Marine Solutions Aerospace Solutions Automotive Solutions
| Overview | | High Lift Validation | | Compressibility Validation | | Unsteady Validation(1) | | Unsteady Validation(2) | | Low AR Validation | | Low AR Validation(2) |

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
Mach 0.621
Frequency 24Hz
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.

[1] Compendium of unsteady aerodynamic measurements. AGARD Report No.702. August 1982.
[2] Compendium of unsteady aerodynamic measurements. AGARD Report No.702 Addendum 1. May 1985.



Use the interactive NEWPAN results browser to view the comparision with experimental data.

To change the spanwise section displayed in the graph plot, left mouse click on a white wing section in the 3D view above.


[Home] [Products] [Solutions] [About Us] [Contact Us] [Support] [Site Map]

Copyright © 2019 Flow Solutions Ltd.  All rights reserved. 
Company Registration No 2010440, Registered Office 61 Grace Close Chipping Sodbury, South Glos BS37 6ND