0947
  -4.250  -0.3489   0.02127   0.01235  -0.0390   1.0000   0.1062
  -4.000  -0.3255   0.01986   0.01082  -0.0381   1.0000   0.1161
  -3.750  -0.3024   0.01886   0.00976  -0.0373   1.0000   0.1294
  -3.500  -0.2789   0.01784   0.00871  -0.0365   1.0000   0.1427
  -3.250  -0.2555   0.01705   0.00794  -0.0357   1.0000   0.1621
  -3.000  -0.2323   0.01621   0.00725  -0.0350   1.0000   0.1880
  -2.750  -0.2092   0.01536   0.00663  -0.0343   1.0000   0.2311
  -2.500  -0.1866   0.01429   0.00617  -0.0338   1.0000   0.3271
  -2.250  -0.1687   0.01300   0.00613  -0.0319   1.0000   0.5710
  -2.000  -0.1577   0.01256   0.00632  -0.0273   1.0000   0.7635
  -1.750  -0.1395   0.01231   0.00633  -0.0237   1.0000   0.9184
  -1.500  -0.1029   0.01223   0.00599  -0.0262   1.0000   1.0000
  -1.250  -0.0806   0.01236   0.00589  -0.0259   1.0000   1.0000
  -1.000  -0.0584   0.01253   0.00587  -0.0256   1.0000   1.0000
  -0.750  -0.0365   0.01274   0.00590  -0.0253   1.0000   1.0000
  -0.500  -0.0148   0.01298   0.00599  -0.0249   1.0000   1.0000
  -0.250   0.0066   0.01325   0.00615  -0.0246   1.0000   1.0000
   0.000   0.0276   0.01357   0.00637  -0.0243   1.0000   1.0000
   0.250   0.0661   0.01409   0.00677  -0.0273   0.9940   1.0000
   0.500   0.1168   0.01465   0.00726  -0.0325   0.9835   1.0000
   0.750   0.1652   0.01506   0.00763  -0.0371   0.9716   1.0000
   1.000   0.2124   0.01538   0.00792  -0.0413   0.9589   1.0000
   1.250   0.2592   0.01560   0.00815  -0.0453   0.9458   1.0000
   1.500   0.3062   0.01572   0.00831  -0.0491   0.9323   1.0000
   1.750   0.3538   0.01573   0.00839  -0.0527   0.9186   1.0000
   2.000   0.4024   0.01561   0.00835  -0.0563   0.9048   1.0000
   2.250   0.4508   0.01537   0.00824  -0.0596   0.8908   1.0000
   2.500   0.4951   0.01504   0.00802  -0.0618   0.8754   1.0000
   2.750   0.5365   0.01464   0.00774  -0.0632   0.8586   1.0000
   3.000   0.5696   0.01433   0.00757  -0.0629   0.8375   1.0000
   3.250   0.6027   0.01397   0.00730  -0.0624   0.8152   1.0000
   3.500   0.6306   0.01373   0.00713  -0.0611   0.7876   1.0000
   3.750   0.6577   0.01354   0.00696  -0.0595   0.7564   1.0000
   4.000   0.6823   0.01347   0.00694  -0.0577   0.7184   1.0000
   4.250   0.7067   0.01350   0.00694  -0.0559   0.6756   1.0000
   4.500   0.7300   0.01368   0.00701  -0.0540   0.6265   1.0000
   4.750   0.7517   0.01402   0.00719  -0.0520   0.5697   1.0000
   5.000   0.7719   0.01451   0.00750  -0.0500   0.5063   1.0000
   5.250   0.7903   0.01516   0.00784  -0.0478   0.4336   1.0000
   5.500   0.8068   0.01600   0.00826  -0.0457   0.3487   1.0000
   5.750   0.8230   0.01705   0.00885  -0.0439   0.2601   1.0000
   6.000   0.8365   0.01880   0.00990  -0.0420   0.1506   1.0000
   6.250   0.8480   0.02142   0.01195  -0.0393   0.0874   1.0000
   6.500   0.8667   0.02315   0.01360  -0.0376   0.0730   1.0000
   6.750   0.8875   0.02490   0.01529  -0.0364   0.0645   1.0000
   7.000   0.9116   0.02665   0.01712  -0.0354   0.0597   1.0000
   7.250   0.9367   0.02884   0.01932  -0.0348   0.0567   1.0000
   7.500   0.9631   0.03222   0.02280  -0.0344   0.0549   1.0000
   7.750   0.9861   0.03482   0.02585  -0.0333   0.0542   1.0000
   8.000   1.0053   0.03736   0.02889  -0.0317   0.0529   1.0000
   8.250   1.0215   0.04021   0.03225  -0.0300   0.0514   1.0000
   8.500   1.0344   0.04399   0.03653  -0.0282   0.0518   1.0000
   8.750   1.0435   0.04822   0.04121  -0.0263   0.0527   1.0000
   9.000   1.0497   0.05298   0.04633  -0.0246   0.0539   1.0000
   9.250   1.0604   0.05733   0.05097  -0.0232   0.0560   1.0000
   9.500   1.0251   0.06447   0.05915  -0.0192   0.0627   1.0000
   9.750   1.0139   0.07060   0.06560  -0.0178   0.0700   1.0000
  10.000   0.9689   0.07648   0.07180  -0.0166   0.0728   1.0000
  10.250   0.8795   0.07120   0.06675  -0.0114   0.0638   1.0000
  10.500   0.8487   0.07801   0.07366  -0.0141   0.0643   1.0000
  10.750   0.8254   0.08549   0.08121  -0.0175   0.0654   1.0000
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