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NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NREL's S803 Airfoil (s803-nr)
Reynolds number: 50,000
Max Cl/Cd: 38.6 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s803-nr-50000.txt
Download as CSV file: xf-s803-nr-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3353   0.11182   0.10503  -0.0321   1.0000   0.2392
  -8.500  -0.3294   0.10841   0.10168  -0.0310   1.0000   0.2463
  -8.250  -0.3446   0.10778   0.10120  -0.0301   1.0000   0.2559
  -8.000  -0.3311   0.10395   0.09740  -0.0283   1.0000   0.2684
  -7.750  -0.3320   0.10144   0.09500  -0.0267   1.0000   0.2781
  -7.500  -0.3571   0.10156   0.09531  -0.0245   1.0000   0.2875
  -7.250  -0.3465   0.09823   0.09202  -0.0223   1.0000   0.3014
  -7.000  -0.3428   0.09551   0.08937  -0.0199   1.0000   0.3130
  -6.750  -0.3606   0.09449   0.08852  -0.0167   1.0000   0.3226
  -6.500  -0.3806   0.09420   0.08838  -0.0127   1.0000   0.3340
  -6.250  -0.3746   0.09139   0.08562  -0.0100   1.0000   0.3469
  -6.000  -0.3823   0.08972   0.08407  -0.0065   1.0000   0.3578
  -5.750  -0.4348   0.09168   0.08627  -0.0011   1.0000   0.3665
  -5.500  -0.4386   0.08978   0.08444   0.0023   1.0000   0.3820
  -5.250  -0.4499   0.08840   0.08317   0.0056   1.0000   0.3979
  -4.500  -0.4200   0.05737   0.05108  -0.0492   1.0000   0.1774
  -4.000  -0.3374   0.04400   0.03595  -0.0639   1.0000   0.1310
  -3.750  -0.3073   0.04105   0.03246  -0.0663   1.0000   0.1305
  -3.500  -0.2770   0.03866   0.02951  -0.0682   1.0000   0.1315
  -3.250  -0.2480   0.03668   0.02703  -0.0694   1.0000   0.1325
  -3.000  -0.2209   0.03498   0.02497  -0.0699   1.0000   0.1345
  -2.750  -0.1976   0.03371   0.02365  -0.0699   1.0000   0.1400
  -2.500  -0.1732   0.03281   0.02247  -0.0698   1.0000   0.1499
  -2.250  -0.1514   0.03204   0.02163  -0.0690   1.0000   0.1635
  -2.000  -0.1298   0.03117   0.02095  -0.0682   1.0000   0.1843
  -1.750  -0.1001   0.02999   0.02015  -0.0690   1.0000   0.2561
  -1.500  -0.0952   0.02850   0.02144  -0.0611   1.0000   0.7276
  -1.250  -0.1078   0.02878   0.02176  -0.0512   1.0000   0.8163
  -1.000  -0.1194   0.02847   0.02147  -0.0422   1.0000   0.8866
  -0.750  -0.1217   0.02723   0.02029  -0.0371   1.0000   1.0000
  -0.500  -0.0744   0.02839   0.02086  -0.0430   0.9933   1.0000
  -0.250  -0.0325   0.02942   0.02144  -0.0478   0.9867   1.0000
   0.000   0.0072   0.03045   0.02210  -0.0521   0.9803   1.0000
   0.250   0.0487   0.03161   0.02292  -0.0566   0.9738   1.0000
   0.500   0.0813   0.03249   0.02354  -0.0595   0.9677   1.0000
   0.750   0.1215   0.03370   0.02451  -0.0637   0.9613   1.0000
   1.000   0.1500   0.03456   0.02519  -0.0657   0.9550   1.0000
   1.250   0.1892   0.03582   0.02624  -0.0696   0.9484   1.0000
   1.500   0.2148   0.03671   0.02700  -0.0711   0.9418   1.0000
   1.750   0.2537   0.03803   0.02817  -0.0748   0.9347   1.0000
   2.000   0.2765   0.03896   0.02900  -0.0758   0.9280   1.0000
   2.250   0.3176   0.04038   0.03031  -0.0797   0.9197   1.0000
   2.500   0.3360   0.04130   0.03118  -0.0800   0.9125   1.0000
   2.750   0.3724   0.04266   0.03245  -0.0830   0.9033   1.0000
   3.000   0.3960   0.04377   0.03353  -0.0840   0.8947   1.0000
   3.250   0.4247   0.04504   0.03478  -0.0858   0.8850   1.0000
   3.500   0.4629   0.04643   0.03616  -0.0888   0.8741   1.0000
   3.750   0.4858   0.04761   0.03734  -0.0896   0.8631   1.0000
   4.000   0.5112   0.04888   0.03863  -0.0907   0.8511   1.0000
   4.250   0.5407   0.05018   0.03996  -0.0922   0.8381   1.0000
   4.500   0.5714   0.05147   0.04130  -0.0938   0.8242   1.0000
   4.750   0.6020   0.05270   0.04260  -0.0953   0.8092   1.0000
   5.000   0.6317   0.05391   0.04388  -0.0964   0.7935   1.0000
   5.250   0.6614   0.05505   0.04514  -0.0974   0.7766   1.0000
   5.500   0.6936   0.05606   0.04625  -0.0985   0.7587   1.0000
   5.750   0.7324   0.05679   0.04711  -0.0999   0.7403   1.0000
   6.000   0.7741   0.05721   0.04772  -0.1012   0.7213   1.0000
   6.250   0.7928   0.05825   0.04888  -0.1003   0.6998   1.0000
   6.500   0.8386   0.05793   0.04877  -0.1011   0.6789   1.0000
   6.750   0.8734   0.05782   0.04887  -0.1007   0.6566   1.0000
   7.000   0.9216   0.05640   0.04772  -0.1004   0.6337   1.0000
   7.250   0.9721   0.05412   0.04576  -0.0994   0.6101   1.0000
   7.500   1.0807   0.04545   0.03763  -0.0994   0.5873   1.0000
   7.750   1.1756   0.03759   0.03023  -0.0994   0.5499   1.0000
   8.000   1.2272   0.03295   0.02566  -0.0965   0.4935   1.0000
   8.250   1.2378   0.03207   0.02450  -0.0912   0.4278   1.0000
   8.500   1.2497   0.03273   0.02434  -0.0870   0.3578   1.0000
   8.750   1.2603   0.03479   0.02584  -0.0841   0.3052   1.0000
   9.000   1.2785   0.03706   0.02770  -0.0826   0.2651   1.0000
   9.250   1.3039   0.03946   0.02991  -0.0821   0.2342   1.0000
   9.500   1.3350   0.04197   0.03216  -0.0826   0.2093   1.0000
   9.750   1.3607   0.04466   0.03496  -0.0824   0.1924   1.0000
  10.000   1.3836   0.04737   0.03776  -0.0819   0.1783   1.0000
  10.250   1.4134   0.05057   0.04096  -0.0825   0.1667   1.0000
  10.500   1.4178   0.05350   0.04447  -0.0796   0.1601   1.0000
  10.750   1.4395   0.05685   0.04786  -0.0793   0.1516   1.0000
  11.000   1.4363   0.06038   0.05196  -0.0760   0.1483   1.0000
  11.250   1.4347   0.06401   0.05600  -0.0732   0.1448   1.0000
  11.500   1.4567   0.06800   0.05994  -0.0734   0.1383   1.0000
  11.750   1.4373   0.07172   0.06415  -0.0692   0.1372   1.0000
  12.000   1.4146   0.07553   0.06832  -0.0651   0.1366   1.0000
  12.250   1.3893   0.07970   0.07280  -0.0617   0.1365   1.0000
  12.500   1.3620   0.08445   0.07782  -0.0593   0.1367   1.0000
  12.750   1.3331   0.08990   0.08350  -0.0582   0.1372   1.0000
  13.000   1.3036   0.09613   0.08994  -0.0582   0.1379   1.0000
  13.250   1.2760   0.10313   0.09708  -0.0594   0.1386   1.0000
  13.500   1.0486   0.15004   0.14377  -0.0926   0.1803   1.0000
  13.750   1.0503   0.15679   0.15055  -0.0950   0.1814   1.0000
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