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NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NREL's S803 Airfoil (s803-nr)
Reynolds number: 1,000,000
Max Cl/Cd: 140.3 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s803-nr-1000000.txt
Download as CSV file: xf-s803-nr-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3485   0.08589   0.08429  -0.0529   0.9956   0.0139
  -9.000  -0.3383   0.08028   0.07868  -0.0591   0.9943   0.0142
  -8.750  -0.4374   0.02733   0.02436  -0.1139   0.9735   0.0121
  -8.500  -0.4203   0.02385   0.02042  -0.1155   0.9662   0.0123
  -8.250  -0.3946   0.01944   0.01557  -0.1187   0.9627   0.0128
  -8.000  -0.3615   0.01826   0.01428  -0.1209   0.9608   0.0132
  -7.750  -0.3396   0.01740   0.01335  -0.1203   0.9524   0.0136
  -7.500  -0.3076   0.01652   0.01237  -0.1218   0.9489   0.0141
  -7.250  -0.2779   0.01567   0.01140  -0.1226   0.9423   0.0147
  -7.000  -0.2416   0.01475   0.01033  -0.1248   0.9376   0.0153
  -6.750  -0.1989   0.01391   0.00934  -0.1284   0.9342   0.0158
  -6.500  -0.1584   0.01345   0.00876  -0.1313   0.9258   0.0160
  -6.250  -0.1194   0.01131   0.00642  -0.1346   0.9157   0.0167
  -6.000  -0.0833   0.01062   0.00565  -0.1367   0.9010   0.0174
  -5.750  -0.0519   0.01023   0.00517  -0.1377   0.8834   0.0181
  -5.500  -0.0233   0.00992   0.00475  -0.1379   0.8656   0.0189
  -5.250   0.0039   0.00959   0.00430  -0.1379   0.8484   0.0194
  -5.000   0.0306   0.00931   0.00391  -0.1378   0.8320   0.0198
  -4.750   0.0573   0.00907   0.00357  -0.1376   0.8166   0.0203
  -4.500   0.0842   0.00888   0.00328  -0.1374   0.8022   0.0206
  -4.250   0.1114   0.00846   0.00275  -0.1375   0.7890   0.0216
  -4.000   0.1387   0.00824   0.00246  -0.1374   0.7768   0.0230
  -3.750   0.1661   0.00811   0.00226  -0.1374   0.7653   0.0245
  -3.500   0.1936   0.00800   0.00207  -0.1373   0.7541   0.0257
  -3.250   0.2215   0.00786   0.00188  -0.1373   0.7434   0.0286
  -3.000   0.2495   0.00766   0.00172  -0.1374   0.7335   0.0459
  -2.750   0.2776   0.00733   0.00157  -0.1378   0.7238   0.1105
  -2.500   0.3062   0.00705   0.00148  -0.1382   0.7152   0.1758
  -2.250   0.3346   0.00678   0.00141  -0.1386   0.7069   0.2591
  -2.000   0.3636   0.00647   0.00134  -0.1392   0.6990   0.3488
  -1.750   0.3924   0.00613   0.00129  -0.1397   0.6914   0.4652
  -1.500   0.4214   0.00591   0.00133  -0.1401   0.6842   0.5701
  -1.250   0.4494   0.00594   0.00137  -0.1401   0.6773   0.6058
  -1.000   0.4778   0.00598   0.00142  -0.1402   0.6712   0.6305
  -0.750   0.5058   0.00604   0.00147  -0.1401   0.6649   0.6472
  -0.500   0.5338   0.00611   0.00151  -0.1401   0.6591   0.6581
  -0.250   0.5621   0.00615   0.00154  -0.1401   0.6533   0.6651
   0.000   0.5900   0.00623   0.00159  -0.1401   0.6475   0.6729
   0.250   0.6182   0.00629   0.00162  -0.1401   0.6417   0.6790
   0.500   0.6461   0.00634   0.00166  -0.1400   0.6351   0.6845
   0.750   0.6738   0.00643   0.00171  -0.1400   0.6285   0.6905
   1.000   0.7017   0.00647   0.00175  -0.1399   0.6214   0.6959
   1.250   0.7291   0.00656   0.00182  -0.1398   0.6145   0.7013
   1.500   0.7572   0.00662   0.00187  -0.1398   0.6075   0.7073
   2.000   0.8121   0.00674   0.00199  -0.1396   0.5927   0.7182
   2.250   0.8395   0.00684   0.00205  -0.1394   0.5855   0.7224
   2.500   0.8673   0.00687   0.00212  -0.1394   0.5782   0.7259
   2.750   0.8942   0.00696   0.00219  -0.1392   0.5698   0.7291
   3.000   0.9220   0.00701   0.00226  -0.1392   0.5620   0.7324
   3.250   0.9489   0.00712   0.00234  -0.1390   0.5534   0.7357
   3.500   0.9764   0.00719   0.00242  -0.1390   0.5438   0.7389
   3.750   1.0033   0.00727   0.00251  -0.1388   0.5341   0.7425
   4.000   1.0297   0.00739   0.00261  -0.1385   0.5209   0.7461
   4.250   1.0560   0.00753   0.00273  -0.1382   0.5042   0.7498
   4.500   1.0817   0.00771   0.00285  -0.1378   0.4826   0.7536
   4.750   1.1057   0.00798   0.00302  -0.1371   0.4503   0.7577
   5.000   1.1259   0.00856   0.00333  -0.1358   0.3905   0.7623
   5.250   1.1457   0.00922   0.00372  -0.1344   0.3332   0.7673
   5.500   1.1654   0.00987   0.00413  -0.1331   0.2815   0.7720
   5.750   1.1855   0.01048   0.00453  -0.1319   0.2371   0.7774
   6.000   1.2060   0.01105   0.00491  -0.1307   0.1995   0.7832
   6.250   1.2265   0.01157   0.00531  -0.1295   0.1688   0.7892
   6.500   1.2478   0.01203   0.00568  -0.1284   0.1451   0.7964
   7.000   1.2899   0.01293   0.00644  -0.1262   0.1090   0.8130
   7.250   1.3106   0.01335   0.00684  -0.1250   0.0949   0.8227
   7.500   1.3311   0.01377   0.00724  -0.1238   0.0834   0.8341
   7.750   1.3510   0.01419   0.00765  -0.1225   0.0738   0.8479
   8.000   1.3712   0.01454   0.00804  -0.1212   0.0672   0.8656
   8.250   1.3888   0.01492   0.00847  -0.1194   0.0601   0.8931
   8.500   1.4030   0.01512   0.00880  -0.1168   0.0558   1.0000
   8.750   1.4196   0.01565   0.00930  -0.1150   0.0501   1.0000
   9.000   1.4383   0.01603   0.00970  -0.1135   0.0475   1.0000
   9.250   1.4541   0.01655   0.01021  -0.1115   0.0437   1.0000
   9.500   1.4692   0.01712   0.01080  -0.1094   0.0404   1.0000
   9.750   1.4866   0.01755   0.01127  -0.1078   0.0385   1.0000
  10.000   1.5018   0.01812   0.01183  -0.1059   0.0358   1.0000
  10.250   1.5138   0.01887   0.01258  -0.1035   0.0327   1.0000
  10.500   1.5309   0.01934   0.01310  -0.1020   0.0316   1.0000
  10.750   1.5457   0.01993   0.01373  -0.1002   0.0300   1.0000
  11.000   1.5588   0.02065   0.01447  -0.0982   0.0284   1.0000
  11.250   1.5687   0.02159   0.01543  -0.0958   0.0265   1.0000
  11.500   1.5814   0.02237   0.01627  -0.0939   0.0256   1.0000
  11.750   1.5951   0.02310   0.01706  -0.0922   0.0247   1.0000
  12.000   1.6078   0.02392   0.01792  -0.0905   0.0236   1.0000
  12.250   1.6187   0.02489   0.01893  -0.0887   0.0224   1.0000
  12.500   1.6264   0.02614   0.02021  -0.0866   0.0209   1.0000
  12.750   1.6359   0.02730   0.02144  -0.0849   0.0200   1.0000
  13.000   1.6479   0.02830   0.02250  -0.0835   0.0193   1.0000
  13.250   1.6583   0.02946   0.02372  -0.0821   0.0184   1.0000
  13.500   1.6670   0.03080   0.02510  -0.0806   0.0174   1.0000
  13.750   1.6725   0.03248   0.02682  -0.0790   0.0163   1.0000
  14.000   1.6801   0.03403   0.02844  -0.0777   0.0155   1.0000
  14.250   1.6897   0.03544   0.02993  -0.0767   0.0147   1.0000
  14.500   1.6971   0.03709   0.03163  -0.0756   0.0138   1.0000
  14.750   1.7014   0.03911   0.03369  -0.0745   0.0128   1.0000
  15.000   1.7058   0.04119   0.03585  -0.0735   0.0119   1.0000
  15.250   1.7120   0.04313   0.03787  -0.0728   0.0111   1.0000
  15.500   1.7155   0.04542   0.04020  -0.0720   0.0102   1.0000
  15.750   1.7149   0.04826   0.04311  -0.0714   0.0093   1.0000
  16.000   1.7186   0.05068   0.04563  -0.0709   0.0087   1.0000
  16.250   1.7200   0.05343   0.04845  -0.0706   0.0081   1.0000
  16.500   1.7187   0.05662   0.05171  -0.0704   0.0075   1.0000
  16.750   1.7124   0.06057   0.05577  -0.0704   0.0070   1.0000
  17.000   1.7128   0.06374   0.05905  -0.0706   0.0068   1.0000
  17.250   1.7110   0.06730   0.06272  -0.0709   0.0065   1.0000
  17.500   1.7080   0.07112   0.06666  -0.0715   0.0062   1.0000
  17.750   1.7036   0.07529   0.07093  -0.0723   0.0060   1.0000
  18.000   1.6976   0.07980   0.07555  -0.0733   0.0058   1.0000
  18.250   1.6898   0.08471   0.08058  -0.0747   0.0056   1.0000
  18.500   1.6796   0.09020   0.08618  -0.0764   0.0054   1.0000
  18.750   1.6661   0.09644   0.09257  -0.0787   0.0053   1.0000
  19.000   1.6492   0.10349   0.09977  -0.0816   0.0051   1.0000
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