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NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NREL's S803 Airfoil (s803-nr)
Reynolds number: 200,000
Max Cl/Cd: 83.8 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s803-nr-200000-n5.txt
Download as CSV file: xf-s803-nr-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S803 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3772   0.09235   0.08883  -0.0439   1.0000   0.0198
  -9.000  -0.3826   0.08922   0.08576  -0.0438   1.0000   0.0194
  -8.750  -0.3885   0.08299   0.07958  -0.0479   0.9982   0.0200
  -8.500  -0.3810   0.07645   0.07306  -0.0551   0.9934   0.0198
  -8.250  -0.3766   0.06914   0.06576  -0.0635   0.9860   0.0195
  -8.000  -0.3820   0.05476   0.05126  -0.0827   0.9700   0.0190
  -7.750  -0.3839   0.04383   0.03984  -0.0936   0.9545   0.0187
  -7.500  -0.3704   0.03594   0.03129  -0.0999   0.9446   0.0188
  -7.250  -0.3477   0.03066   0.02534  -0.1036   0.9368   0.0192
  -7.000  -0.3206   0.02708   0.02115  -0.1060   0.9302   0.0198
  -6.750  -0.2905   0.02457   0.01809  -0.1080   0.9237   0.0209
  -6.500  -0.2563   0.02276   0.01609  -0.1103   0.9199   0.0217
  -6.250  -0.2272   0.02128   0.01439  -0.1112   0.9114   0.0222
  -6.000  -0.1912   0.01984   0.01273  -0.1134   0.9068   0.0229
  -5.750  -0.1578   0.01864   0.01135  -0.1148   0.8999   0.0237
  -5.500  -0.1212   0.01756   0.01011  -0.1169   0.8937   0.0247
  -5.250  -0.0847   0.01677   0.00914  -0.1188   0.8867   0.0261
  -5.000  -0.0490   0.01573   0.00807  -0.1208   0.8786   0.0275
  -4.750  -0.0132   0.01498   0.00727  -0.1227   0.8698   0.0287
  -4.500   0.0238   0.01433   0.00653  -0.1249   0.8612   0.0303
  -4.250   0.0575   0.01381   0.00588  -0.1263   0.8508   0.0321
  -4.000   0.0916   0.01331   0.00532  -0.1278   0.8407   0.0355
  -3.750   0.1250   0.01295   0.00486  -0.1290   0.8302   0.0410
  -3.500   0.1558   0.01252   0.00441  -0.1298   0.8189   0.0525
  -3.250   0.1866   0.01209   0.00407  -0.1307   0.8085   0.0860
  -2.750   0.2467   0.01119   0.00362  -0.1325   0.7889   0.2346
  -2.500   0.2766   0.01052   0.00348  -0.1337   0.7798   0.3890
  -2.250   0.3041   0.01017   0.00367  -0.1337   0.7705   0.5494
  -2.000   0.3315   0.01024   0.00376  -0.1333   0.7616   0.6076
  -1.750   0.3596   0.01036   0.00380  -0.1331   0.7537   0.6396
  -1.500   0.3873   0.01046   0.00383  -0.1329   0.7457   0.6608
  -1.250   0.4152   0.01057   0.00385  -0.1327   0.7385   0.6770
  -1.000   0.4422   0.01066   0.00390  -0.1324   0.7307   0.6904
  -0.750   0.4695   0.01076   0.00394  -0.1321   0.7239   0.7014
  -0.500   0.4968   0.01085   0.00398  -0.1318   0.7173   0.7121
  -0.250   0.5246   0.01096   0.00402  -0.1317   0.7109   0.7230
   0.000   0.5512   0.01105   0.00410  -0.1313   0.7051   0.7320
   0.250   0.5782   0.01114   0.00417  -0.1310   0.6986   0.7414
   0.500   0.6056   0.01124   0.00423  -0.1308   0.6933   0.7493
   0.750   0.6332   0.01132   0.00429  -0.1307   0.6876   0.7557
   1.000   0.6602   0.01140   0.00437  -0.1305   0.6818   0.7607
   1.250   0.6885   0.01150   0.00442  -0.1306   0.6768   0.7659
   1.500   0.7160   0.01158   0.00452  -0.1306   0.6709   0.7704
   1.750   0.7431   0.01166   0.00461  -0.1304   0.6650   0.7743
   2.000   0.7707   0.01176   0.00470  -0.1303   0.6594   0.7786
   2.250   0.7979   0.01185   0.00481  -0.1302   0.6521   0.7833
   2.500   0.8249   0.01195   0.00488  -0.1300   0.6454   0.7872
   2.750   0.8506   0.01203   0.00503  -0.1296   0.6365   0.7916
   3.000   0.8774   0.01213   0.00511  -0.1293   0.6280   0.7962
   3.250   0.9034   0.01222   0.00522  -0.1289   0.6178   0.8008
   3.500   0.9284   0.01230   0.00534  -0.1283   0.6069   0.8056
   3.750   0.9541   0.01240   0.00547  -0.1278   0.5962   0.8112
   4.000   0.9794   0.01251   0.00559  -0.1273   0.5849   0.8164
   4.250   1.0036   0.01261   0.00574  -0.1265   0.5721   0.8218
   4.500   1.0283   0.01273   0.00591  -0.1258   0.5585   0.8283
   4.750   1.0518   0.01284   0.00607  -0.1249   0.5437   0.8348
   5.000   1.0753   0.01299   0.00623  -0.1240   0.5267   0.8427
   5.250   1.0975   0.01314   0.00641  -0.1229   0.5058   0.8506
   5.500   1.1187   0.01335   0.00661  -0.1215   0.4775   0.8600
   5.750   1.1367   0.01365   0.00681  -0.1196   0.4363   0.8710
   6.000   1.1492   0.01422   0.00713  -0.1167   0.3810   0.8860
   6.250   1.1585   0.01491   0.00759  -0.1134   0.3294   0.9110
   6.500   1.1704   0.01564   0.00813  -0.1107   0.2825   1.0000
   6.750   1.1855   0.01655   0.00881  -0.1089   0.2408   1.0000
   7.000   1.2010   0.01740   0.00949  -0.1072   0.2061   1.0000
   7.250   1.2162   0.01824   0.01018  -0.1054   0.1776   1.0000
   7.500   1.2301   0.01905   0.01088  -0.1034   0.1543   1.0000
   7.750   1.2441   0.01984   0.01160  -0.1014   0.1359   1.0000
   8.000   1.2581   0.02063   0.01234  -0.0994   0.1204   1.0000
   8.250   1.2716   0.02145   0.01313  -0.0974   0.1076   1.0000
   8.500   1.2844   0.02231   0.01396  -0.0954   0.0972   1.0000
   8.750   1.2979   0.02314   0.01481  -0.0935   0.0882   1.0000
   9.000   1.3104   0.02404   0.01575  -0.0915   0.0810   1.0000
   9.250   1.3219   0.02502   0.01674  -0.0895   0.0746   1.0000
   9.500   1.3334   0.02602   0.01779  -0.0876   0.0698   1.0000
   9.750   1.3448   0.02706   0.01889  -0.0857   0.0652   1.0000
  10.000   1.3529   0.02836   0.02020  -0.0837   0.0611   1.0000
  10.250   1.3645   0.02945   0.02142  -0.0820   0.0577   1.0000
  10.500   1.3745   0.03070   0.02274  -0.0804   0.0544   1.0000
  10.750   1.3822   0.03217   0.02425  -0.0786   0.0517   1.0000
  11.000   1.3893   0.03376   0.02590  -0.0770   0.0494   1.0000
  11.250   1.3991   0.03517   0.02744  -0.0756   0.0470   1.0000
  11.500   1.4077   0.03672   0.02909  -0.0743   0.0447   1.0000
  11.750   1.4147   0.03846   0.03090  -0.0730   0.0428   1.0000
  12.000   1.4182   0.04059   0.03309  -0.0717   0.0410   1.0000
  12.250   1.4265   0.04235   0.03498  -0.0707   0.0395   1.0000
  12.500   1.4342   0.04418   0.03695  -0.0697   0.0378   1.0000
  12.750   1.4409   0.04615   0.03904  -0.0689   0.0362   1.0000
  13.000   1.4464   0.04828   0.04127  -0.0681   0.0347   1.0000
  13.250   1.4492   0.05076   0.04380  -0.0674   0.0334   1.0000
  13.500   1.4529   0.05323   0.04638  -0.0668   0.0322   1.0000
  13.750   1.4587   0.05550   0.04883  -0.0663   0.0308   1.0000
  14.000   1.4632   0.05797   0.05146  -0.0660   0.0294   1.0000
  14.250   1.4667   0.06059   0.05421  -0.0658   0.0281   1.0000
  14.500   1.4682   0.06351   0.05722  -0.0658   0.0270   1.0000
  14.750   1.4664   0.06694   0.06070  -0.0660   0.0259   1.0000
  15.000   1.4694   0.06990   0.06388  -0.0661   0.0249   1.0000
  15.250   1.4704   0.07317   0.06734  -0.0665   0.0237   1.0000
  15.500   1.4702   0.07667   0.07099  -0.0670   0.0227   1.0000
  15.750   1.4689   0.08042   0.07487  -0.0679   0.0218   1.0000
  16.000   1.4658   0.08454   0.07911  -0.0690   0.0211   1.0000
  16.250   1.4601   0.08917   0.08383  -0.0704   0.0204   1.0000
  16.500   1.4562   0.09369   0.08855  -0.0718   0.0197   1.0000
  16.750   1.4513   0.09847   0.09356  -0.0734   0.0190   1.0000
  17.000   1.4455   0.10355   0.09883  -0.0755   0.0183   1.0000
  17.250   1.4388   0.10891   0.10435  -0.0778   0.0177   1.0000
  17.500   1.4315   0.11454   0.11014  -0.0806   0.0171   1.0000
  17.750   1.4232   0.12048   0.11622  -0.0837   0.0167   1.0000
  18.000   1.4140   0.12676   0.12263  -0.0872   0.0163   1.0000
  18.250   1.4040   0.13332   0.12931  -0.0910   0.0160   1.0000
  18.500   1.3930   0.14027   0.13642  -0.0951   0.0157   1.0000
  18.750   1.3806   0.14779   0.14415  -0.0998   0.0154   1.0000
  19.000   1.3670   0.15582   0.15238  -0.1050   0.0152   1.0000
  19.250   1.3517   0.16453   0.16128  -0.1109   0.0150   1.0000
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