Validation of the unsteady NEWPAN method has been performed for a number of the available
and appropriate standard aerospace testcases.
A working group of the AGARD Structures and Materials panel compiled a set of
unsteady 2D and 3D testcases known as the AGARD Aeroelastic Configurations, and
published a compendium of experimental data [1,2] specifically for the purpose
of assisting in the validation of unsteady aerodynamic methods.
Dataset 9 is the NLR LANN wing testcase. This is an isolated wing of aspect ratio 8,
with a leading edge sweep of 28 degrees, undergoing a pitch oscillation about a
spanwise axis running through the 62.1% root chord location. Experimental data
is available in the Mach range 0.6 to 0.95.
Run number 22 is presented here, with the following conditions:
Alpha (mean) 0.6 degrees
Reduced frequency based on (full) root chord: 0.266
Plots below show excellent agreement between NEWPAN and experimental results for both
the steady and unsteady data. Steady Cp, and the real and imaginary parts of the unsteady
Cp may be selected for comparison, at any of six different spanwise locations.
 Compendium of unsteady aerodynamic measurements. AGARD Report No.702. August 1982.
 Compendium of unsteady aerodynamic measurements. AGARD Report No.702 Addendum 1. May 1985.
Use the interactive NEWPAN results browser to view the comparision with
To change the spanwise section displayed in the graph plot,
left mouse click on a white wing section in the 3D view above.