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NREL's S802 Airfoil (s802-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NREL's S802 Airfoil (s802-nr)
Reynolds number: 1,000,000
Max Cl/Cd: 149.48 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s802-nr-1000000.txt
Download as CSV file: xf-s802-nr-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2965   0.08924   0.08758  -0.0672   0.9914   0.0132
  -9.500  -0.2838   0.08522   0.08357  -0.0715   0.9890   0.0140
  -9.000  -0.3974   0.03181   0.02932  -0.1206   0.9490   0.0118
  -8.750  -0.3793   0.02442   0.02112  -0.1277   0.9380   0.0121
  -8.500  -0.3453   0.02040   0.01670  -0.1330   0.9301   0.0127
  -8.250  -0.3065   0.01946   0.01566  -0.1366   0.9200   0.0132
  -8.000  -0.2748   0.01833   0.01432  -0.1385   0.9048   0.0136
  -7.750  -0.2488   0.01723   0.01299  -0.1389   0.8881   0.0141
  -7.500  -0.2240   0.01651   0.01205  -0.1389   0.8729   0.0147
  -7.250  -0.1998   0.01571   0.01103  -0.1386   0.8591   0.0151
  -7.000  -0.1754   0.01504   0.01016  -0.1383   0.8467   0.0154
  -6.750  -0.1498   0.01471   0.00968  -0.1380   0.8356   0.0157
  -6.500  -0.1270   0.01316   0.00790  -0.1376   0.8254   0.0160
  -6.250  -0.1033   0.01201   0.00661  -0.1372   0.8159   0.0165
  -6.000  -0.0779   0.01139   0.00594  -0.1370   0.8075   0.0170
  -5.750  -0.0518   0.01104   0.00552  -0.1369   0.7998   0.0177
  -5.500  -0.0252   0.01067   0.00510  -0.1368   0.7929   0.0184
  -5.250   0.0014   0.01029   0.00463  -0.1367   0.7862   0.0189
  -5.000   0.0283   0.00991   0.00420  -0.1367   0.7803   0.0193
  -4.750   0.0556   0.00961   0.00383  -0.1367   0.7743   0.0198
  -4.500   0.0829   0.00936   0.00350  -0.1367   0.7688   0.0201
  -4.250   0.1106   0.00900   0.00310  -0.1369   0.7638   0.0206
  -4.000   0.1384   0.00862   0.00266  -0.1371   0.7588   0.0219
  -3.750   0.1663   0.00844   0.00243  -0.1372   0.7543   0.0234
  -3.500   0.1947   0.00827   0.00223  -0.1374   0.7502   0.0246
  -3.250   0.2231   0.00813   0.00206  -0.1375   0.7461   0.0258
  -3.000   0.2514   0.00796   0.00187  -0.1377   0.7422   0.0300
  -2.750   0.2799   0.00768   0.00172  -0.1381   0.7382   0.0686
  -2.500   0.3086   0.00734   0.00161  -0.1386   0.7348   0.1372
  -2.250   0.3373   0.00704   0.00154  -0.1391   0.7313   0.2095
  -2.000   0.3662   0.00672   0.00148  -0.1397   0.7280   0.2998
  -1.750   0.3953   0.00646   0.00144  -0.1402   0.7248   0.3895
  -1.500   0.4247   0.00610   0.00141  -0.1410   0.7217   0.5126
  -1.250   0.4536   0.00579   0.00147  -0.1415   0.7188   0.6375
  -1.000   0.4821   0.00577   0.00154  -0.1416   0.7157   0.6861
  -0.750   0.5105   0.00582   0.00161  -0.1416   0.7127   0.7134
  -0.500   0.5388   0.00591   0.00167  -0.1417   0.7095   0.7282
  -0.250   0.5674   0.00598   0.00172  -0.1418   0.7060   0.7372
   0.000   0.5954   0.00600   0.00176  -0.1417   0.7021   0.7447
   0.250   0.6235   0.00605   0.00179  -0.1418   0.6978   0.7519
   0.500   0.6515   0.00613   0.00183  -0.1418   0.6932   0.7578
   0.750   0.6792   0.00616   0.00188  -0.1417   0.6885   0.7635
   1.000   0.7071   0.00620   0.00191  -0.1417   0.6832   0.7691
   1.250   0.7345   0.00627   0.00195  -0.1415   0.6776   0.7739
   1.500   0.7620   0.00629   0.00201  -0.1414   0.6725   0.7789
   1.750   0.7897   0.00634   0.00205  -0.1414   0.6669   0.7838
   2.000   0.8169   0.00641   0.00210  -0.1413   0.6609   0.7880
   2.250   0.8442   0.00642   0.00215  -0.1411   0.6544   0.7926
   2.500   0.8712   0.00651   0.00222  -0.1409   0.6480   0.7972
   2.750   0.8989   0.00655   0.00228  -0.1409   0.6413   0.8007
   3.000   0.9257   0.00659   0.00232  -0.1407   0.6339   0.8037
   3.250   0.9527   0.00663   0.00239  -0.1405   0.6247   0.8062
   3.500   0.9792   0.00671   0.00246  -0.1403   0.6156   0.8088
   3.750   1.0057   0.00679   0.00253  -0.1400   0.6031   0.8114
   4.000   1.0314   0.00690   0.00260  -0.1396   0.5855   0.8139
   4.250   1.0556   0.00708   0.00270  -0.1389   0.5576   0.8163
   4.500   1.0762   0.00744   0.00288  -0.1376   0.5090   0.8189
   4.750   1.0921   0.00815   0.00326  -0.1354   0.4391   0.8216
   5.000   1.1093   0.00884   0.00365  -0.1335   0.3783   0.8245
   5.250   1.1274   0.00946   0.00403  -0.1319   0.3250   0.8276
   5.500   1.1448   0.01013   0.00443  -0.1301   0.2743   0.8305
   5.750   1.1628   0.01069   0.00481  -0.1284   0.2325   0.8335
   6.000   1.1808   0.01124   0.00519  -0.1268   0.1972   0.8365
   6.250   1.1995   0.01175   0.00557  -0.1253   0.1686   0.8400
   6.500   1.2186   0.01222   0.00593  -0.1238   0.1454   0.8437
   6.750   1.2374   0.01267   0.00630  -0.1223   0.1264   0.8474
   7.000   1.2559   0.01309   0.00667  -0.1207   0.1104   0.8514
   7.250   1.2729   0.01350   0.00704  -0.1188   0.0968   0.8558
   7.500   1.2896   0.01393   0.00742  -0.1169   0.0858   0.8606
   7.750   1.3055   0.01436   0.00783  -0.1148   0.0762   0.8659
   8.000   1.3230   0.01475   0.00823  -0.1131   0.0693   0.8720
   8.250   1.3387   0.01520   0.00868  -0.1111   0.0621   0.8791
   8.500   1.3549   0.01563   0.00913  -0.1092   0.0571   0.8881
   8.750   1.3695   0.01610   0.00964  -0.1070   0.0518   0.9003
   9.000   1.3834   0.01641   0.01006  -0.1046   0.0490   0.9254
   9.250   1.3967   0.01689   0.01057  -0.1023   0.0450   1.0000
   9.500   1.4127   0.01748   0.01119  -0.1006   0.0419   1.0000
   9.750   1.4298   0.01800   0.01175  -0.0992   0.0399   1.0000
  10.000   1.4446   0.01865   0.01239  -0.0975   0.0372   1.0000
  10.250   1.4570   0.01947   0.01322  -0.0954   0.0341   1.0000
  10.500   1.4743   0.01999   0.01377  -0.0941   0.0327   1.0000
  10.750   1.4892   0.02066   0.01448  -0.0926   0.0310   1.0000
  11.000   1.5024   0.02147   0.01530  -0.0908   0.0291   1.0000
  11.250   1.5121   0.02254   0.01641  -0.0887   0.0271   1.0000
  11.500   1.5276   0.02323   0.01715  -0.0874   0.0264   1.0000
  11.750   1.5419   0.02401   0.01798  -0.0860   0.0254   1.0000
  12.000   1.5551   0.02490   0.01890  -0.0846   0.0242   1.0000
  12.250   1.5665   0.02594   0.01996  -0.0830   0.0228   1.0000
  12.500   1.5742   0.02732   0.02138  -0.0811   0.0212   1.0000
  12.750   1.5883   0.02820   0.02233  -0.0800   0.0206   1.0000
  13.000   1.6011   0.02920   0.02339  -0.0788   0.0197   1.0000
  13.250   1.6125   0.03034   0.02458  -0.0775   0.0187   1.0000
  13.500   1.6221   0.03168   0.02594  -0.0762   0.0176   1.0000
  13.750   1.6281   0.03336   0.02768  -0.0746   0.0164   1.0000
  14.000   1.6404   0.03450   0.02888  -0.0737   0.0158   1.0000
  14.250   1.6509   0.03582   0.03026  -0.0726   0.0149   1.0000
  14.500   1.6595   0.03735   0.03184  -0.0716   0.0139   1.0000
  14.750   1.6633   0.03941   0.03394  -0.0703   0.0128   1.0000
  15.000   1.6732   0.04088   0.03549  -0.0694   0.0121   1.0000
  15.250   1.6807   0.04262   0.03729  -0.0686   0.0111   1.0000
  15.500   1.6844   0.04483   0.03954  -0.0676   0.0101   1.0000
  15.750   1.6889   0.04700   0.04179  -0.0668   0.0094   1.0000
  16.000   1.6936   0.04919   0.04406  -0.0661   0.0086   1.0000
  16.250   1.6957   0.05173   0.04666  -0.0655   0.0080   1.0000
  16.500   1.6923   0.05503   0.05005  -0.0649   0.0073   1.0000
  16.750   1.6953   0.05764   0.05277  -0.0645   0.0071   1.0000
  17.000   1.6966   0.06052   0.05575  -0.0643   0.0067   1.0000
  17.250   1.6962   0.06368   0.05902  -0.0643   0.0064   1.0000
  17.500   1.6941   0.06718   0.06262  -0.0644   0.0062   1.0000
  17.750   1.6904   0.07102   0.06656  -0.0647   0.0059   1.0000
  18.000   1.6832   0.07549   0.07115  -0.0654   0.0057   1.0000
  18.250   1.6720   0.08076   0.07655  -0.0665   0.0055   1.0000
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