Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NREL's S817 Airfoil (s817-nr) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NREL's S817 Airfoil (s817-nr)
Reynolds number: 500,000
Max Cl/Cd: 101.1 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s817-nr-500000-n5.txt
Download as CSV file: xf-s817-nr-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S817 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2203   0.07541   0.07180  -0.1079   0.7338   0.0053
  -9.500  -0.2686   0.06308   0.05935  -0.1117   0.7310   0.0040
  -9.250  -0.2830   0.06000   0.05620  -0.1107   0.7296   0.0040
  -9.000  -0.2989   0.05718   0.05329  -0.1086   0.7282   0.0040
  -8.750  -0.3113   0.05503   0.05108  -0.1055   0.7269   0.0039
  -8.500  -0.3193   0.05215   0.04809  -0.1030   0.7255   0.0039
  -8.250  -0.3232   0.04917   0.04499  -0.1006   0.7240   0.0038
  -8.000  -0.3237   0.04613   0.04180  -0.0982   0.7226   0.0038
  -7.750  -0.3212   0.04309   0.03859  -0.0959   0.7214   0.0038
  -7.500  -0.3184   0.03948   0.03475  -0.0931   0.7202   0.0037
  -7.250  -0.3140   0.03534   0.03031  -0.0899   0.7191   0.0038
  -7.000  -0.3065   0.03089   0.02551  -0.0868   0.7181   0.0038
  -6.750  -0.2967   0.02067   0.01421  -0.0822   0.7172   0.0043
  -6.500  -0.2728   0.01952   0.01288  -0.0820   0.7163   0.0045
  -6.250  -0.2469   0.01826   0.01141  -0.0819   0.7155   0.0046
  -6.000  -0.2213   0.01752   0.01053  -0.0819   0.7146   0.0049
  -5.750  -0.1954   0.01681   0.00968  -0.0819   0.7138   0.0053
  -5.500  -0.1697   0.01609   0.00885  -0.0818   0.7130   0.0059
  -5.250  -0.1447   0.01556   0.00821  -0.0816   0.7121   0.0063
  -5.000  -0.1227   0.01472   0.00731  -0.0808   0.7111   0.0067
  -4.750  -0.1012   0.01417   0.00673  -0.0800   0.7101   0.0070
  -4.500  -0.0800   0.01371   0.00623  -0.0792   0.7089   0.0073
  -4.250  -0.0589   0.01329   0.00577  -0.0783   0.7079   0.0080
  -4.000  -0.0374   0.01291   0.00534  -0.0775   0.7070   0.0088
  -3.750  -0.0162   0.01251   0.00492  -0.0766   0.7060   0.0105
  -3.500   0.0071   0.01225   0.00461  -0.0761   0.7052   0.0126
  -3.250   0.0309   0.01202   0.00439  -0.0758   0.7043   0.0166
  -3.000   0.0547   0.01178   0.00414  -0.0755   0.7035   0.0206
  -2.750   0.0793   0.01157   0.00391  -0.0752   0.7027   0.0261
  -2.500   0.1038   0.01135   0.00372  -0.0750   0.7020   0.0399
  -2.250   0.1287   0.01115   0.00358  -0.0749   0.7011   0.0639
  -2.000   0.1538   0.01095   0.00344  -0.0748   0.7003   0.0958
  -1.750   0.1547   0.00861   0.00283  -0.0717   0.6992   0.6205
  -1.500   0.1811   0.00868   0.00303  -0.0715   0.6984   0.6862
  -1.250   0.2089   0.00880   0.00316  -0.0717   0.6977   0.7037
  -1.000   0.2372   0.00890   0.00321  -0.0721   0.6969   0.7131
  -0.750   0.2653   0.00899   0.00330  -0.0724   0.6961   0.7187
  -0.500   0.2937   0.00908   0.00335  -0.0728   0.6952   0.7250
  -0.250   0.3219   0.00915   0.00340  -0.0732   0.6943   0.7292
   0.000   0.3503   0.00919   0.00343  -0.0736   0.6933   0.7310
   0.250   0.3789   0.00921   0.00343  -0.0742   0.6923   0.7318
   0.500   0.4075   0.00924   0.00345  -0.0747   0.6915   0.7326
   0.750   0.4361   0.00928   0.00347  -0.0753   0.6907   0.7335
   1.000   0.4648   0.00932   0.00350  -0.0758   0.6899   0.7345
   1.250   0.4934   0.00936   0.00354  -0.0764   0.6891   0.7356
   1.500   0.5221   0.00940   0.00358  -0.0770   0.6883   0.7368
   1.750   0.5509   0.00944   0.00362  -0.0776   0.6874   0.7379
   2.000   0.5797   0.00950   0.00369  -0.0782   0.6867   0.7390
   2.250   0.6085   0.00957   0.00376  -0.0788   0.6860   0.7400
   2.500   0.6373   0.00965   0.00384  -0.0795   0.6853   0.7410
   2.750   0.6650   0.00972   0.00396  -0.0799   0.6843   0.7420
   3.000   0.6923   0.00977   0.00410  -0.0802   0.6832   0.7430
   3.250   0.7196   0.00985   0.00424  -0.0806   0.6821   0.7440
   3.500   0.7470   0.00993   0.00439  -0.0809   0.6810   0.7451
   3.750   0.7744   0.01001   0.00455  -0.0813   0.6798   0.7462
   4.000   0.8018   0.01002   0.00462  -0.0816   0.6773   0.7474
   4.250   0.8308   0.00986   0.00446  -0.0820   0.6724   0.7486
   4.500   0.8549   0.00973   0.00440  -0.0815   0.6647   0.7500
   4.750   0.8803   0.00951   0.00421  -0.0812   0.6549   0.7515
   5.000   0.9020   0.00934   0.00409  -0.0801   0.6388   0.7531
   5.250   0.9233   0.00926   0.00402  -0.0790   0.6171   0.7548
   5.500   0.9412   0.00931   0.00400  -0.0773   0.5803   0.7565
   5.750   0.9393   0.00988   0.00425  -0.0716   0.5125   0.7584
   6.000   0.9176   0.01088   0.00492  -0.0624   0.4465   0.7607
   6.250   0.9019   0.01207   0.00587  -0.0549   0.3906   0.7631
   6.500   0.8848   0.01356   0.00709  -0.0479   0.3304   0.7657
   6.750   0.8743   0.01508   0.00836  -0.0426   0.2762   0.7682
   7.000   0.8693   0.01656   0.00961  -0.0384   0.2271   0.7706
   7.250   0.8679   0.01796   0.01082  -0.0350   0.1816   0.7727
   7.500   0.8707   0.01922   0.01192  -0.0323   0.1445   0.7748
   7.750   0.8770   0.02034   0.01292  -0.0301   0.1146   0.7770
   8.000   0.8866   0.02132   0.01384  -0.0283   0.0941   0.7793
   8.250   0.8984   0.02220   0.01468  -0.0269   0.0798   0.7818
   8.500   0.9112   0.02304   0.01550  -0.0256   0.0686   0.7842
   8.750   0.9251   0.02384   0.01629  -0.0245   0.0595   0.7866
   9.000   0.9382   0.02466   0.01713  -0.0233   0.0520   0.7890
   9.250   0.9514   0.02550   0.01799  -0.0221   0.0452   0.7918
   9.500   0.9660   0.02628   0.01882  -0.0212   0.0412   0.7947
   9.750   0.9800   0.02713   0.01969  -0.0202   0.0373   0.7977
  10.000   0.9929   0.02806   0.02063  -0.0191   0.0335   0.8006
  10.250   1.0081   0.02882   0.02149  -0.0183   0.0314   0.8034
  10.500   1.0219   0.02970   0.02243  -0.0174   0.0289   0.8066
  10.750   1.0347   0.03067   0.02344  -0.0164   0.0265   0.8101
  11.000   1.0479   0.03164   0.02448  -0.0155   0.0246   0.8137
  11.250   1.0617   0.03257   0.02550  -0.0146   0.0235   0.8172
  11.500   1.0758   0.03348   0.02650  -0.0139   0.0219   0.8211
  11.750   1.0892   0.03447   0.02749  -0.0131   0.0194   0.8255
  12.250   1.1153   0.03652   0.02973  -0.0116   0.0167   0.8348
  12.500   1.1295   0.03744   0.03063  -0.0111   0.0131   0.8405
  12.750   1.1432   0.03844   0.03172  -0.0104   0.0113   0.8465
  13.000   1.1550   0.03958   0.03289  -0.0097   0.0092   0.8538
  13.250   1.1670   0.04072   0.03415  -0.0090   0.0083   0.8618
  13.500   1.1783   0.04192   0.03542  -0.0082   0.0071   0.8717
  13.750   1.1884   0.04316   0.03678  -0.0073   0.0062   0.8840
  14.250   1.2103   0.04587   0.03980  -0.0062   0.0043   0.9451
  14.750   1.2280   0.04920   0.04328  -0.0054   0.0021   1.0000
  15.000   1.2339   0.05119   0.04535  -0.0047   0.0014   1.0000
  15.250   1.2425   0.05297   0.04725  -0.0043   0.0013   1.0000
  15.500   1.2493   0.05496   0.04934  -0.0039   0.0012   1.0000
  15.750   1.2542   0.05719   0.05168  -0.0035   0.0010   1.0000
  16.000   1.2578   0.05961   0.05424  -0.0031   0.0008   1.0000
  16.250   1.2638   0.06182   0.05657  -0.0029   0.0009   1.0000
  16.500   1.2641   0.06475   0.05965  -0.0027   0.0007   1.0000
  16.750   1.2656   0.06761   0.06266  -0.0026   0.0007   1.0000
  17.000   1.2680   0.07042   0.06561  -0.0028   0.0007   1.0000
  17.250   1.2661   0.07386   0.06922  -0.0030   0.0006   1.0000
  17.500   1.2662   0.07711   0.07261  -0.0035   0.0007   1.0000
  17.750   1.2629   0.08094   0.07660  -0.0041   0.0006   1.0000
  18.000   1.2560   0.08543   0.08127  -0.0051   0.0006   1.0000
  18.250   1.2505   0.08984   0.08584  -0.0063   0.0006   1.0000
  18.500   1.2420   0.09486   0.09103  -0.0078   0.0005   1.0000
  18.750   1.2311   0.10045   0.09679  -0.0099   0.0005   1.0000
  19.000   1.2188   0.10652   0.10305  -0.0124   0.0005   1.0000
  19.250   1.2035   0.11340   0.11011  -0.0155   0.0005   1.0000
<< Back to NREL's S817 Airfoil (s817-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S817 Airfoil (s817-nr)