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NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NREL's S803 Airfoil (s803-nr)
Reynolds number: 100,000
Max Cl/Cd: 63.12 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s803-nr-100000.txt
Download as CSV file: xf-s803-nr-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3442   0.10854   0.10363  -0.0404   1.0000   0.1012
  -9.000  -0.3695   0.10739   0.10264  -0.0431   1.0000   0.1032
  -8.750  -0.3970   0.10616   0.10157  -0.0444   1.0000   0.1037
  -8.500  -0.3531   0.09990   0.09521  -0.0393   1.0000   0.1075
  -8.250  -0.3519   0.09761   0.09297  -0.0378   1.0000   0.1107
  -8.000  -0.3617   0.09560   0.09106  -0.0368   1.0000   0.1143
  -7.750  -0.3873   0.09445   0.09006  -0.0357   1.0000   0.1168
  -7.500  -0.4220   0.09402   0.08981  -0.0331   1.0000   0.1175
  -7.250  -0.4544   0.09257   0.08853  -0.0339   1.0000   0.1180
  -7.000  -0.4883   0.08959   0.08556  -0.0399   1.0000   0.1185
  -6.750  -0.4591   0.08753   0.08360  -0.0265   1.0000   0.1214
  -6.500  -0.4621   0.08608   0.08221  -0.0232   1.0000   0.1243
  -6.250  -0.4553   0.07710   0.07310  -0.0455   0.9904   0.1346
  -6.000  -0.4292   0.07650   0.07261  -0.0381   0.9873   0.1417
  -5.750  -0.4045   0.07040   0.06642  -0.0484   0.9780   0.1539
  -5.500  -0.3777   0.06502   0.06092  -0.0571   0.9696   0.1680
  -5.250  -0.3485   0.06051   0.05629  -0.0634   0.9621   0.1836
  -5.000  -0.2829   0.04103   0.03483  -0.0864   0.9563   0.0867
  -4.750  -0.2353   0.03567   0.02832  -0.0915   0.9515   0.0752
  -4.500  -0.1896   0.03275   0.02482  -0.0957   0.9480   0.0755
  -4.250  -0.1570   0.03029   0.02200  -0.0972   0.9407   0.0751
  -4.000  -0.1141   0.02832   0.01962  -0.1001   0.9362   0.0756
  -3.750  -0.0791   0.02637   0.01761  -0.1018   0.9304   0.0785
  -3.500  -0.0427   0.02533   0.01651  -0.1035   0.9239   0.0850
  -3.250   0.0001   0.02398   0.01514  -0.1061   0.9203   0.0928
  -3.000   0.0278   0.02325   0.01444  -0.1062   0.9119   0.1044
  -2.750   0.0704   0.02151   0.01329  -0.1095   0.9079   0.1818
  -2.500   0.1062   0.01985   0.01367  -0.1110   0.9045   0.6250
  -2.250   0.1208   0.02058   0.01445  -0.1070   0.8944   0.7086
  -2.000   0.1468   0.02092   0.01474  -0.1046   0.8896   0.7550
  -1.750   0.1571   0.02134   0.01510  -0.1004   0.8797   0.7846
  -1.500   0.1815   0.02130   0.01499  -0.0979   0.8756   0.8160
  -1.250   0.1865   0.02157   0.01523  -0.0931   0.8652   0.8386
  -1.000   0.2102   0.02133   0.01489  -0.0910   0.8612   0.8647
  -0.750   0.2153   0.02159   0.01510  -0.0868   0.8516   0.8865
  -0.500   0.2382   0.02125   0.01467  -0.0849   0.8470   0.9100
  -0.250   0.2507   0.02137   0.01474  -0.0822   0.8392   0.9328
   0.000   0.2840   0.02125   0.01455  -0.0831   0.8342   0.9588
   0.250   0.3531   0.02097   0.01414  -0.0908   0.8325   0.9838
   0.500   0.4143   0.02072   0.01376  -0.0973   0.8306   1.0000
   0.750   0.4139   0.02150   0.01451  -0.0941   0.8196   1.0000
   1.000   0.4594   0.02139   0.01432  -0.0978   0.8164   1.0000
   1.250   0.4796   0.02204   0.01493  -0.0979   0.8084   1.0000
   1.500   0.5175   0.02219   0.01503  -0.1004   0.8032   1.0000
   1.750   0.5645   0.02201   0.01480  -0.1040   0.8003   1.0000
   2.000   0.5827   0.02291   0.01571  -0.1039   0.7909   1.0000
   2.250   0.6258   0.02284   0.01562  -0.1068   0.7867   1.0000
   2.500   0.6747   0.02252   0.01529  -0.1104   0.7839   1.0000
   2.750   0.6907   0.02353   0.01634  -0.1098   0.7731   1.0000
   3.000   0.7392   0.02313   0.01594  -0.1131   0.7696   1.0000
   3.250   0.7593   0.02396   0.01680  -0.1129   0.7593   1.0000
   3.500   0.8077   0.02343   0.01631  -0.1158   0.7547   1.0000
   3.750   0.8312   0.02401   0.01695  -0.1157   0.7443   1.0000
   4.000   0.8814   0.02321   0.01617  -0.1186   0.7387   1.0000
   4.250   0.9072   0.02352   0.01656  -0.1184   0.7272   1.0000
   4.500   0.9435   0.02321   0.01630  -0.1192   0.7171   1.0000
   4.750   0.9893   0.02235   0.01546  -0.1210   0.7076   1.0000
   5.000   1.0179   0.02227   0.01547  -0.1207   0.6944   1.0000
   5.250   1.0488   0.02204   0.01529  -0.1206   0.6808   1.0000
   5.500   1.0803   0.02171   0.01501  -0.1204   0.6666   1.0000
   5.750   1.1114   0.02134   0.01472  -0.1201   0.6512   1.0000
   6.000   1.1418   0.02096   0.01438  -0.1197   0.6347   1.0000
   6.250   1.1719   0.02053   0.01398  -0.1191   0.6165   1.0000
   6.500   1.1955   0.02032   0.01387  -0.1177   0.5955   1.0000
   6.750   1.2191   0.02003   0.01362  -0.1161   0.5712   1.0000
   7.000   1.2378   0.01988   0.01354  -0.1137   0.5416   1.0000
   7.250   1.2529   0.01985   0.01354  -0.1108   0.5022   1.0000
   7.500   1.2633   0.02004   0.01361  -0.1072   0.4434   1.0000
   7.750   1.2653   0.02100   0.01399  -0.1024   0.3634   1.0000
   8.000   1.2619   0.02269   0.01510  -0.0975   0.2971   1.0000
   8.250   1.2592   0.02443   0.01642  -0.0929   0.2507   1.0000
   8.500   1.2603   0.02616   0.01784  -0.0891   0.2165   1.0000
   8.750   1.2654   0.02786   0.01929  -0.0861   0.1909   1.0000
   9.000   1.2742   0.02949   0.02076  -0.0837   0.1710   1.0000
   9.250   1.2862   0.03113   0.02226  -0.0818   0.1548   1.0000
   9.500   1.3015   0.03273   0.02378  -0.0804   0.1411   1.0000
   9.750   1.3204   0.03435   0.02541  -0.0794   0.1296   1.0000
  10.000   1.3417   0.03609   0.02715  -0.0788   0.1195   1.0000
  10.250   1.3730   0.03813   0.02904  -0.0797   0.1103   1.0000
  10.500   1.3904   0.03978   0.03097  -0.0784   0.1037   1.0000
  10.750   1.4236   0.04219   0.03332  -0.0798   0.0964   1.0000
  11.000   1.4405   0.04422   0.03567  -0.0785   0.0918   1.0000
  11.250   1.4646   0.04639   0.03785  -0.0786   0.0866   1.0000
  11.500   1.4808   0.04935   0.04111  -0.0777   0.0828   1.0000
  11.750   1.4860   0.05183   0.04400  -0.0751   0.0801   1.0000
  12.000   1.4944   0.05416   0.04654  -0.0731   0.0769   1.0000
  12.250   1.5211   0.05837   0.05071  -0.0746   0.0725   1.0000
  12.500   1.5075   0.06078   0.05355  -0.0700   0.0717   1.0000
  12.750   1.4928   0.06378   0.05695  -0.0661   0.0708   1.0000
  13.000   1.4761   0.06721   0.06076  -0.0629   0.0699   1.0000
  13.250   1.4578   0.07106   0.06496  -0.0603   0.0691   1.0000
  13.500   1.4375   0.07534   0.06957  -0.0584   0.0684   1.0000
  13.750   1.4150   0.08015   0.07469  -0.0574   0.0679   1.0000
  14.000   1.3894   0.08566   0.08050  -0.0572   0.0677   1.0000
  14.250   1.3602   0.09208   0.08720  -0.0580   0.0681   1.0000
  14.500   1.3283   0.09943   0.09482  -0.0601   0.0687   1.0000
  14.750   1.2953   0.10768   0.10329  -0.0635   0.0696   1.0000
  15.000   1.2630   0.11676   0.11255  -0.0681   0.0706   1.0000
  15.250   1.2336   0.12649   0.12241  -0.0735   0.0716   1.0000
  15.500   1.2087   0.13664   0.13263  -0.0793   0.0723   1.0000
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