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S6062 8% (s6062-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S6062 8% (s6062-il)
Reynolds number: 100,000
Max Cl/Cd: 48.39 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s6062-il-100000-n5.txt
Download as CSV file: xf-s6062-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6062 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5244   0.09396   0.08906  -0.0112   1.0000   0.0234
  -8.750  -0.5226   0.09001   0.08514  -0.0128   1.0000   0.0229
  -8.500  -0.5222   0.08578   0.08097  -0.0150   1.0000   0.0223
  -8.250  -0.5236   0.08128   0.07653  -0.0177   1.0000   0.0217
  -8.000  -0.5268   0.07657   0.07189  -0.0212   1.0000   0.0211
  -7.750  -0.5302   0.07088   0.06623  -0.0263   1.0000   0.0206
  -7.500  -0.5312   0.06456   0.05985  -0.0311   1.0000   0.0199
  -7.250  -0.5319   0.05742   0.05254  -0.0350   1.0000   0.0189
  -7.000  -0.5305   0.04947   0.04402  -0.0377   1.0000   0.0176
  -6.750  -0.5219   0.04539   0.03969  -0.0380   1.0000   0.0175
  -6.500  -0.5111   0.04145   0.03543  -0.0380   1.0000   0.0173
  -6.250  -0.4984   0.03772   0.03130  -0.0375   1.0000   0.0172
  -6.000  -0.4838   0.03432   0.02745  -0.0367   1.0000   0.0172
  -5.750  -0.4670   0.03143   0.02401  -0.0355   1.0000   0.0176
  -5.500  -0.4509   0.02901   0.02140  -0.0346   1.0000   0.0188
  -5.250  -0.4324   0.02725   0.01939  -0.0335   1.0000   0.0198
  -5.000  -0.4130   0.02530   0.01711  -0.0322   1.0000   0.0205
  -4.750  -0.3929   0.02338   0.01483  -0.0307   1.0000   0.0210
  -4.500  -0.3726   0.02175   0.01295  -0.0293   1.0000   0.0215
  -4.250  -0.3524   0.02036   0.01139  -0.0278   1.0000   0.0223
  -4.000  -0.3324   0.01922   0.01010  -0.0264   1.0000   0.0232
  -3.750  -0.3124   0.01826   0.00901  -0.0250   1.0000   0.0243
  -3.500  -0.2929   0.01730   0.00798  -0.0238   1.0000   0.0270
  -3.250  -0.2577   0.01647   0.00701  -0.0255   0.9933   0.0356
  -3.000  -0.2228   0.01530   0.00597  -0.0271   0.9864   0.0702
  -2.750  -0.1910   0.01391   0.00555  -0.0290   0.9795   0.2510
  -2.500  -0.1596   0.01277   0.00534  -0.0304   0.9727   0.4677
  -2.250  -0.1304   0.01212   0.00526  -0.0303   0.9650   0.6412
  -2.000  -0.0988   0.01184   0.00528  -0.0299   0.9585   0.7747
  -1.750  -0.0651   0.01175   0.00523  -0.0300   0.9510   0.8637
  -1.500  -0.0180   0.01171   0.00506  -0.0332   0.9464   0.9274
  -1.250   0.0383   0.01164   0.00479  -0.0387   0.9433   0.9687
  -1.000   0.0934   0.01152   0.00450  -0.0443   0.9375   0.9988
  -0.750   0.1278   0.01150   0.00434  -0.0458   0.9260   1.0000
  -0.500   0.1590   0.01148   0.00419  -0.0466   0.9134   1.0000
  -0.250   0.1880   0.01148   0.00409  -0.0469   0.9002   1.0000
   0.000   0.2149   0.01149   0.00402  -0.0466   0.8863   1.0000
   0.250   0.2409   0.01152   0.00396  -0.0461   0.8721   1.0000
   0.500   0.2660   0.01155   0.00393  -0.0454   0.8575   1.0000
   0.750   0.2905   0.01159   0.00392  -0.0446   0.8424   1.0000
   1.000   0.3149   0.01164   0.00392  -0.0437   0.8271   1.0000
   1.250   0.3393   0.01169   0.00396  -0.0427   0.8113   1.0000
   1.500   0.3638   0.01175   0.00398  -0.0418   0.7949   1.0000
   1.750   0.3883   0.01181   0.00401  -0.0408   0.7782   1.0000
   2.000   0.4130   0.01188   0.00405  -0.0398   0.7608   1.0000
   2.250   0.4374   0.01196   0.00416  -0.0389   0.7410   1.0000
   2.500   0.4622   0.01205   0.00424  -0.0380   0.7213   1.0000
   2.750   0.4869   0.01216   0.00434  -0.0371   0.6998   1.0000
   3.000   0.5117   0.01229   0.00445  -0.0361   0.6777   1.0000
   3.250   0.5364   0.01243   0.00463  -0.0352   0.6530   1.0000
   3.500   0.5611   0.01260   0.00480  -0.0343   0.6265   1.0000
   3.750   0.5857   0.01280   0.00498  -0.0334   0.5977   1.0000
   4.000   0.6100   0.01304   0.00519  -0.0325   0.5659   1.0000
   4.250   0.6341   0.01331   0.00548  -0.0316   0.5301   1.0000
   4.500   0.6580   0.01364   0.00577  -0.0306   0.4911   1.0000
   4.750   0.6809   0.01407   0.00609  -0.0296   0.4421   1.0000
   5.000   0.7010   0.01478   0.00641  -0.0283   0.3581   1.0000
   5.250   0.7191   0.01587   0.00688  -0.0271   0.2494   1.0000
   5.500   0.7393   0.01689   0.00754  -0.0263   0.1743   1.0000
   5.750   0.7585   0.01819   0.00842  -0.0255   0.0942   1.0000
   6.000   0.7777   0.01959   0.00953  -0.0245   0.0484   1.0000
   6.250   0.7982   0.02082   0.01078  -0.0234   0.0372   1.0000
   6.500   0.8187   0.02199   0.01209  -0.0223   0.0331   1.0000
   6.750   0.8394   0.02305   0.01330  -0.0214   0.0292   1.0000
   7.000   0.8582   0.02437   0.01470  -0.0204   0.0263   1.0000
   7.250   0.8769   0.02579   0.01626  -0.0192   0.0251   1.0000
   7.500   0.8963   0.02727   0.01797  -0.0180   0.0242   1.0000
   7.750   0.9162   0.02895   0.01982  -0.0169   0.0235   1.0000
   8.000   0.9364   0.03083   0.02190  -0.0159   0.0229   1.0000
   8.250   0.9566   0.03296   0.02427  -0.0149   0.0224   1.0000
   8.500   0.9757   0.03536   0.02698  -0.0139   0.0220   1.0000
   8.750   0.9926   0.03805   0.03002  -0.0128   0.0218   1.0000
   9.000   1.0064   0.04093   0.03330  -0.0115   0.0214   1.0000
   9.250   1.0177   0.04352   0.03620  -0.0102   0.0206   1.0000
   9.500   1.0261   0.04611   0.03908  -0.0090   0.0198   1.0000
   9.750   1.0310   0.04891   0.04212  -0.0077   0.0191   1.0000
  10.000   1.0303   0.05244   0.04596  -0.0063   0.0186   1.0000
  10.250   1.0247   0.05603   0.04987  -0.0047   0.0186   1.0000
  10.500   1.0127   0.05942   0.05352  -0.0028   0.0186   1.0000
  10.750   0.9984   0.06300   0.05734  -0.0018   0.0186   1.0000
  11.000   0.9821   0.06712   0.06169  -0.0022   0.0186   1.0000
  11.250   0.9647   0.07192   0.06672  -0.0041   0.0188   1.0000
  11.500   0.9444   0.07803   0.07303  -0.0077   0.0189   1.0000
  11.750   0.9190   0.08651   0.08167  -0.0142   0.0192   1.0000
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