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NREL's S802 Airfoil (s802-nr) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NREL's S802 Airfoil (s802-nr)
Reynolds number: 100,000
Max Cl/Cd: 60.23 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s802-nr-100000-n5.txt
Download as CSV file: xf-s802-nr-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S802 Airfoil                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3460   0.10883   0.10397  -0.0439   1.0000   0.0564
  -9.250  -0.3534   0.10635   0.10159  -0.0429   1.0000   0.0558
  -8.750  -0.3622   0.08980   0.08507  -0.0564   0.9903   0.0323
  -8.500  -0.3494   0.08515   0.08043  -0.0610   0.9845   0.0319
  -8.250  -0.3439   0.07933   0.07462  -0.0671   0.9748   0.0319
  -8.000  -0.3417   0.07307   0.06837  -0.0741   0.9630   0.0318
  -7.750  -0.3367   0.06523   0.06046  -0.0843   0.9501   0.0315
  -7.500  -0.3332   0.05780   0.05278  -0.0920   0.9381   0.0315
  -7.250  -0.3252   0.05126   0.04589  -0.0978   0.9282   0.0315
  -7.000  -0.3085   0.04547   0.03964  -0.1025   0.9214   0.0314
  -6.750  -0.2918   0.04085   0.03454  -0.1050   0.9133   0.0314
  -6.500  -0.2669   0.03652   0.02963  -0.1079   0.9081   0.0315
  -6.250  -0.2353   0.03280   0.02524  -0.1109   0.9051   0.0318
  -6.000  -0.2120   0.03039   0.02228  -0.1112   0.8975   0.0326
  -5.750  -0.1810   0.02858   0.02034  -0.1131   0.8936   0.0344
  -5.500  -0.1464   0.02689   0.01837  -0.1151   0.8908   0.0361
  -5.250  -0.1200   0.02538   0.01657  -0.1152   0.8844   0.0370
  -5.000  -0.0891   0.02396   0.01489  -0.1160   0.8799   0.0381
  -4.750  -0.0556   0.02269   0.01340  -0.1172   0.8768   0.0396
  -4.500  -0.0254   0.02166   0.01230  -0.1180   0.8728   0.0421
  -4.250   0.0008   0.02101   0.01163  -0.1180   0.8669   0.0456
  -4.000   0.0327   0.02022   0.01071  -0.1190   0.8631   0.0490
  -3.750   0.0669   0.01934   0.00978  -0.1205   0.8603   0.0538
  -3.500   0.0918   0.01889   0.00926  -0.1202   0.8539   0.0617
  -3.250   0.1218   0.01821   0.00869  -0.1210   0.8496   0.0845
  -3.000   0.1542   0.01746   0.00821  -0.1223   0.8465   0.1473
  -2.750   0.1837   0.01654   0.00800  -0.1236   0.8429   0.3033
  -2.500   0.2047   0.01578   0.00812  -0.1228   0.8372   0.5072
  -2.250   0.2243   0.01577   0.00856  -0.1200   0.8330   0.6457
  -2.000   0.2526   0.01594   0.00867  -0.1194   0.8300   0.7147
  -1.750   0.2717   0.01626   0.00891  -0.1173   0.8244   0.7494
  -1.500   0.2939   0.01647   0.00902  -0.1157   0.8199   0.7753
  -1.250   0.3192   0.01658   0.00903  -0.1146   0.8165   0.7980
  -1.000   0.3430   0.01667   0.00904  -0.1133   0.8130   0.8170
  -0.750   0.3581   0.01689   0.00922  -0.1106   0.8072   0.8334
  -0.500   0.3797   0.01696   0.00923  -0.1090   0.8033   0.8496
  -0.250   0.4043   0.01694   0.00913  -0.1079   0.8003   0.8652
   0.000   0.4219   0.01705   0.00921  -0.1058   0.7955   0.8799
   0.250   0.4397   0.01715   0.00929  -0.1037   0.7905   0.8941
   0.500   0.4643   0.01713   0.00923  -0.1029   0.7870   0.9070
   0.750   0.4935   0.01707   0.00911  -0.1031   0.7844   0.9183
   1.000   0.5112   0.01728   0.00933  -0.1014   0.7786   0.9298
   1.250   0.5378   0.01736   0.00940  -0.1014   0.7742   0.9391
   1.500   0.5710   0.01736   0.00938  -0.1026   0.7710   0.9472
   1.750   0.6083   0.01732   0.00931  -0.1045   0.7685   0.9545
   2.000   0.6322   0.01768   0.00972  -0.1045   0.7614   0.9676
   2.250   0.6682   0.01774   0.00978  -0.1064   0.7572   0.9823
   2.500   0.7051   0.01770   0.00975  -0.1083   0.7539   1.0000
   2.750   0.7254   0.01811   0.01020  -0.1076   0.7466   1.0000
   3.000   0.7575   0.01818   0.01029  -0.1086   0.7414   1.0000
   3.250   0.7907   0.01821   0.01035  -0.1097   0.7362   1.0000
   3.500   0.8155   0.01843   0.01062  -0.1094   0.7278   1.0000
   3.750   0.8516   0.01828   0.01049  -0.1108   0.7216   1.0000
   4.000   0.8766   0.01841   0.01070  -0.1104   0.7116   1.0000
   4.250   0.9051   0.01841   0.01075  -0.1105   0.7017   1.0000
   4.500   0.9408   0.01813   0.01049  -0.1116   0.6924   1.0000
   4.750   0.9644   0.01820   0.01064  -0.1108   0.6795   1.0000
   5.000   0.9895   0.01821   0.01074  -0.1101   0.6660   1.0000
   5.250   1.0146   0.01820   0.01080  -0.1095   0.6513   1.0000
   5.500   1.0390   0.01819   0.01085  -0.1087   0.6349   1.0000
   5.750   1.0630   0.01818   0.01093  -0.1077   0.6163   1.0000
   6.000   1.0803   0.01838   0.01123  -0.1058   0.5929   1.0000
   6.250   1.0988   0.01851   0.01140  -0.1040   0.5627   1.0000
   6.500   1.1191   0.01858   0.01137  -0.1023   0.5174   1.0000
   6.750   1.1369   0.01890   0.01133  -0.1001   0.4547   1.0000
   7.000   1.1452   0.01976   0.01180  -0.0967   0.3944   1.0000
   7.250   1.1504   0.02085   0.01257  -0.0932   0.3412   1.0000
   7.500   1.1552   0.02207   0.01350  -0.0899   0.2941   1.0000
   7.750   1.1613   0.02330   0.01451  -0.0870   0.2546   1.0000
   8.000   1.1688   0.02454   0.01557  -0.0844   0.2205   1.0000
   8.250   1.1772   0.02578   0.01669  -0.0821   0.1920   1.0000
   8.500   1.1860   0.02706   0.01785  -0.0800   0.1693   1.0000
   8.750   1.1962   0.02830   0.01903  -0.0781   0.1499   1.0000
   9.000   1.2062   0.02959   0.02028  -0.0762   0.1343   1.0000
   9.250   1.2163   0.03092   0.02159  -0.0745   0.1218   1.0000
   9.500   1.2259   0.03232   0.02300  -0.0728   0.1117   1.0000
   9.750   1.2357   0.03374   0.02443  -0.0713   0.1025   1.0000
  10.000   1.2465   0.03514   0.02590  -0.0698   0.0949   1.0000
  10.250   1.2553   0.03671   0.02748  -0.0683   0.0888   1.0000
  10.500   1.2663   0.03819   0.02906  -0.0670   0.0829   1.0000
  10.750   1.2763   0.03976   0.03069  -0.0657   0.0777   1.0000
  11.000   1.2855   0.04149   0.03246  -0.0644   0.0738   1.0000
  11.250   1.2976   0.04304   0.03417  -0.0632   0.0696   1.0000
  11.500   1.3075   0.04473   0.03594  -0.0622   0.0660   1.0000
  11.750   1.3166   0.04662   0.03783  -0.0611   0.0629   1.0000
  12.000   1.3291   0.04830   0.03974  -0.0601   0.0596   1.0000
  12.250   1.3401   0.05012   0.04170  -0.0591   0.0568   1.0000
  12.500   1.3488   0.05205   0.04371  -0.0583   0.0543   1.0000
  12.750   1.3582   0.05417   0.04588  -0.0574   0.0519   1.0000
  13.000   1.3676   0.05631   0.04831  -0.0565   0.0496   1.0000
  13.250   1.3757   0.05859   0.05081  -0.0557   0.0474   1.0000
  13.500   1.3809   0.06097   0.05334  -0.0550   0.0454   1.0000
  13.750   1.3852   0.06341   0.05586  -0.0544   0.0437   1.0000
  14.000   1.3900   0.06618   0.05874  -0.0539   0.0421   1.0000
  14.250   1.3901   0.06947   0.06239  -0.0533   0.0407   1.0000
  14.500   1.3879   0.07298   0.06619  -0.0530   0.0392   1.0000
  14.750   1.3843   0.07658   0.07006  -0.0530   0.0378   1.0000
  15.000   1.3804   0.08021   0.07387  -0.0532   0.0366   1.0000
  15.250   1.3774   0.08377   0.07754  -0.0536   0.0355   1.0000
  15.500   1.3756   0.08736   0.08120  -0.0541   0.0345   1.0000
  15.750   1.3646   0.09255   0.08666  -0.0553   0.0338   1.0000
  16.000   1.3487   0.09868   0.09313  -0.0573   0.0332   1.0000
  16.250   1.3310   0.10541   0.10018  -0.0600   0.0327   1.0000
  16.500   1.3114   0.11289   0.10795  -0.0636   0.0323   1.0000
  16.750   1.2893   0.12138   0.11672  -0.0683   0.0321   1.0000
  17.000   1.2635   0.13139   0.12698  -0.0746   0.0322   1.0000
  17.250   1.2323   0.14368   0.13951  -0.0829   0.0326   1.0000
  17.500   1.1933   0.15960   0.15557  -0.0939   0.0334   1.0000
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