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S8025 (8%) (s8025-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S8025 (8%) (s8025-il)
Reynolds number: 100,000
Max Cl/Cd: 33.64 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8025-il-100000.txt
Download as CSV file: xf-s8025-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8025 (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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.6491   0.08849   0.08396   0.0134   1.0000   0.1176
  -8.000  -0.6538   0.08390   0.07943   0.0106   1.0000   0.1195
  -7.750  -0.7168   0.05944   0.05439  -0.0119   1.0000   0.0612
  -7.500  -0.7076   0.05389   0.04870  -0.0122   1.0000   0.0539
  -7.250  -0.7092   0.04507   0.03883  -0.0132   1.0000   0.0464
  -7.000  -0.6967   0.04016   0.03353  -0.0130   1.0000   0.0452
  -6.750  -0.6811   0.03572   0.02856  -0.0123   1.0000   0.0445
  -6.500  -0.6619   0.03191   0.02415  -0.0114   1.0000   0.0444
  -6.250  -0.6398   0.02872   0.02040  -0.0104   1.0000   0.0454
  -6.000  -0.6164   0.02592   0.01716  -0.0094   1.0000   0.0485
  -5.750  -0.5927   0.02407   0.01527  -0.0088   1.0000   0.0557
  -5.500  -0.5682   0.02177   0.01286  -0.0078   1.0000   0.0644
  -5.250  -0.5441   0.02003   0.01106  -0.0068   1.0000   0.0867
  -5.000  -0.5209   0.01862   0.00976  -0.0060   1.0000   0.1266
  -4.750  -0.4974   0.01757   0.00884  -0.0053   1.0000   0.1658
  -4.500  -0.4737   0.01658   0.00803  -0.0046   1.0000   0.2042
  -4.250  -0.4497   0.01560   0.00723  -0.0038   1.0000   0.2473
  -4.000  -0.4262   0.01469   0.00658  -0.0029   1.0000   0.2999
  -3.750  -0.4029   0.01385   0.00605  -0.0020   1.0000   0.3621
  -3.500  -0.3803   0.01312   0.00563  -0.0008   1.0000   0.4342
  -3.250  -0.3582   0.01251   0.00537   0.0007   1.0000   0.5130
  -3.000  -0.3366   0.01201   0.00518   0.0025   1.0000   0.5909
  -2.750  -0.3153   0.01161   0.00503   0.0046   1.0000   0.6631
  -2.500  -0.2944   0.01128   0.00489   0.0071   1.0000   0.7302
  -2.250  -0.2739   0.01102   0.00479   0.0098   1.0000   0.7945
  -2.000  -0.2505   0.01085   0.00472   0.0122   1.0000   0.8580
  -1.750  -0.2085   0.01082   0.00466   0.0108   1.0000   0.9200
  -1.500  -0.1411   0.01087   0.00450   0.0037   1.0000   0.9672
  -1.250  -0.0632   0.01074   0.00415  -0.0064   1.0000   1.0000
  -1.000  -0.0489   0.01048   0.00385  -0.0050   1.0000   1.0000
  -0.750  -0.0323   0.01032   0.00364  -0.0037   1.0000   1.0000
  -0.500  -0.0145   0.01023   0.00353  -0.0024   1.0000   1.0000
  -0.250   0.0035   0.01021   0.00348  -0.0010   1.0000   1.0000
   0.000   0.0206   0.01024   0.00352   0.0004   1.0000   1.0000
   0.250   0.0355   0.01037   0.00368   0.0019   1.0000   1.0000
   0.500   0.0883   0.01052   0.00390  -0.0039   0.9726   1.0000
   0.750   0.1590   0.01054   0.00394  -0.0120   0.9136   1.0000
   1.000   0.1984   0.01067   0.00392  -0.0132   0.8429   1.0000
   1.250   0.2207   0.01094   0.00395  -0.0110   0.7832   1.0000
   1.500   0.2418   0.01125   0.00405  -0.0088   0.7306   1.0000
   1.750   0.2636   0.01159   0.00416  -0.0070   0.6840   1.0000
   2.000   0.2862   0.01194   0.00429  -0.0054   0.6404   1.0000
   2.250   0.3094   0.01229   0.00444  -0.0041   0.5987   1.0000
   2.500   0.3331   0.01265   0.00464  -0.0029   0.5595   1.0000
   2.750   0.3570   0.01304   0.00483  -0.0018   0.5241   1.0000
   3.000   0.3815   0.01342   0.00509  -0.0009   0.4889   1.0000
   3.250   0.4061   0.01384   0.00536  -0.0001   0.4567   1.0000
   3.500   0.4309   0.01428   0.00569   0.0007   0.4263   1.0000
   3.750   0.4558   0.01474   0.00603   0.0014   0.3972   1.0000
   4.000   0.4808   0.01522   0.00642   0.0021   0.3692   1.0000
   4.250   0.5059   0.01572   0.00687   0.0027   0.3419   1.0000
   4.500   0.5310   0.01624   0.00734   0.0033   0.3158   1.0000
   4.750   0.5560   0.01680   0.00783   0.0039   0.2915   1.0000
   5.000   0.5809   0.01740   0.00834   0.0045   0.2684   1.0000
   5.250   0.6060   0.01805   0.00906   0.0051   0.2457   1.0000
   5.500   0.6307   0.01875   0.00963   0.0056   0.2250   1.0000
   5.750   0.6557   0.01952   0.01053   0.0062   0.2041   1.0000
   6.000   0.6802   0.02032   0.01127   0.0067   0.1850   1.0000
   6.250   0.7046   0.02129   0.01223   0.0073   0.1671   1.0000
   6.500   0.7288   0.02223   0.01334   0.0079   0.1495   1.0000
   6.750   0.7528   0.02338   0.01457   0.0085   0.1348   1.0000
   7.000   0.7765   0.02462   0.01591   0.0091   0.1214   1.0000
   7.250   0.7998   0.02606   0.01744   0.0097   0.1099   1.0000
   7.500   0.8232   0.02786   0.01922   0.0102   0.1014   1.0000
   7.750   0.8448   0.02981   0.02171   0.0111   0.0933   1.0000
   8.000   0.8660   0.03191   0.02386   0.0116   0.0867   1.0000
   8.250   0.8837   0.03495   0.02759   0.0125   0.0825   1.0000
   8.500   0.9021   0.03760   0.03054   0.0132   0.0785   1.0000
   8.750   0.9171   0.04082   0.03392   0.0135   0.0743   1.0000
   9.000   0.9218   0.04541   0.03930   0.0141   0.0721   1.0000
   9.250   0.9193   0.05110   0.04559   0.0140   0.0714   1.0000
   9.500   0.9081   0.05741   0.05235   0.0131   0.0716   1.0000
   9.750   0.8904   0.06382   0.05903   0.0112   0.0724   1.0000
  10.000   0.8695   0.06976   0.06509   0.0089   0.0733   1.0000
  10.250   0.8506   0.07618   0.07154   0.0050   0.0742   1.0000
  10.500   0.8396   0.08298   0.07837   0.0012   0.0752   1.0000
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