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 S815 Airfoil (s815-nr)

NREL's S815 Airfoil - NREL HAWT airfoil S815 root 26.0% Dia=20 to 30 m Re=1.2E+6 Clmax(S)=1.46 Clmax(R)=1.40 High max lift coef


Airfoil s815-nr
Details Dat file Parser  
(s815-nr) NREL's S815 Airfoil
NREL HAWT airfoil S815 root 26.0% Dia=20 to 30 m Re=1.2E+6 Clmax(S)=1.46 Clmax(R)=1.40 High max lift coef
Max thickness 26.2% at 25.7% chord.
Max camber 2.9% at 77.9% chord
Source NWTC National WInd Technology Center
Source dat file
The dat file is in Selig format
NREL's S815 Airfoil
   x/c        y/c
1.000000   0.000000
0.996173   0.001133
0.985317   0.004881
0.968744   0.011230
0.947570   0.019426
0.922318   0.028413
0.892882   0.037295
0.858861   0.045992
0.820626   0.054798
0.778755   0.063696
0.733854   0.072589
0.686557   0.081333
0.637515   0.089752
0.587388   0.097641
0.536833   0.104767
0.486493   0.110878
0.436986   0.115700
0.388903   0.118923
0.342805   0.120166
0.299024   0.118640
0.256752   0.114308
0.216262   0.107924
0.178016   0.099823
0.142448   0.090268
0.109968   0.079497
0.080953   0.067752
0.055765   0.055278
0.034732   0.042339
0.018216   0.029212
0.006536   0.016218
0.001725   0.007768
0.000670   0.004717
0.000438   0.003825
0.000070   0.001733
0.000038  -0.001324
0.000429  -0.004570
0.001456  -0.009000
0.007838  -0.023840
0.018563  -0.039818
0.033214  -0.056411
0.051397  -0.073093
0.072764  -0.089487
0.096824  -0.105023
0.123271  -0.119221
0.151614  -0.131452
0.181610  -0.140977
0.213063  -0.147149
0.245908  -0.148514
0.282132  -0.145003
0.321561  -0.137586
0.364402  -0.126505
0.410645  -0.112506
0.460091  -0.096324
0.512409  -0.078791
0.567090  -0.060824
0.623409  -0.043386
0.680405  -0.027417
0.736890  -0.013751
0.791474  -0.003038
0.842638   0.004338
0.888816   0.008316
0.928515   0.009176
0.960420   0.007502
0.983194   0.004101
0.996007   0.001072
1.000000   0.000000
Dat file parser warnings
  • Line 2 - Invalid characters : x/c y/c
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

AH 93-W-257PreviewDetails
NREL's S811 AirfoilPreviewDetails
NREL's S821 AirfoilPreviewDetails
NREL's S814 AirfoilPreviewDetails
NREL's S818 AirfoilPreviewDetails
RAF 89 AIRFOILPreviewDetails
GOE 435 AIRFOILPreviewDetails
GOE 776 AIRFOILPreviewDetails
MH 150 23.89%PreviewDetails
AH 93-W-300PreviewDetails

Polars for NREL's S815 Airfoil (s815-nr)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s815-nr50,00093.2 at α=-1.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s815-nr50,00059 at α=15.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s815-nr100,000926.2 at α=12.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s815-nr100,000536 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s815-nr200,000954.4 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   s815-nr200,000554.8 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   s815-nr500,000979.5 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s815-nr500,000575.9 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   s815-nr1,000,000999.4 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s815-nr1,000,000591.1 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit