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 S830 Airfoil (s830-nr)

NREL's S830 Airfoil - NREL HAWT airfoil S830 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.60 Clmax(R)=1.57 High max lift coef


Airfoil s830-nr
Details Dat file Parser  
(s830-nr) NREL's S830 Airfoil
NREL HAWT airfoil S830 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.60 Clmax(R)=1.57 High max lift coef
Max thickness 21% at 38.4% chord.
Max camber 4.4% at 70.5% chord
Source NWTC National WInd Technology Center
Source dat file
The dat file is in Selig format
NREL's S830 Airfoil
   x/c        y/c
1.000000   0.000000
0.996213   0.001203
0.985542   0.005326
0.969428   0.012449
0.949079   0.021787
0.925040   0.032223
0.897194   0.042832
0.865181   0.053521
0.829431   0.064492
0.790530   0.075592
0.749037   0.086574
0.705495   0.097154
0.660423   0.107035
0.614313   0.115922
0.567636   0.123536
0.520836   0.129621
0.474335   0.133952
0.428537   0.136323
0.383830   0.136529
0.340479   0.134168
0.298097   0.129336
0.256986   0.122622
0.217623   0.114339
0.180420   0.104736
0.145802   0.094056
0.114129   0.082530
0.085764   0.070410
0.061007   0.057940
0.040147   0.045401
0.023428   0.033066
0.011037   0.021266
0.003211   0.010402
0.000060   0.001115
0.000039  -0.000844
0.000412  -0.002542
0.001382  -0.004060
0.002881  -0.005598
0.013177  -0.011916
0.029422  -0.017940
0.051653  -0.023853
0.079316  -0.030134
0.111461  -0.036739
0.147559  -0.043513
0.186873  -0.050302
0.228869  -0.057009
0.272529  -0.063925
0.315889  -0.070022
0.358731  -0.073340
0.401930  -0.072877
0.446270  -0.068586
0.492158  -0.060861
0.539713  -0.049835
0.590178  -0.036452
0.643069  -0.022820
0.697235  -0.010292
0.751317   0.000132
0.803810   0.007746
0.853141   0.012117
0.897549   0.012956
0.934906   0.010830
0.963907   0.007210
0.984220   0.003569
0.996109   0.000965
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

WORTMANN FX 2 AIRFOILPreviewDetails
WORTMANN FX 75-193PreviewDetails
WORTMANN FX 3 AIRFOILPreviewDetails
NASA/LANGLEY LS(1)-0421 AIRFOILPreviewDetails
NREL's S827 AirfoilPreviewDetails
NREL's S835 AirfoilPreviewDetails
UNIVERSITY OF ALBERTA UA 79-SF-187PreviewDetails
EPPLER 748 AIRFOILPreviewDetails
NREL's S816 AirfoilPreviewDetails
UNIVERSITY OF ALBERTA UA 79-SF-187PreviewDetails

Polars for NREL's S830 Airfoil (s830-nr)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s830-nr50,00094.2 at α=12.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s830-nr50,000510.8 at α=15.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s830-nr100,000917.7 at α=14°Mach=0 Ncrit=9Xfoil predictionDetails
   s830-nr100,000534.2 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s830-nr200,000961.1 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s830-nr200,000566.3 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s830-nr500,000995.2 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s830-nr500,000594 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   s830-nr1,000,0009117.8 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s830-nr1,000,0005115.3 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit