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 S807 Airfoil (s807-nr) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NREL's S807 Airfoil (s807-nr)
Reynolds number: 200,000
Max Cl/Cd: 59.37 at α=10.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s807-nr-200000-n5.txt
Download as CSV file: xf-s807-nr-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S807 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -19.750  -0.7814   0.15115   0.14656  -0.0217   1.0000   0.0184
 -19.500  -0.8189   0.13863   0.13377  -0.0286   1.0000   0.0183
 -19.250  -0.8410   0.13024   0.12517  -0.0330   1.0000   0.0184
 -19.000  -0.8588   0.12310   0.11785  -0.0365   1.0000   0.0185
 -18.750  -0.8716   0.11718   0.11176  -0.0392   1.0000   0.0186
 -18.500  -0.8829   0.11169   0.10608  -0.0416   1.0000   0.0188
 -18.250  -0.8925   0.10667   0.10088  -0.0436   1.0000   0.0190
 -18.000  -0.8993   0.10228   0.09633  -0.0452   1.0000   0.0191
 -17.750  -0.9049   0.09814   0.09201  -0.0465   1.0000   0.0193
 -17.500  -0.9071   0.09465   0.08839  -0.0474   1.0000   0.0194
 -17.250  -0.9049   0.09207   0.08578  -0.0477   1.0000   0.0197
 -17.000  -0.9021   0.08956   0.08323  -0.0480   1.0000   0.0199
 -16.750  -0.8996   0.08701   0.08064  -0.0483   1.0000   0.0202
 -16.500  -0.8970   0.08449   0.07806  -0.0486   1.0000   0.0204
 -16.250  -0.8936   0.08212   0.07564  -0.0487   1.0000   0.0207
 -16.000  -0.8907   0.07969   0.07314  -0.0489   1.0000   0.0211
 -15.750  -0.8875   0.07731   0.07069  -0.0490   1.0000   0.0215
 -15.500  -0.8838   0.07505   0.06835  -0.0491   1.0000   0.0220
 -15.250  -0.8791   0.07296   0.06618  -0.0489   1.0000   0.0225
 -15.000  -0.8739   0.07096   0.06409  -0.0487   1.0000   0.0229
 -14.750  -0.8680   0.06909   0.06213  -0.0483   1.0000   0.0233
 -14.500  -0.8626   0.06732   0.06037  -0.0478   1.0000   0.0238
 -14.250  -0.8574   0.06548   0.05853  -0.0474   1.0000   0.0242
 -14.000  -0.8521   0.06365   0.05668  -0.0470   1.0000   0.0246
 -13.750  -0.8471   0.06183   0.05482  -0.0465   1.0000   0.0250
 -13.500  -0.8418   0.06007   0.05303  -0.0460   1.0000   0.0255
 -13.250  -0.8367   0.05831   0.05123  -0.0454   1.0000   0.0262
 -13.000  -0.8316   0.05659   0.04946  -0.0448   1.0000   0.0269
 -12.750  -0.8262   0.05491   0.04773  -0.0441   1.0000   0.0276
 -12.500  -0.8230   0.05309   0.04591  -0.0434   1.0000   0.0283
 -12.250  -0.8204   0.05125   0.04406  -0.0426   1.0000   0.0288
 -12.000  -0.8169   0.04952   0.04231  -0.0418   1.0000   0.0297
 -11.750  -0.8137   0.04784   0.04059  -0.0409   1.0000   0.0307
 -11.500  -0.8110   0.04616   0.03888  -0.0399   1.0000   0.0317
 -11.250  -0.8084   0.04458   0.03725  -0.0387   1.0000   0.0326
 -11.000  -0.8087   0.04285   0.03552  -0.0374   1.0000   0.0335
 -10.750  -0.8092   0.04117   0.03384  -0.0360   1.0000   0.0347
 -10.500  -0.8094   0.03958   0.03224  -0.0344   1.0000   0.0361
 -10.250  -0.8100   0.03803   0.03066  -0.0327   1.0000   0.0376
 -10.000  -0.8123   0.03644   0.02906  -0.0308   1.0000   0.0397
  -9.750  -0.8161   0.03486   0.02748  -0.0286   1.0000   0.0416
  -9.500  -0.8210   0.03332   0.02594  -0.0262   1.0000   0.0444
  -9.250  -0.8294   0.03175   0.02437  -0.0233   1.0000   0.0472
  -9.000  -0.8429   0.03019   0.02282  -0.0196   1.0000   0.0499
  -8.750  -0.8570   0.02862   0.02123  -0.0158   1.0000   0.0529
  -8.500  -0.8607   0.02667   0.01930  -0.0145   1.0000   0.0580
  -8.250  -0.8554   0.02464   0.01728  -0.0148   1.0000   0.0666
  -8.000  -0.8430   0.02272   0.01539  -0.0161   1.0000   0.0812
  -7.750  -0.8070   0.02084   0.01366  -0.0216   0.9955   0.1132
  -7.500  -0.7574   0.01827   0.01148  -0.0306   0.9865   0.1869
  -7.250  -0.7116   0.01572   0.00964  -0.0386   0.9806   0.3128
  -7.000  -0.6764   0.01540   0.00958  -0.0406   0.9751   0.3738
  -6.750  -0.6360   0.01541   0.00958  -0.0432   0.9707   0.4039
  -6.500  -0.5997   0.01554   0.00967  -0.0448   0.9654   0.4226
  -6.250  -0.5645   0.01557   0.00961  -0.0462   0.9594   0.4349
  -6.000  -0.5229   0.01580   0.00975  -0.0488   0.9550   0.4488
  -5.750  -0.4955   0.01629   0.01031  -0.0478   0.9460   0.4585
  -5.500  -0.4569   0.01624   0.01015  -0.0499   0.9400   0.4657
  -5.250  -0.4306   0.01615   0.01005  -0.0493   0.9289   0.4681
  -5.000  -0.4033   0.01596   0.00983  -0.0490   0.9163   0.4705
  -4.750  -0.3757   0.01570   0.00949  -0.0489   0.9009   0.4731
  -4.500  -0.3446   0.01535   0.00904  -0.0495   0.8842   0.4759
  -4.250  -0.3056   0.01489   0.00844  -0.0517   0.8648   0.4787
  -4.000  -0.2498   0.01444   0.00781  -0.0569   0.8341   0.4811
  -3.750  -0.1578   0.01423   0.00726  -0.0691   0.7647   0.4829
  -3.500  -0.1173   0.01437   0.00701  -0.0714   0.6907   0.4843
  -3.250  -0.0905   0.01454   0.00686  -0.0711   0.6339   0.4859
  -3.000  -0.0656   0.01469   0.00675  -0.0705   0.5885   0.4878
  -2.500  -0.0142   0.01485   0.00645  -0.0698   0.5220   0.4921
  -2.250   0.0124   0.01487   0.00626  -0.0697   0.4982   0.4942
  -2.000   0.0399   0.01486   0.00606  -0.0699   0.4787   0.4963
  -1.750   0.0668   0.01489   0.00598  -0.0697   0.4621   0.4977
  -1.500   0.0938   0.01495   0.00595  -0.0695   0.4476   0.4991
  -1.250   0.1210   0.01500   0.00595  -0.0694   0.4345   0.5007
  -1.000   0.1484   0.01507   0.00594  -0.0693   0.4232   0.5025
  -0.750   0.1758   0.01514   0.00592  -0.0692   0.4127   0.5044
  -0.500   0.2039   0.01517   0.00589  -0.0693   0.4034   0.5064
  -0.250   0.2317   0.01523   0.00585  -0.0694   0.3955   0.5084
   0.000   0.2602   0.01526   0.00581  -0.0696   0.3885   0.5105
   0.250   0.2888   0.01530   0.00577  -0.0698   0.3817   0.5126
   0.500   0.3167   0.01538   0.00577  -0.0699   0.3760   0.5143
   0.750   0.3447   0.01543   0.00584  -0.0699   0.3700   0.5159
   1.000   0.3723   0.01553   0.00593  -0.0699   0.3643   0.5177
   1.250   0.3998   0.01566   0.00601  -0.0698   0.3593   0.5197
   1.500   0.4282   0.01573   0.00610  -0.0699   0.3543   0.5219
   1.750   0.4565   0.01582   0.00618  -0.0700   0.3497   0.5240
   2.000   0.4846   0.01593   0.00625  -0.0701   0.3457   0.5262
   2.250   0.5129   0.01608   0.00632  -0.0703   0.3422   0.5285
   2.500   0.5418   0.01617   0.00642  -0.0705   0.3385   0.5308
   2.750   0.5696   0.01627   0.00657  -0.0705   0.3346   0.5324
   3.000   0.5973   0.01640   0.00673  -0.0705   0.3309   0.5343
   3.250   0.6248   0.01657   0.00689  -0.0704   0.3274   0.5365
   3.500   0.6526   0.01676   0.00707  -0.0705   0.3243   0.5390
   3.750   0.6809   0.01690   0.00727  -0.0706   0.3212   0.5416
   4.000   0.7091   0.01705   0.00746  -0.0707   0.3181   0.5443
   4.250   0.7373   0.01722   0.00763  -0.0708   0.3152   0.5469
   4.500   0.7650   0.01740   0.00784  -0.0708   0.3126   0.5490
   4.750   0.7924   0.01761   0.00807  -0.0707   0.3100   0.5510
   5.000   0.8199   0.01783   0.00834  -0.0707   0.3072   0.5533
   5.250   0.8474   0.01800   0.00862  -0.0707   0.3042   0.5558
   5.500   0.8749   0.01821   0.00890  -0.0706   0.3015   0.5588
   5.750   0.9024   0.01843   0.00917  -0.0706   0.2990   0.5620
   6.000   0.9299   0.01866   0.00942  -0.0706   0.2963   0.5652
   6.250   0.9567   0.01891   0.00971  -0.0705   0.2937   0.5676
   6.500   0.9837   0.01919   0.01005  -0.0704   0.2913   0.5702
   6.750   1.0102   0.01941   0.01042  -0.0702   0.2884   0.5730
   7.000   1.0364   0.01962   0.01074  -0.0700   0.2850   0.5761
   7.250   1.0623   0.01983   0.01101  -0.0697   0.2814   0.5794
   7.500   1.0882   0.02006   0.01126  -0.0694   0.2778   0.5828
   7.750   1.1135   0.02032   0.01161  -0.0690   0.2744   0.5857
   8.000   1.1382   0.02053   0.01200  -0.0685   0.2705   0.5891
   8.250   1.1628   0.02074   0.01233  -0.0680   0.2663   0.5929
   8.500   1.1870   0.02096   0.01258  -0.0675   0.2622   0.5969
   8.750   1.2109   0.02121   0.01290  -0.0669   0.2579   0.6006
   9.000   1.2339   0.02141   0.01330  -0.0661   0.2528   0.6038
   9.250   1.2564   0.02162   0.01361  -0.0653   0.2478   0.6076
   9.500   1.2783   0.02188   0.01391  -0.0644   0.2431   0.6119
   9.750   1.3007   0.02212   0.01433  -0.0635   0.2368   0.6167
  10.000   1.3209   0.02235   0.01466  -0.0623   0.2306   0.6209
  10.250   1.3416   0.02263   0.01509  -0.0613   0.2238   0.6256
  10.500   1.3607   0.02292   0.01547  -0.0600   0.2161   0.6308
  10.750   1.3795   0.02326   0.01593  -0.0586   0.2079   0.6357
  11.000   1.3939   0.02362   0.01636  -0.0566   0.1991   0.6404
  11.250   1.4095   0.02407   0.01693  -0.0549   0.1882   0.6460
  11.500   1.4227   0.02465   0.01755  -0.0528   0.1760   0.6521
  11.750   1.4326   0.02538   0.01833  -0.0505   0.1628   0.6579
  12.000   1.4400   0.02633   0.01928  -0.0480   0.1498   0.6647
  12.250   1.4449   0.02746   0.02044  -0.0454   0.1378   0.6713
  12.500   1.4476   0.02878   0.02180  -0.0428   0.1274   0.6784
  12.750   1.4481   0.03032   0.02339  -0.0403   0.1181   0.6859
  13.000   1.4490   0.03191   0.02508  -0.0381   0.1101   0.6934
  13.250   1.4454   0.03393   0.02718  -0.0359   0.1036   0.7021
  13.500   1.4426   0.03605   0.02943  -0.0343   0.0973   0.7111
  14.000   1.4275   0.04183   0.03547  -0.0324   0.0878   0.7328
  14.250   1.4161   0.04565   0.03945  -0.0326   0.0839   0.7451
  14.500   1.4004   0.05041   0.04436  -0.0336   0.0809   0.7583
  14.750   1.3883   0.05511   0.04926  -0.0351   0.0779   0.7745
  15.000   1.3722   0.06054   0.05489  -0.0369   0.0753   0.7931
  15.250   1.3526   0.06651   0.06104  -0.0391   0.0730   0.8162
  15.500   1.3308   0.07244   0.06718  -0.0408   0.0713   0.8563
  15.750   1.3089   0.07790   0.07282  -0.0421   0.0697   1.0000
  16.000   1.2962   0.08352   0.07855  -0.0446   0.0673   1.0000
  16.250   1.2830   0.08932   0.08443  -0.0472   0.0649   1.0000
<< Back to NREL's S807 Airfoil (s807-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S807 Airfoil (s807-nr)