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NREL's S810 Airfoil (s810-nr) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NREL's S810 Airfoil (s810-nr)
Reynolds number: 200,000
Max Cl/Cd: 50 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s810-nr-200000.txt
Download as CSV file: xf-s810-nr-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4696   0.09438   0.09041  -0.0843   0.8826   0.0285
 -12.000  -0.4798   0.09078   0.08671  -0.0849   0.8771   0.0284
 -11.750  -0.4959   0.08760   0.08337  -0.0850   0.8723   0.0285
 -11.500  -0.5128   0.08466   0.08030  -0.0847   0.8674   0.0285
 -11.250  -0.5357   0.08239   0.07786  -0.0832   0.8625   0.0285
 -11.000  -0.5458   0.07974   0.07507  -0.0820   0.8588   0.0285
 -10.750  -0.5647   0.07784   0.07301  -0.0795   0.8551   0.0286
 -10.500  -0.5801   0.07605   0.07108  -0.0765   0.8514   0.0286
 -10.250  -0.5950   0.06867   0.06360  -0.0754   0.8489   0.0292
 -10.000  -0.5776   0.06142   0.05644  -0.0778   0.8473   0.0308
  -9.750  -0.5815   0.05913   0.05404  -0.0756   0.8448   0.0313
  -9.500  -0.5826   0.05681   0.05158  -0.0737   0.8427   0.0321
  -9.250  -0.5823   0.05456   0.04921  -0.0719   0.8404   0.0336
  -9.000  -0.5802   0.05279   0.04725  -0.0699   0.8381   0.0361
  -8.750  -0.5757   0.05184   0.04602  -0.0673   0.8359   0.0383
  -8.500  -0.5533   0.03697   0.03112  -0.0619   0.8310   0.0416
  -8.250  -0.5370   0.03302   0.02720  -0.0625   0.8299   0.0437
  -8.000  -0.5260   0.03056   0.02462  -0.0614   0.8286   0.0466
  -7.750  -0.5165   0.02988   0.02364  -0.0591   0.8269   0.0515
  -7.500  -0.5086   0.02643   0.01994  -0.0578   0.8255   0.0555
  -7.250  -0.4891   0.02392   0.01744  -0.0580   0.8242   0.0597
  -7.000  -0.4804   0.02240   0.01558  -0.0559   0.8227   0.0691
  -6.750  -0.4586   0.02030   0.01349  -0.0562   0.8213   0.0763
  -6.500  -0.4438   0.01838   0.01143  -0.0555   0.8198   0.0901
  -5.500  -0.2958   0.02791   0.01945  -0.0588   0.8173   0.0403
  -5.250  -0.1834   0.02505   0.01679  -0.0680   0.8184   0.0385
  -5.000  -0.1584   0.02460   0.01637  -0.0669   0.8174   0.0377
  -4.750  -0.1440   0.02405   0.01582  -0.0651   0.8163   0.0378
  -4.500  -0.1351   0.02338   0.01514  -0.0629   0.8152   0.0385
  -4.250  -0.1295   0.02269   0.01445  -0.0607   0.8139   0.0392
  -4.000  -0.1270   0.02214   0.01387  -0.0583   0.8122   0.0401
  -3.750  -0.1356   0.02169   0.01336  -0.0541   0.8097   0.0411
  -3.500  -0.1393   0.02134   0.01292  -0.0504   0.8079   0.0453
  -3.250  -0.1310   0.02124   0.01274  -0.0482   0.8064   0.0515
  -3.000  -0.1227   0.02098   0.01240  -0.0457   0.8046   0.0645
  -2.750  -0.1370   0.01941   0.01165  -0.0407   0.8026   0.3144
  -2.500  -0.1339   0.02134   0.01497  -0.0347   0.8015   0.6482
  -2.250   0.0367   0.03282   0.02674  -0.0400   0.8038   0.6866
  -2.000  -0.0084   0.03087   0.02476  -0.0329   0.8014   0.6897
  -1.750   0.0562   0.03238   0.02621  -0.0362   0.8012   0.6951
  -1.500   0.0653   0.03260   0.02643  -0.0343   0.7992   0.6976
  -1.250  -0.0245   0.03205   0.02596  -0.0209   0.7922   0.7064
  -1.000  -0.0058   0.03208   0.02595  -0.0199   0.7903   0.7075
  -0.750   0.0170   0.03199   0.02580  -0.0197   0.7888   0.7086
  -0.500   0.0419   0.03188   0.02566  -0.0198   0.7876   0.7100
  -0.250  -0.0476   0.03291   0.02675  -0.0036   0.7778   0.7153
   0.000  -0.0226   0.03238   0.02613  -0.0052   0.7758   0.7178
   0.250   0.0145   0.03186   0.02550  -0.0084   0.7743   0.7202
   0.500   0.0558   0.03176   0.02538  -0.0109   0.7733   0.7211
   0.750   0.0967   0.03162   0.02522  -0.0133   0.7725   0.7220
   1.000   0.0402   0.03266   0.02629  -0.0014   0.7616   0.7244
   1.250   0.0793   0.03249   0.02610  -0.0039   0.7599   0.7256
   1.500   0.1230   0.03229   0.02588  -0.0070   0.7588   0.7269
   1.750   0.1012   0.03295   0.02652  -0.0012   0.7486   0.7299
   2.000   0.1393   0.03269   0.02623  -0.0038   0.7465   0.7320
   2.250   0.1842   0.03234   0.02584  -0.0076   0.7451   0.7338
   2.500   0.2282   0.03213   0.02568  -0.0104   0.7441   0.7346
   2.750   0.2110   0.03288   0.02646  -0.0045   0.7326   0.7360
   3.000   0.2529   0.03260   0.02622  -0.0068   0.7311   0.7371
   3.250   0.2964   0.03237   0.02605  -0.0094   0.7299   0.7384
   3.500   0.2891   0.03303   0.02675  -0.0052   0.7183   0.7405
   3.750   0.3036   0.03338   0.02712  -0.0041   0.7103   0.7424
   4.000   0.3360   0.03318   0.02696  -0.0054   0.7059   0.7440
   4.250   0.3797   0.03262   0.02646  -0.0081   0.7039   0.7456
   4.500   0.4300   0.03186   0.02579  -0.0117   0.7027   0.7472
   4.750   0.4825   0.03093   0.02496  -0.0153   0.7012   0.7485
   5.000   0.4854   0.03116   0.02526  -0.0118   0.6897   0.7501
   5.250   0.4990   0.03123   0.02542  -0.0099   0.6796   0.7517
   5.500   0.5604   0.02942   0.02380  -0.0137   0.6781   0.7531
   5.750   0.6396   0.02674   0.02129  -0.0197   0.6777   0.7543
   6.000   0.7137   0.02395   0.01867  -0.0251   0.6756   0.7557
   6.250   0.7518   0.02232   0.01714  -0.0258   0.6642   0.7574
   6.500   0.7916   0.02049   0.01541  -0.0268   0.6504   0.7593
   6.750   0.8174   0.01955   0.01460  -0.0262   0.6359   0.7614
   7.000   0.8324   0.01891   0.01412  -0.0238   0.6173   0.7632
   7.250   0.8266   0.01896   0.01433  -0.0182   0.5917   0.7652
   7.500   0.8615   0.01723   0.01195  -0.0171   0.4714   0.7669
   7.750   0.8443   0.01830   0.01252  -0.0101   0.3957   0.7689
   8.000   0.8273   0.01995   0.01376  -0.0045   0.3277   0.7712
   8.250   0.8136   0.02181   0.01523  -0.0002   0.2624   0.7734
   8.750   0.7972   0.02564   0.01829   0.0063   0.1443   0.7774
   9.000   0.7960   0.02730   0.01973   0.0088   0.1099   0.7794
   9.250   0.7993   0.02879   0.02109   0.0108   0.0919   0.7815
   9.500   0.8070   0.03009   0.02234   0.0122   0.0791   0.7836
   9.750   0.8192   0.03114   0.02341   0.0131   0.0685   0.7858
  10.000   0.8309   0.03228   0.02456   0.0139   0.0603   0.7881
  10.250   0.8410   0.03359   0.02584   0.0147   0.0520   0.7901
  10.500   0.8551   0.03447   0.02688   0.0155   0.0456   0.7920
  10.750   0.8633   0.03600   0.02846   0.0169   0.0374   0.7940
  11.000   0.8711   0.03773   0.03019   0.0182   0.0292   0.7963
  11.250   0.8839   0.03898   0.03154   0.0190   0.0245   0.7990
  11.500   0.8983   0.04063   0.03321   0.0197   0.0222   0.8017
  11.750   0.9232   0.04255   0.03531   0.0202   0.0200   0.8040
  12.000   0.9432   0.04423   0.03723   0.0209   0.0189   0.8061
  12.250   0.9617   0.04632   0.03960   0.0215   0.0182   0.8084
  12.500   0.9753   0.04883   0.04240   0.0223   0.0178   0.8109
  12.750   0.9832   0.05176   0.04568   0.0232   0.0176   0.8135
  13.000   0.9844   0.05526   0.04950   0.0243   0.0176   0.8161
  13.250   0.9786   0.05911   0.05369   0.0254   0.0177   0.8185
  13.500   0.9674   0.06313   0.05805   0.0265   0.0179   0.8206
  13.750   0.9515   0.06769   0.06292   0.0274   0.0181   0.8229
  14.000   0.9343   0.07239   0.06791   0.0276   0.0183   0.8254
  14.250   0.9132   0.07780   0.07358   0.0273   0.0185   0.8279
  14.500   0.8930   0.08338   0.07939   0.0261   0.0188   0.8305
  14.750   0.8700   0.08973   0.08596   0.0241   0.0190   0.8327
  15.000   0.8470   0.09651   0.09295   0.0214   0.0192   0.8348
  15.250   0.8232   0.10420   0.10083   0.0175   0.0195   0.8370
  15.500   0.7998   0.11274   0.10954   0.0125   0.0197   0.8393
  15.750   0.7734   0.12326   0.12017   0.0059   0.0200   0.8411
  16.000   0.7475   0.13515   0.13213  -0.0014   0.0206   0.8426
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