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NREL's S802 Airfoil (s802-nr) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NREL's S802 Airfoil (s802-nr)
Reynolds number: 50,000
Max Cl/Cd: 33.77 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s802-nr-50000-n5.txt
Download as CSV file: xf-s802-nr-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3976   0.10333   0.09680  -0.0474   1.0000   0.0625
  -8.500  -0.3890   0.10100   0.09450  -0.0438   1.0000   0.0610
  -8.250  -0.3977   0.09899   0.09259  -0.0416   1.0000   0.0599
  -8.000  -0.4110   0.09709   0.09079  -0.0393   1.0000   0.0590
  -7.750  -0.4272   0.09530   0.08912  -0.0370   1.0000   0.0581
  -7.500  -0.4276   0.09104   0.08490  -0.0407   0.9941   0.0565
  -7.000  -0.4237   0.07228   0.06574  -0.0659   0.9718   0.0504
  -6.750  -0.4137   0.06699   0.06021  -0.0705   0.9634   0.0504
  -6.250  -0.3814   0.05946   0.05243  -0.0760   0.9504   0.0527
  -6.000  -0.3631   0.05525   0.04789  -0.0793   0.9443   0.0534
  -5.750  -0.3418   0.05076   0.04290  -0.0826   0.9382   0.0535
  -5.500  -0.3121   0.04640   0.03795  -0.0865   0.9343   0.0535
  -5.250  -0.2895   0.04332   0.03439  -0.0878   0.9282   0.0539
  -5.000  -0.2599   0.04050   0.03108  -0.0898   0.9238   0.0549
  -4.750  -0.2266   0.03823   0.02834  -0.0920   0.9206   0.0580
  -4.500  -0.1996   0.03641   0.02597  -0.0926   0.9159   0.0610
  -4.250  -0.1716   0.03475   0.02391  -0.0930   0.9114   0.0629
  -4.000  -0.1414   0.03332   0.02236  -0.0938   0.9078   0.0655
  -3.750  -0.1086   0.03218   0.02104  -0.0947   0.9050   0.0701
  -3.500  -0.0881   0.03153   0.02014  -0.0934   0.8994   0.0759
  -3.250  -0.0619   0.03075   0.01937  -0.0935   0.8953   0.0841
  -3.000  -0.0318   0.02992   0.01847  -0.0940   0.8920   0.0954
  -2.750  -0.0014   0.02911   0.01771  -0.0951   0.8886   0.1228
  -2.500   0.0227   0.02821   0.01723  -0.0955   0.8836   0.1912
  -2.250   0.0516   0.02659   0.01703  -0.0972   0.8805   0.4385
  -2.000   0.0595   0.02651   0.01787  -0.0911   0.8764   0.6661
  -1.750   0.0700   0.02700   0.01826  -0.0869   0.8709   0.7628
  -1.500   0.0779   0.02728   0.01846  -0.0820   0.8653   0.8193
  -1.250   0.0905   0.02729   0.01834  -0.0778   0.8613   0.8683
  -1.000   0.1021   0.02727   0.01822  -0.0741   0.8562   0.9129
  -0.500   0.1777   0.02738   0.01786  -0.0788   0.8479   1.0000
  -0.250   0.2118   0.02762   0.01784  -0.0808   0.8449   1.0000
   0.000   0.2283   0.02809   0.01816  -0.0801   0.8382   1.0000
   0.250   0.2576   0.02846   0.01833  -0.0813   0.8338   1.0000
   0.500   0.2924   0.02876   0.01845  -0.0832   0.8305   1.0000
   0.750   0.3131   0.02932   0.01888  -0.0832   0.8243   1.0000
   1.000   0.3414   0.02977   0.01920  -0.0841   0.8192   1.0000
   1.250   0.3761   0.03011   0.01943  -0.0859   0.8155   1.0000
   1.500   0.3972   0.03074   0.01997  -0.0858   0.8090   1.0000
   1.750   0.4256   0.03121   0.02038  -0.0867   0.8036   1.0000
   2.000   0.4616   0.03153   0.02063  -0.0885   0.7998   1.0000
   2.250   0.4792   0.03228   0.02135  -0.0878   0.7918   1.0000
   2.500   0.5112   0.03268   0.02172  -0.0890   0.7867   1.0000
   2.750   0.5386   0.03320   0.02223  -0.0896   0.7806   1.0000
   3.000   0.5631   0.03378   0.02282  -0.0898   0.7732   1.0000
   3.250   0.6010   0.03397   0.02303  -0.0915   0.7690   1.0000
   3.500   0.6167   0.03481   0.02390  -0.0905   0.7589   1.0000
   4.000   0.6715   0.03570   0.02489  -0.0911   0.7434   1.0000
   4.250   0.7121   0.03559   0.02489  -0.0928   0.7384   1.0000
   4.500   0.7291   0.03632   0.02569  -0.0917   0.7267   1.0000
   4.750   0.7544   0.03670   0.02616  -0.0914   0.7167   1.0000
   5.250   0.8136   0.03680   0.02653  -0.0914   0.6968   1.0000
   5.500   0.8397   0.03687   0.02674  -0.0908   0.6848   1.0000
   5.750   0.8868   0.03567   0.02571  -0.0920   0.6774   1.0000
   6.000   0.9116   0.03551   0.02574  -0.0909   0.6630   1.0000
   6.250   0.9386   0.03510   0.02550  -0.0899   0.6480   1.0000
   6.750   0.9766   0.03491   0.02567  -0.0860   0.6105   1.0000
   7.000   0.9994   0.03441   0.02534  -0.0842   0.5898   1.0000
   7.250   1.0116   0.03465   0.02575  -0.0817   0.5645   1.0000
   7.500   1.0278   0.03462   0.02588  -0.0794   0.5357   1.0000
   7.750   1.0521   0.03397   0.02535  -0.0776   0.5007   1.0000
   8.000   1.0830   0.03289   0.02418  -0.0758   0.4519   1.0000
   8.250   1.1062   0.03276   0.02368  -0.0738   0.3913   1.0000
   8.500   1.1152   0.03395   0.02452  -0.0712   0.3387   1.0000
   8.750   1.1193   0.03567   0.02594  -0.0687   0.2954   1.0000
   9.000   1.1228   0.03757   0.02763  -0.0665   0.2604   1.0000
   9.250   1.1272   0.03954   0.02942  -0.0646   0.2310   1.0000
   9.500   1.1333   0.04150   0.03126  -0.0629   0.2062   1.0000
   9.750   1.1404   0.04345   0.03310  -0.0614   0.1864   1.0000
  10.000   1.1495   0.04534   0.03491  -0.0601   0.1691   1.0000
  10.250   1.1611   0.04713   0.03670  -0.0590   0.1546   1.0000
  10.500   1.1736   0.04889   0.03842  -0.0579   0.1418   1.0000
  10.750   1.1886   0.05055   0.04020  -0.0570   0.1301   1.0000
  11.000   1.2080   0.05209   0.04188  -0.0562   0.1200   1.0000
  11.250   1.2269   0.05369   0.04352  -0.0555   0.1113   1.0000
  11.500   1.2451   0.05540   0.04538  -0.0548   0.1036   1.0000
  11.750   1.2674   0.05721   0.04738  -0.0542   0.0971   1.0000
  12.000   1.2817   0.05930   0.04968  -0.0535   0.0912   1.0000
  12.250   1.2999   0.06140   0.05184  -0.0530   0.0863   1.0000
  12.500   1.3109   0.06428   0.05514  -0.0521   0.0824   1.0000
  12.750   1.3184   0.06699   0.05808  -0.0513   0.0787   1.0000
  13.000   1.3330   0.06930   0.06035  -0.0509   0.0750   1.0000
  13.250   1.3259   0.07331   0.06488  -0.0499   0.0730   1.0000
  13.500   1.3185   0.07762   0.06960  -0.0492   0.0713   1.0000
  13.750   1.3082   0.08219   0.07451  -0.0489   0.0698   1.0000
  14.000   1.2952   0.08703   0.07966  -0.0491   0.0684   1.0000
  14.250   1.2808   0.09215   0.08505  -0.0497   0.0672   1.0000
  14.500   1.2655   0.09755   0.09068  -0.0509   0.0662   1.0000
  14.750   1.2491   0.10336   0.09669  -0.0527   0.0653   1.0000
  15.000   1.2536   0.10651   0.09981  -0.0532   0.0633   1.0000
  15.250   1.2266   0.11441   0.10798  -0.0569   0.0632   1.0000
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