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NREL's S810 Airfoil (s810-nr) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NREL's S810 Airfoil (s810-nr)
Reynolds number: 100,000
Max Cl/Cd: 27.1 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s810-nr-100000-n5.txt
Download as CSV file: xf-s810-nr-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S810 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4353   0.09798   0.09311  -0.0779   0.8883   0.0494
 -12.000  -0.4488   0.09289   0.08792  -0.0806   0.8802   0.0493
 -11.750  -0.4656   0.08813   0.08303  -0.0826   0.8733   0.0493
 -11.500  -0.4849   0.08383   0.07859  -0.0838   0.8670   0.0496
 -11.250  -0.5066   0.08009   0.07468  -0.0842   0.8611   0.0502
 -11.000  -0.5219   0.07692   0.07134  -0.0839   0.8563   0.0503
 -10.750  -0.5511   0.07530   0.06948  -0.0822   0.8503   0.0516
 -10.500  -0.5858   0.07544   0.06932  -0.0781   0.8445   0.0525
 -10.250  -0.6110   0.07542   0.06902  -0.0739   0.8399   0.0528
 -10.000  -0.6287   0.07511   0.06838  -0.0700   0.8356   0.0531
  -9.750  -0.5983   0.06391   0.05748  -0.0742   0.8343   0.0560
  -8.750  -0.5620   0.05260   0.04479  -0.0655   0.8228   0.0272
  -8.500  -0.5498   0.04922   0.04120  -0.0646   0.8206   0.0258
  -8.250  -0.5364   0.04660   0.03833  -0.0633   0.8185   0.0247
  -8.000  -0.5197   0.04401   0.03543  -0.0621   0.8166   0.0236
  -7.750  -0.4986   0.04164   0.03274  -0.0612   0.8151   0.0226
  -7.500  -0.4731   0.03936   0.03016  -0.0608   0.8133   0.0220
  -7.250  -0.4434   0.03729   0.02781  -0.0610   0.8117   0.0217
  -7.000  -0.4135   0.03561   0.02596  -0.0615   0.8101   0.0230
  -6.750  -0.3801   0.03413   0.02426  -0.0624   0.8086   0.0250
  -6.500  -0.3173   0.03201   0.02195  -0.0665   0.8081   0.0257
  -6.250  -0.2578   0.03094   0.02078  -0.0689   0.8077   0.0262
  -6.000  -0.2146   0.03051   0.02032  -0.0693   0.8065   0.0268
  -5.750  -0.1819   0.03043   0.02021  -0.0685   0.8052   0.0279
  -5.500  -0.1596   0.03031   0.02009  -0.0670   0.8036   0.0291
  -5.250  -0.1489   0.02971   0.01946  -0.0650   0.8020   0.0321
  -5.000  -0.1383   0.02905   0.01872  -0.0634   0.8006   0.0348
  -4.750  -0.1289   0.02841   0.01798  -0.0618   0.7986   0.0372
  -4.500  -0.1200   0.02777   0.01722  -0.0600   0.7966   0.0394
  -4.250  -0.1135   0.02707   0.01644  -0.0579   0.7946   0.0425
  -4.000  -0.1071   0.02645   0.01575  -0.0558   0.7925   0.0493
  -3.750  -0.1050   0.02578   0.01505  -0.0529   0.7902   0.0627
  -3.500  -0.1188   0.02477   0.01425  -0.0480   0.7879   0.1156
  -3.250  -0.1434   0.02336   0.01333  -0.0421   0.7853   0.2650
  -3.000  -0.1609   0.02364   0.01517  -0.0342   0.7822   0.5779
  -2.750  -0.1469   0.02566   0.01709  -0.0308   0.7797   0.6345
  -2.500  -0.0981   0.02953   0.02095  -0.0293   0.7790   0.6611
  -2.250  -0.0498   0.03167   0.02301  -0.0297   0.7783   0.6712
  -2.000  -0.0533   0.03077   0.02198  -0.0270   0.7760   0.6778
  -1.750  -0.0306   0.03074   0.02186  -0.0266   0.7746   0.6791
  -1.500  -0.0079   0.03063   0.02166  -0.0264   0.7732   0.6805
  -1.250   0.0052   0.03069   0.02167  -0.0248   0.7707   0.6824
  -1.000   0.0097   0.03084   0.02181  -0.0222   0.7672   0.6855
  -0.750   0.0167   0.03049   0.02136  -0.0205   0.7640   0.6900
  -0.500   0.0336   0.03028   0.02108  -0.0199   0.7619   0.6923
  -0.250   0.0571   0.03028   0.02104  -0.0197   0.7603   0.6935
   0.000   0.0826   0.03026   0.02098  -0.0199   0.7590   0.6949
   0.250   0.0810   0.03082   0.02157  -0.0162   0.7538   0.6973
   0.500   0.0927   0.03098   0.02171  -0.0146   0.7501   0.6997
   0.750   0.1137   0.03089   0.02159  -0.0145   0.7477   0.7020
   1.000   0.1394   0.03067   0.02130  -0.0154   0.7459   0.7046
   1.250   0.1678   0.03056   0.02118  -0.0162   0.7446   0.7064
   1.500   0.1571   0.03143   0.02212  -0.0111   0.7365   0.7082
   1.750   0.1803   0.03156   0.02226  -0.0110   0.7339   0.7098
   2.000   0.2083   0.03156   0.02228  -0.0116   0.7319   0.7114
   2.250   0.2392   0.03149   0.02225  -0.0127   0.7305   0.7130
   2.500   0.2277   0.03226   0.02303  -0.0080   0.7210   0.7156
   2.750   0.2576   0.03221   0.02300  -0.0091   0.7187   0.7176
   3.000   0.2915   0.03209   0.02291  -0.0109   0.7170   0.7199
   3.500   0.3134   0.03291   0.02389  -0.0070   0.7048   0.7230
   3.750   0.3471   0.03281   0.02388  -0.0082   0.7029   0.7244
   4.250   0.3787   0.03340   0.02462  -0.0062   0.6902   0.7280
   4.500   0.4156   0.03313   0.02448  -0.0078   0.6883   0.7298
   5.000   0.4552   0.03345   0.02498  -0.0069   0.6750   0.7343
   5.500   0.4989   0.03345   0.02526  -0.0056   0.6613   0.7374
   6.000   0.5515   0.03275   0.02490  -0.0052   0.6465   0.7408
   6.250   0.5649   0.03285   0.02513  -0.0036   0.6342   0.7429
   6.750   0.6024   0.03243   0.02498  -0.0017   0.6081   0.7478
   7.000   0.6209   0.03204   0.02481  -0.0002   0.5931   0.7496
   7.250   0.6294   0.03231   0.02524   0.0019   0.5728   0.7515
   7.500   0.6480   0.03193   0.02503   0.0032   0.5519   0.7535
   7.750   0.6719   0.03123   0.02446   0.0042   0.5239   0.7556
   8.000   0.7359   0.02716   0.02004   0.0039   0.4311   0.7576
   8.250   0.7460   0.02761   0.01986   0.0064   0.3345   0.7598
   8.500   0.7467   0.02906   0.02089   0.0088   0.2663   0.7622
   8.750   0.7489   0.03047   0.02198   0.0111   0.2071   0.7641
   9.000   0.7560   0.03172   0.02300   0.0127   0.1620   0.7663
   9.250   0.7650   0.03294   0.02406   0.0141   0.1292   0.7687
   9.500   0.7751   0.03417   0.02519   0.0152   0.1047   0.7713
   9.750   0.7860   0.03543   0.02638   0.0161   0.0881   0.7739
  10.000   0.7968   0.03674   0.02765   0.0170   0.0766   0.7763
  10.250   0.8082   0.03793   0.02899   0.0181   0.0686   0.7782
  10.500   0.8184   0.03931   0.03045   0.0192   0.0623   0.7804
  10.750   0.8305   0.04058   0.03183   0.0199   0.0549   0.7829
  11.000   0.8423   0.04197   0.03331   0.0206   0.0479   0.7857
  11.250   0.8523   0.04347   0.03480   0.0209   0.0404   0.7887
  11.500   0.8646   0.04480   0.03631   0.0215   0.0340   0.7915
  11.750   0.8727   0.04652   0.03812   0.0223   0.0288   0.7942
  12.000   0.8833   0.04823   0.04001   0.0230   0.0248   0.7972
  12.250   0.8912   0.05023   0.04210   0.0236   0.0222   0.8004
  12.500   0.9020   0.05250   0.04449   0.0243   0.0204   0.8034
  12.750   0.9150   0.05460   0.04689   0.0250   0.0189   0.8061
  13.000   0.9249   0.05693   0.04950   0.0256   0.0178   0.8090
  13.250   0.9309   0.05940   0.05225   0.0261   0.0168   0.8124
  13.500   0.9336   0.06189   0.05491   0.0262   0.0159   0.8160
  13.750   0.9330   0.06456   0.05770   0.0262   0.0149   0.8195
  14.000   0.9315   0.06782   0.06113   0.0264   0.0144   0.8230
  14.250   0.9262   0.07168   0.06538   0.0264   0.0139   0.8268
  14.500   0.9196   0.07583   0.06984   0.0259   0.0137   0.8309
  14.750   0.9082   0.08062   0.07496   0.0253   0.0134   0.8345
  15.000   0.8945   0.08586   0.08050   0.0240   0.0134   0.8384
  15.250   0.8791   0.09172   0.08663   0.0220   0.0133   0.8426
  15.500   0.8628   0.09806   0.09323   0.0192   0.0134   0.8469
  15.750   0.8426   0.10552   0.10095   0.0156   0.0134   0.8509
  16.000   0.8225   0.11367   0.10931   0.0110   0.0135   0.8554
  16.500   0.7803   0.13301   0.12898  -0.0006   0.0140   0.8640
  16.750   0.7653   0.14199   0.13803  -0.0058   0.0144   0.8696
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