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 S809 Airfoil (s809-nr) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NREL's S809 Airfoil (s809-nr)
Reynolds number: 100,000
Max Cl/Cd: 26.85 at α=9°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s809-nr-100000-n5.txt
Download as CSV file: xf-s809-nr-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S809 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
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.6466   0.11054   0.10494  -0.0495   1.0000   0.0178
 -15.500  -0.6691   0.10380   0.09801  -0.0522   1.0000   0.0175
 -15.250  -0.6909   0.09761   0.09160  -0.0542   1.0000   0.0172
 -15.000  -0.7128   0.09185   0.08557  -0.0557   1.0000   0.0168
 -14.750  -0.7404   0.08601   0.07938  -0.0566   1.0000   0.0164
 -14.250  -0.7600   0.07874   0.07164  -0.0572   1.0000   0.0162
 -14.000  -0.7644   0.07530   0.06803  -0.0571   1.0000   0.0161
 -13.750  -0.7661   0.07202   0.06455  -0.0568   1.0000   0.0161
 -13.500  -0.7637   0.06919   0.06155  -0.0565   1.0000   0.0160
 -13.250  -0.7597   0.06624   0.05839  -0.0560   1.0000   0.0161
 -13.000  -0.7504   0.06367   0.05562  -0.0555   1.0000   0.0160
 -12.750  -0.7374   0.06140   0.05315  -0.0549   1.0000   0.0161
 -12.500  -0.7186   0.05938   0.05092  -0.0542   1.0000   0.0161
 -12.250  -0.6949   0.05781   0.04918  -0.0535   1.0000   0.0162
 -12.000  -0.6614   0.05687   0.04822  -0.0528   1.0000   0.0166
 -11.750  -0.6311   0.05639   0.04770  -0.0519   1.0000   0.0168
 -11.500  -0.5960   0.05606   0.04738  -0.0517   0.9805   0.0175
 -11.250  -0.5252   0.05646   0.04747  -0.0572   0.8405   0.0186
 -11.000  -0.4905   0.05698   0.04767  -0.0571   0.8000   0.0212
 -10.750  -0.4629   0.05772   0.04832  -0.0561   0.7791   0.0222
 -10.500  -0.4396   0.05805   0.04853  -0.0551   0.7654   0.0244
 -10.250  -0.4227   0.05760   0.04791  -0.0543   0.7555   0.0258
 -10.000  -0.4106   0.05651   0.04670  -0.0539   0.7477   0.0270
  -9.750  -0.4008   0.05514   0.04525  -0.0535   0.7412   0.0313
  -9.500  -0.3919   0.05364   0.04366  -0.0532   0.7358   0.0350
  -9.250  -0.3831   0.05212   0.04205  -0.0529   0.7309   0.0398
  -9.000  -0.3762   0.05045   0.04037  -0.0525   0.7266   0.0473
  -8.500  -0.3993   0.04441   0.03507  -0.0505   0.7204   0.1604
  -8.000  -0.2955   0.05954   0.05130  -0.0441   0.7120   0.4777
  -7.750  -0.2744   0.05875   0.05034  -0.0443   0.7093   0.4799
  -7.500  -0.2600   0.05769   0.04911  -0.0442   0.7071   0.4831
  -7.250  -0.2697   0.05543   0.04676  -0.0432   0.7049   0.4889
  -7.000  -0.2450   0.05479   0.04600  -0.0436   0.7024   0.4901
  -6.750  -0.2212   0.05419   0.04528  -0.0439   0.7002   0.4916
  -6.500  -0.2004   0.05346   0.04442  -0.0440   0.6981   0.4934
  -6.250  -0.1841   0.05250   0.04336  -0.0439   0.6960   0.4955
  -6.000  -0.2025   0.05006   0.04086  -0.0421   0.6942   0.5027
  -5.750  -0.1788   0.04950   0.04019  -0.0423   0.6923   0.5038
  -5.500  -0.1556   0.04893   0.03950  -0.0424   0.6905   0.5049
  -5.250  -0.1346   0.04828   0.03879  -0.0425   0.6887   0.5061
  -5.000  -0.1155   0.04756   0.03802  -0.0424   0.6868   0.5076
  -4.750  -0.0980   0.04685   0.03727  -0.0422   0.6851   0.5100
  -4.500  -0.1264   0.04402   0.03442  -0.0393   0.6835   0.5177
  -4.250  -0.1028   0.04356   0.03389  -0.0393   0.6820   0.5185
  -4.000  -0.0796   0.04313   0.03342  -0.0394   0.6806   0.5195
  -3.750  -0.0570   0.04273   0.03298  -0.0393   0.6793   0.5208
  -3.000  -0.0643   0.03849   0.02861  -0.0341   0.6757   0.5332
  -2.750  -0.0397   0.03832   0.02842  -0.0340   0.6746   0.5341
  -2.500  -0.0172   0.03810   0.02823  -0.0338   0.6731   0.5353
  -2.250   0.0031   0.03779   0.02793  -0.0335   0.6714   0.5368
  -1.750  -0.0060   0.03367   0.02369  -0.0320   0.6681   0.5484
  -1.500   0.0184   0.03365   0.02370  -0.0319   0.6669   0.5492
  -1.250   0.0420   0.03359   0.02366  -0.0317   0.6658   0.5502
  -1.000   0.0647   0.03348   0.02356  -0.0315   0.6646   0.5515
  -0.750   0.0859   0.03324   0.02333  -0.0314   0.6635   0.5531
  -0.500   0.1058   0.03282   0.02291  -0.0314   0.6622   0.5550
  -0.250   0.1241   0.03216   0.02221  -0.0315   0.6609   0.5577
   0.000   0.1363   0.03054   0.02043  -0.0327   0.6596   0.5637
   0.250   0.1593   0.03065   0.02062  -0.0325   0.6584   0.5647
   0.500   0.1806   0.03078   0.02085  -0.0321   0.6569   0.5658
   0.750   0.2014   0.03088   0.02104  -0.0317   0.6548   0.5670
   1.000   0.2225   0.03091   0.02112  -0.0315   0.6528   0.5684
   1.250   0.2441   0.03087   0.02114  -0.0315   0.6509   0.5699
   1.500   0.2664   0.03077   0.02107  -0.0316   0.6490   0.5718
   1.750   0.2898   0.03059   0.02091  -0.0321   0.6472   0.5740
   2.000   0.3146   0.03026   0.02055  -0.0331   0.6456   0.5771
   2.250   0.3406   0.03007   0.02036  -0.0339   0.6442   0.5794
   2.500   0.3589   0.03045   0.02088  -0.0332   0.6415   0.5805
   2.750   0.3744   0.03089   0.02147  -0.0322   0.6381   0.5817
   3.000   0.3942   0.03118   0.02186  -0.0318   0.6351   0.5829
   3.250   0.4175   0.03133   0.02211  -0.0318   0.6327   0.5843
   3.500   0.4438   0.03138   0.02223  -0.0321   0.6305   0.5858
   3.750   0.4718   0.03138   0.02229  -0.0327   0.6287   0.5877
   4.000   0.4811   0.03206   0.02310  -0.0313   0.6233   0.5898
   4.250   0.4993   0.03237   0.02350  -0.0311   0.6187   0.5921
   4.500   0.5280   0.03227   0.02344  -0.0321   0.6157   0.5944
   4.750   0.5585   0.03218   0.02347  -0.0326   0.6134   0.5955
   5.000   0.5629   0.03309   0.02456  -0.0302   0.6062   0.5965
   5.250   0.5847   0.03327   0.02488  -0.0297   0.6014   0.5978
   5.500   0.6189   0.03292   0.02465  -0.0306   0.5984   0.5992
   6.000   0.6543   0.03336   0.02538  -0.0286   0.5849   0.6027
   6.250   0.6995   0.03228   0.02442  -0.0305   0.5814   0.6050
   6.500   0.7016   0.03293   0.02520  -0.0278   0.5704   0.6070
   6.750   0.7574   0.03102   0.02338  -0.0307   0.5652   0.6095
   7.000   0.7572   0.03152   0.02407  -0.0272   0.5529   0.6107
   7.250   0.7642   0.03162   0.02434  -0.0244   0.5413   0.6119
   7.500   0.7760   0.03131   0.02420  -0.0220   0.5299   0.6132
   7.750   0.7668   0.03210   0.02512  -0.0177   0.5162   0.6145
   8.000   0.7379   0.03525   0.02837  -0.0141   0.4951   0.6158
   8.250   0.7341   0.03701   0.03026  -0.0127   0.4737   0.6173
   8.500   0.7441   0.03763   0.03099  -0.0117   0.4522   0.6192
   8.750   0.7767   0.03621   0.02965  -0.0112   0.4261   0.6217
   9.000   0.8411   0.03133   0.02422  -0.0101   0.3482   0.6249
   9.500   0.8318   0.03496   0.02728  -0.0056   0.2550   0.6276
   9.750   0.8271   0.03710   0.02921  -0.0040   0.2170   0.6290
  10.000   0.8250   0.03917   0.03107  -0.0027   0.1824   0.6304
  10.250   0.8258   0.04109   0.03283  -0.0017   0.1524   0.6320
  10.500   0.8298   0.04284   0.03445  -0.0009   0.1275   0.6337
  10.750   0.8344   0.04462   0.03611  -0.0002   0.1079   0.6355
  11.000   0.8405   0.04636   0.03776   0.0003   0.0925   0.6375
  11.250   0.8467   0.04815   0.03951   0.0007   0.0807   0.6395
  11.500   0.8545   0.04981   0.04121   0.0011   0.0710   0.6414
  11.750   0.8611   0.05157   0.04302   0.0017   0.0639   0.6431
  12.000   0.8672   0.05345   0.04493   0.0021   0.0578   0.6450
  12.250   0.8755   0.05519   0.04677   0.0024   0.0530   0.6472
  12.500   0.8837   0.05702   0.04867   0.0026   0.0488   0.6496
  12.750   0.8907   0.05903   0.05068   0.0027   0.0456   0.6520
  13.000   0.9016   0.06076   0.05255   0.0028   0.0421   0.6545
  13.250   0.9107   0.06266   0.05456   0.0028   0.0395   0.6568
  13.500   0.9189   0.06463   0.05656   0.0029   0.0375   0.6587
  13.750   0.9305   0.06640   0.05850   0.0031   0.0354   0.6610
  14.000   0.9400   0.06843   0.06071   0.0031   0.0332   0.6635
  14.250   0.9482   0.07063   0.06300   0.0028   0.0315   0.6661
  14.500   0.9567   0.07285   0.06524   0.0026   0.0302   0.6690
  14.750   0.9679   0.07499   0.06751   0.0026   0.0291   0.6719
  15.000   0.9741   0.07770   0.07051   0.0024   0.0280   0.6743
  15.250   0.9774   0.08077   0.07383   0.0019   0.0268   0.6770
  15.500   0.9791   0.08400   0.07728   0.0011   0.0258   0.6800
  15.750   0.9795   0.08737   0.08080   0.0000   0.0249   0.6833
  16.250   0.9826   0.09404   0.08767  -0.0021   0.0235   0.6896
  16.500   0.9751   0.09896   0.09287  -0.0038   0.0231   0.6922
  16.750   0.9642   0.10459   0.09881  -0.0061   0.0229   0.6947
  17.000   0.9505   0.11089   0.10540  -0.0091   0.0226   0.6972
  17.250   0.9343   0.11796   0.11274  -0.0129   0.0225   0.6994
  17.500   0.9160   0.12577   0.12080  -0.0174   0.0225   0.7015
  17.750   0.8938   0.13488   0.13016  -0.0229   0.0225   0.7028
  18.000   0.8680   0.14557   0.14105  -0.0297   0.0227   0.7035
  18.250   0.8383   0.15831   0.15392  -0.0378   0.0230   0.7035
<< Back to NREL's S809 Airfoil (s809-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S809 Airfoil (s809-nr)