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NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NREL's S803 Airfoil (s803-nr)
Reynolds number: 500,000
Max Cl/Cd: 118.38 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s803-nr-500000.txt
Download as CSV file: xf-s803-nr-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2635   0.08699   0.08492  -0.0487   0.9955   0.0250
  -9.250  -0.2693   0.07815   0.07609  -0.0561   0.9939   0.0261
  -8.000  -0.3634   0.05008   0.04763  -0.0951   0.9752   0.0268
  -7.750  -0.3371   0.04747   0.04500  -0.0993   0.9729   0.0273
  -7.500  -0.3189   0.04520   0.04268  -0.1015   0.9649   0.0280
  -7.250  -0.2918   0.04099   0.03827  -0.1073   0.9612   0.0295
  -7.000  -0.2748   0.03281   0.02925  -0.1138   0.9506   0.0338
  -6.750  -0.2480   0.02405   0.01961  -0.1176   0.9457   0.0271
  -6.500  -0.2201   0.02045   0.01571  -0.1187   0.9393   0.0240
  -6.250  -0.1849   0.01764   0.01249  -0.1209   0.9360   0.0235
  -6.000  -0.1507   0.01602   0.01063  -0.1225   0.9305   0.0238
  -5.750  -0.1140   0.01486   0.00931  -0.1246   0.9245   0.0246
  -5.500  -0.0718   0.01385   0.00815  -0.1277   0.9203   0.0255
  -5.250  -0.0353   0.01296   0.00714  -0.1296   0.9108   0.0260
  -5.000   0.0035   0.01194   0.00602  -0.1321   0.9016   0.0265
  -4.750   0.0403   0.01099   0.00499  -0.1344   0.8902   0.0277
  -4.500   0.0731   0.01052   0.00444  -0.1356   0.8761   0.0291
  -4.250   0.1041   0.01019   0.00403  -0.1363   0.8615   0.0310
  -4.000   0.1336   0.00990   0.00363  -0.1367   0.8468   0.0324
  -3.750   0.1624   0.00954   0.00316  -0.1369   0.8325   0.0349
  -3.500   0.1906   0.00933   0.00288  -0.1370   0.8189   0.0392
  -3.250   0.2191   0.00896   0.00256  -0.1373   0.8064   0.0662
  -3.000   0.2476   0.00842   0.00236  -0.1379   0.7950   0.1679
  -2.750   0.2760   0.00807   0.00222  -0.1384   0.7841   0.2570
  -2.500   0.3045   0.00763   0.00210  -0.1390   0.7732   0.3704
  -2.250   0.3331   0.00717   0.00209  -0.1396   0.7635   0.5260
  -2.000   0.3608   0.00718   0.00220  -0.1395   0.7541   0.6045
  -1.750   0.3884   0.00726   0.00228  -0.1393   0.7452   0.6365
  -1.500   0.4162   0.00740   0.00233  -0.1391   0.7375   0.6580
  -1.250   0.4437   0.00750   0.00241  -0.1389   0.7292   0.6759
  -1.000   0.4712   0.00763   0.00248  -0.1386   0.7221   0.6883
  -0.750   0.4988   0.00769   0.00253  -0.1385   0.7145   0.6970
  -0.500   0.5267   0.00781   0.00257  -0.1384   0.7082   0.7065
  -0.250   0.5542   0.00787   0.00264  -0.1382   0.7018   0.7135
   0.000   0.5821   0.00796   0.00268  -0.1381   0.6954   0.7209
   0.250   0.6098   0.00806   0.00275  -0.1380   0.6898   0.7275
   0.500   0.6374   0.00812   0.00282  -0.1379   0.6837   0.7345
   0.750   0.6652   0.00822   0.00287  -0.1378   0.6780   0.7410
   1.000   0.6924   0.00829   0.00296  -0.1376   0.6719   0.7478
   1.250   0.7201   0.00837   0.00301  -0.1375   0.6653   0.7543
   1.500   0.7472   0.00845   0.00308  -0.1373   0.6588   0.7589
   1.750   0.7742   0.00849   0.00314  -0.1371   0.6513   0.7636
   2.000   0.8020   0.00860   0.00319  -0.1371   0.6443   0.7680
   2.250   0.8288   0.00861   0.00324  -0.1368   0.6362   0.7715
   2.500   0.8557   0.00870   0.00331  -0.1366   0.6285   0.7751
   2.750   0.8825   0.00874   0.00338  -0.1363   0.6202   0.7791
   3.000   0.9098   0.00884   0.00345  -0.1362   0.6126   0.7831
   3.250   0.9362   0.00887   0.00352  -0.1359   0.6037   0.7867
   3.500   0.9626   0.00895   0.00362  -0.1356   0.5952   0.7908
   3.750   0.9891   0.00903   0.00371  -0.1353   0.5863   0.7952
   4.000   1.0157   0.00910   0.00380  -0.1351   0.5764   0.7997
   4.250   1.0414   0.00918   0.00392  -0.1346   0.5664   0.8038
   4.500   1.0670   0.00928   0.00403  -0.1341   0.5551   0.8090
   4.750   1.0925   0.00939   0.00415  -0.1337   0.5409   0.8147
   5.000   1.1168   0.00949   0.00428  -0.1329   0.5247   0.8199
   5.250   1.1412   0.00964   0.00444  -0.1323   0.5051   0.8262
   5.500   1.1638   0.00985   0.00460  -0.1313   0.4761   0.8326
   5.750   1.1829   0.01027   0.00485  -0.1296   0.4260   0.8401
   6.000   1.1978   0.01103   0.00530  -0.1274   0.3617   0.8487
   6.250   1.2127   0.01188   0.00586  -0.1252   0.3019   0.8592
   6.500   1.2277   0.01264   0.00640  -0.1231   0.2523   0.8709
   6.750   1.2428   0.01332   0.00691  -0.1209   0.2118   0.8863
   7.000   1.2559   0.01387   0.00738  -0.1183   0.1794   0.9127
   7.250   1.2706   0.01441   0.00783  -0.1160   0.1520   1.0000
   7.500   1.2896   0.01507   0.00838  -0.1148   0.1293   1.0000
   7.750   1.3071   0.01576   0.00895  -0.1133   0.1113   1.0000
   8.000   1.3236   0.01639   0.00951  -0.1115   0.0974   1.0000
   8.250   1.3390   0.01703   0.01010  -0.1095   0.0863   1.0000
   8.500   1.3551   0.01762   0.01069  -0.1077   0.0782   1.0000
   8.750   1.3689   0.01833   0.01138  -0.1055   0.0711   1.0000
   9.000   1.3839   0.01896   0.01203  -0.1035   0.0655   1.0000
   9.250   1.3953   0.01982   0.01288  -0.1010   0.0602   1.0000
   9.500   1.4109   0.02043   0.01355  -0.0993   0.0566   1.0000
   9.750   1.4225   0.02128   0.01441  -0.0970   0.0529   1.0000
  10.000   1.4307   0.02237   0.01554  -0.0944   0.0496   1.0000
  10.250   1.4451   0.02309   0.01634  -0.0927   0.0473   1.0000
  10.500   1.4574   0.02397   0.01727  -0.0908   0.0449   1.0000
  10.750   1.4649   0.02520   0.01852  -0.0884   0.0425   1.0000
  11.000   1.4688   0.02676   0.02014  -0.0858   0.0405   1.0000
  11.250   1.4826   0.02763   0.02112  -0.0844   0.0390   1.0000
  11.500   1.4948   0.02865   0.02219  -0.0830   0.0370   1.0000
  11.750   1.5049   0.02986   0.02343  -0.0815   0.0351   1.0000
  12.000   1.5057   0.03191   0.02553  -0.0793   0.0331   1.0000
  12.250   1.5165   0.03317   0.02689  -0.0780   0.0319   1.0000
  12.500   1.5272   0.03448   0.02829  -0.0769   0.0306   1.0000
  12.750   1.5368   0.03592   0.02980  -0.0758   0.0293   1.0000
  13.000   1.5445   0.03758   0.03152  -0.0747   0.0280   1.0000
  13.250   1.5459   0.03992   0.03392  -0.0734   0.0267   1.0000
  13.500   1.5473   0.04237   0.03647  -0.0722   0.0257   1.0000
  13.750   1.5564   0.04406   0.03828  -0.0715   0.0248   1.0000
  14.000   1.5639   0.04595   0.04027  -0.0709   0.0236   1.0000
  14.250   1.5710   0.04794   0.04233  -0.0704   0.0225   1.0000
  14.500   1.5743   0.05041   0.04485  -0.0699   0.0215   1.0000
  14.750   1.5666   0.05425   0.04877  -0.0693   0.0203   1.0000
  15.000   1.5753   0.05623   0.05089  -0.0692   0.0195   1.0000
  15.250   1.5809   0.05864   0.05341  -0.0691   0.0185   1.0000
  15.500   1.5850   0.06129   0.05615  -0.0692   0.0175   1.0000
  15.750   1.5845   0.06461   0.05953  -0.0694   0.0166   1.0000
  16.000   1.5741   0.06939   0.06441  -0.0699   0.0158   1.0000
  16.250   1.5771   0.07247   0.06764  -0.0704   0.0151   1.0000
  16.500   1.5769   0.07608   0.07138  -0.0710   0.0143   1.0000
  16.750   1.5753   0.07997   0.07538  -0.0720   0.0136   1.0000
  17.000   1.5711   0.08437   0.07987  -0.0732   0.0131   1.0000
  17.250   1.5613   0.08979   0.08539  -0.0748   0.0126   1.0000
  17.500   1.5484   0.09589   0.09162  -0.0769   0.0122   1.0000
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