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S2062 8% (s2062-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S2062 8% (s2062-il)
Reynolds number: 200,000
Max Cl/Cd: 69.74 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2062-il-200000.txt
Download as CSV file: xf-s2062-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2062 8%                                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5030   0.08471   0.08129  -0.0327   1.0000   0.0522
  -8.250  -0.5140   0.07948   0.07611  -0.0390   1.0000   0.0524
  -8.000  -0.5214   0.07461   0.07115  -0.0431   1.0000   0.0525
  -7.750  -0.5287   0.06795   0.06454  -0.0440   1.0000   0.0534
  -7.500  -0.5211   0.06529   0.06193  -0.0419   1.0000   0.0544
  -7.250  -0.5163   0.06251   0.05916  -0.0411   1.0000   0.0555
  -7.000  -0.5130   0.05910   0.05571  -0.0413   1.0000   0.0566
  -6.750  -0.5099   0.05537   0.05190  -0.0417   1.0000   0.0582
  -6.500  -0.5062   0.05137   0.04776  -0.0420   1.0000   0.0603
  -6.250  -0.5183   0.03406   0.02892  -0.0425   1.0000   0.0308
  -6.000  -0.5040   0.03075   0.02541  -0.0411   1.0000   0.0284
  -5.750  -0.4898   0.02676   0.02091  -0.0398   1.0000   0.0271
  -5.500  -0.4717   0.02353   0.01715  -0.0384   1.0000   0.0262
  -5.250  -0.4511   0.02110   0.01429  -0.0371   1.0000   0.0262
  -5.000  -0.4292   0.01925   0.01213  -0.0359   1.0000   0.0267
  -4.750  -0.4068   0.01797   0.01062  -0.0348   1.0000   0.0286
  -4.500  -0.3844   0.01650   0.00900  -0.0339   1.0000   0.0318
  -4.250  -0.3619   0.01549   0.00796  -0.0330   1.0000   0.0355
  -4.000  -0.3383   0.01440   0.00676  -0.0321   1.0000   0.0424
  -3.750  -0.3146   0.01340   0.00589  -0.0315   1.0000   0.0718
  -3.500  -0.2916   0.01300   0.00552  -0.0309   1.0000   0.1045
  -3.250  -0.2689   0.01263   0.00531  -0.0304   1.0000   0.1377
  -3.000  -0.2460   0.01222   0.00502  -0.0298   1.0000   0.1754
  -2.750  -0.2232   0.01176   0.00478  -0.0294   1.0000   0.2283
  -2.500  -0.1993   0.01131   0.00467  -0.0292   0.9996   0.3079
  -2.250  -0.1613   0.01079   0.00468  -0.0319   0.9950   0.4467
  -2.000  -0.1280   0.01018   0.00478  -0.0332   0.9896   0.6223
  -1.750  -0.0955   0.00995   0.00505  -0.0335   0.9841   0.7786
  -1.500  -0.0666   0.00986   0.00514  -0.0329   0.9766   0.8721
  -1.250  -0.0161   0.00981   0.00511  -0.0369   0.9738   0.9606
  -1.000   0.0396   0.00983   0.00498  -0.0428   0.9710   1.0000
  -0.750   0.0779   0.00983   0.00488  -0.0452   0.9628   1.0000
  -0.500   0.1244   0.00982   0.00477  -0.0491   0.9576   1.0000
  -0.250   0.1630   0.00978   0.00466  -0.0513   0.9491   1.0000
   0.000   0.2107   0.00968   0.00452  -0.0553   0.9441   1.0000
   0.250   0.2507   0.00956   0.00437  -0.0577   0.9355   1.0000
   0.500   0.2956   0.00936   0.00416  -0.0609   0.9292   1.0000
   0.750   0.3292   0.00922   0.00400  -0.0617   0.9180   1.0000
   1.250   0.3925   0.00894   0.00373  -0.0624   0.8936   1.0000
   1.500   0.4207   0.00883   0.00361  -0.0620   0.8792   1.0000
   1.750   0.4475   0.00875   0.00352  -0.0612   0.8632   1.0000
   2.000   0.4738   0.00869   0.00346  -0.0604   0.8459   1.0000
   2.250   0.4991   0.00866   0.00343  -0.0593   0.8260   1.0000
   2.500   0.5243   0.00866   0.00340  -0.0583   0.8037   1.0000
   2.750   0.5492   0.00869   0.00340  -0.0572   0.7781   1.0000
   3.000   0.5740   0.00876   0.00342  -0.0561   0.7496   1.0000
   3.250   0.5986   0.00887   0.00348  -0.0550   0.7177   1.0000
   3.500   0.6228   0.00904   0.00357  -0.0538   0.6809   1.0000
   3.750   0.6465   0.00927   0.00368  -0.0527   0.6391   1.0000
   4.000   0.6694   0.00960   0.00383  -0.0514   0.5907   1.0000
   4.250   0.6909   0.01003   0.00404  -0.0499   0.5278   1.0000
   4.500   0.7113   0.01058   0.00429  -0.0484   0.4565   1.0000
   4.750   0.7318   0.01122   0.00461  -0.0471   0.3850   1.0000
   5.000   0.7526   0.01190   0.00500  -0.0460   0.3168   1.0000
   5.250   0.7731   0.01268   0.00547  -0.0450   0.2443   1.0000
   5.500   0.7932   0.01362   0.00602  -0.0440   0.1665   1.0000
   5.750   0.8079   0.01556   0.00722  -0.0422   0.0575   1.0000
   6.000   0.8282   0.01673   0.00838  -0.0408   0.0441   1.0000
   6.250   0.8462   0.01820   0.00986  -0.0391   0.0394   1.0000
   6.500   0.8684   0.01913   0.01090  -0.0381   0.0366   1.0000
   6.750   0.8902   0.02016   0.01203  -0.0371   0.0337   1.0000
   7.000   0.9116   0.02150   0.01342  -0.0360   0.0320   1.0000
   7.250   0.9334   0.02322   0.01519  -0.0350   0.0308   1.0000
   7.500   0.9564   0.02558   0.01767  -0.0341   0.0300   1.0000
   7.750   0.9796   0.02832   0.02064  -0.0333   0.0297   1.0000
   8.000   0.9997   0.03195   0.02462  -0.0322   0.0293   1.0000
   8.250   1.0182   0.03343   0.02646  -0.0307   0.0283   1.0000
   8.500   1.0337   0.03647   0.02994  -0.0291   0.0282   1.0000
   8.750   1.0438   0.04102   0.03491  -0.0272   0.0287   1.0000
   9.000   1.0592   0.04419   0.03834  -0.0257   0.0298   1.0000
  14.000   0.7118   0.16216   0.15923  -0.0563   0.0509   1.0000
  14.250   0.7048   0.16611   0.16317  -0.0601   0.0506   1.0000
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