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NREL's S817 Airfoil (s817-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NREL's S817 Airfoil (s817-nr)
Reynolds number: 1,000,000
Max Cl/Cd: 137.26 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s817-nr-1000000.txt
Download as CSV file: xf-s817-nr-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S817 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1507   0.09332   0.09059  -0.0882   0.7384   0.0064
 -11.250  -0.1495   0.08916   0.08643  -0.0900   0.7376   0.0064
  -6.000  -0.2328   0.01747   0.01185  -0.0812   0.7185   0.0051
  -5.750  -0.2061   0.01583   0.00996  -0.0810   0.7176   0.0057
  -5.500  -0.1792   0.01478   0.00874  -0.0809   0.7167   0.0061
  -5.250  -0.1530   0.01425   0.00810  -0.0808   0.7158   0.0063
  -5.000  -0.1289   0.01319   0.00691  -0.0804   0.7148   0.0066
  -4.750  -0.1075   0.01247   0.00613  -0.0795   0.7138   0.0069
  -4.500  -0.0860   0.01194   0.00557  -0.0787   0.7132   0.0071
  -4.250  -0.0624   0.01164   0.00526  -0.0783   0.7126   0.0077
  -4.000  -0.0379   0.01141   0.00502  -0.0781   0.7119   0.0085
  -3.750  -0.0141   0.01113   0.00471  -0.0776   0.7111   0.0092
  -3.500   0.0054   0.01052   0.00406  -0.0764   0.7102   0.0107
  -3.250   0.0289   0.01020   0.00373  -0.0759   0.7093   0.0150
  -3.000   0.0547   0.01003   0.00355  -0.0759   0.7084   0.0178
  -2.750   0.0798   0.00980   0.00333  -0.0758   0.7075   0.0231
  -2.500   0.1051   0.00957   0.00314  -0.0757   0.7067   0.0368
  -2.250   0.1303   0.00932   0.00301  -0.0756   0.7060   0.0742
  -2.000   0.1509   0.00865   0.00280  -0.0750   0.7052   0.2298
  -1.750   0.1614   0.00685   0.00239  -0.0732   0.7043   0.6709
  -1.500   0.1901   0.00692   0.00246  -0.0736   0.7036   0.6915
  -1.250   0.2190   0.00703   0.00255  -0.0740   0.7028   0.7049
  -1.000   0.2478   0.00718   0.00269  -0.0744   0.7020   0.7170
  -0.750   0.2768   0.00733   0.00282  -0.0749   0.7011   0.7240
  -0.500   0.3060   0.00747   0.00290  -0.0755   0.7002   0.7269
  -0.250   0.3347   0.00756   0.00300  -0.0760   0.6994   0.7312
   0.000   0.3635   0.00762   0.00308  -0.0765   0.6989   0.7344
   0.250   0.3924   0.00768   0.00314  -0.0771   0.6983   0.7374
   0.500   0.4213   0.00769   0.00314  -0.0777   0.6976   0.7382
   0.750   0.4503   0.00771   0.00316  -0.0783   0.6968   0.7390
   1.000   0.4793   0.00774   0.00319  -0.0790   0.6960   0.7398
   1.250   0.5082   0.00777   0.00322  -0.0796   0.6953   0.7405
   1.500   0.5372   0.00781   0.00327  -0.0803   0.6945   0.7412
   1.750   0.5661   0.00785   0.00332  -0.0809   0.6936   0.7419
   2.000   0.5949   0.00786   0.00334  -0.0815   0.6927   0.7430
   2.250   0.6237   0.00788   0.00339  -0.0822   0.6918   0.7440
   2.500   0.6526   0.00791   0.00345  -0.0828   0.6910   0.7451
   2.750   0.6815   0.00796   0.00353  -0.0834   0.6902   0.7461
   3.000   0.7104   0.00801   0.00360  -0.0841   0.6893   0.7473
   3.250   0.7395   0.00804   0.00366  -0.0847   0.6882   0.7484
   3.500   0.7690   0.00811   0.00372  -0.0854   0.6856   0.7496
   3.750   0.7956   0.00792   0.00360  -0.0854   0.6809   0.7508
   4.000   0.8239   0.00766   0.00332  -0.0857   0.6742   0.7520
   4.250   0.8498   0.00745   0.00313  -0.0855   0.6653   0.7532
   4.500   0.8765   0.00730   0.00295  -0.0855   0.6564   0.7545
   4.750   0.9026   0.00722   0.00296  -0.0855   0.6498   0.7556
   5.000   0.9293   0.00721   0.00295  -0.0856   0.6436   0.7567
   5.250   0.9553   0.00715   0.00298  -0.0856   0.6342   0.7583
   5.500   0.9800   0.00714   0.00300  -0.0852   0.6193   0.7599
   5.750   0.9988   0.00728   0.00306  -0.0837   0.5814   0.7614
   6.000   0.9930   0.00822   0.00357  -0.0774   0.4918   0.7634
   6.250   0.9762   0.00925   0.00424  -0.0691   0.4176   0.7658
   6.500   0.9607   0.01033   0.00505  -0.0613   0.3557   0.7683
   6.750   0.9478   0.01155   0.00598  -0.0545   0.2969   0.7706
   7.000   0.9373   0.01284   0.00704  -0.0487   0.2426   0.7733
   7.250   0.9315   0.01415   0.00816  -0.0440   0.1944   0.7759
   7.500   0.9303   0.01542   0.00926  -0.0403   0.1535   0.7784
   7.750   0.9322   0.01665   0.01032  -0.0373   0.1192   0.7808
   8.000   0.9395   0.01766   0.01123  -0.0350   0.0951   0.7832
   8.250   0.9496   0.01858   0.01207  -0.0332   0.0777   0.7854
   8.500   0.9611   0.01942   0.01288  -0.0317   0.0648   0.7878
   8.750   0.9728   0.02025   0.01369  -0.0301   0.0542   0.7905
   9.000   0.9848   0.02109   0.01452  -0.0287   0.0454   0.7931
   9.250   0.9994   0.02182   0.01528  -0.0276   0.0414   0.7958
   9.500   1.0113   0.02271   0.01612  -0.0262   0.0338   0.7986
   9.750   1.0276   0.02336   0.01680  -0.0255   0.0316   0.8012
  10.000   1.0415   0.02412   0.01758  -0.0244   0.0284   0.8044
  10.250   1.0546   0.02498   0.01849  -0.0232   0.0262   0.8076
  10.500   1.0698   0.02573   0.01929  -0.0224   0.0243   0.8111
  10.750   1.0854   0.02646   0.02006  -0.0216   0.0226   0.8146
  11.000   1.0996   0.02727   0.02091  -0.0207   0.0210   0.8185
  11.250   1.1114   0.02826   0.02193  -0.0195   0.0184   0.8227
  11.500   1.1275   0.02898   0.02271  -0.0189   0.0176   0.8272
  11.750   1.1428   0.02976   0.02353  -0.0182   0.0160   0.8317
  12.000   1.1565   0.03063   0.02444  -0.0174   0.0144   0.8368
  12.250   1.1684   0.03169   0.02556  -0.0164   0.0132   0.8426
  12.500   1.1843   0.03243   0.02635  -0.0159   0.0117   0.8488
  12.750   1.1975   0.03338   0.02734  -0.0151   0.0103   0.8564
  13.000   1.2100   0.03437   0.02837  -0.0143   0.0076   0.8652
  13.250   1.2215   0.03544   0.02951  -0.0133   0.0065   0.8764
  13.500   1.2269   0.03693   0.03105  -0.0118   0.0026   0.8924
  13.750   1.2326   0.03815   0.03247  -0.0099   0.0018   0.9355
  14.000   1.2471   0.03974   0.03421  -0.0104   0.0013   1.0000
  14.250   1.2570   0.04117   0.03571  -0.0097   0.0011   1.0000
  14.500   1.2658   0.04275   0.03737  -0.0089   0.0010   1.0000
  14.750   1.2683   0.04495   0.03972  -0.0077   0.0008   1.0000
  15.000   1.2757   0.04676   0.04163  -0.0070   0.0007   1.0000
  15.250   1.2833   0.04855   0.04351  -0.0064   0.0007   1.0000
  15.500   1.2895   0.05051   0.04558  -0.0058   0.0007   1.0000
  15.750   1.2947   0.05263   0.04780  -0.0053   0.0007   1.0000
  16.000   1.2981   0.05499   0.05028  -0.0048   0.0007   1.0000
  16.250   1.3018   0.05738   0.05277  -0.0044   0.0007   1.0000
  16.500   1.3021   0.06020   0.05574  -0.0040   0.0007   1.0000
  16.750   1.3006   0.06330   0.05897  -0.0037   0.0006   1.0000
  17.000   1.3022   0.06612   0.06191  -0.0037   0.0007   1.0000
  17.250   1.2968   0.06992   0.06586  -0.0038   0.0006   1.0000
  17.500   1.2965   0.07318   0.06922  -0.0041   0.0007   1.0000
  17.750   1.2911   0.07722   0.07341  -0.0046   0.0006   1.0000
  18.000   1.2801   0.08222   0.07858  -0.0055   0.0006   1.0000
  18.250   1.2723   0.08693   0.08343  -0.0067   0.0006   1.0000
  18.500   1.2617   0.09228   0.08894  -0.0082   0.0006   1.0000
  18.750   1.2480   0.09833   0.09515  -0.0103   0.0006   1.0000
  19.000   1.2335   0.10479   0.10177  -0.0129   0.0006   1.0000
  19.250   1.2159   0.11211   0.10927  -0.0162   0.0006   1.0000
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