Imperial College London
Portrait Picture

DrPaulBruce

Faculty of Engineering, Department of Aeronautics

Reader in High-Speed Aerodynamics
 
 
 
//

Contact

 

+44 (0)20 7594 5048p.bruce

 
 
//

Location

 

333City and Guilds BuildingSouth Kensington Campus

//

Summary

 

Publications

Citation

BibTex format

@article{Bruce:2011:10.2514/1.55029,
author = {Bruce, PJK and Babinsky, H and Tartinville, B and Hirsch, C},
doi = {10.2514/1.55029},
journal = {AIAA Journal},
pages = {1710--1720},
title = {Experimental and Numerical Study of Oscillating Transonic Shock Waves in Ducts},
url = {http://dx.doi.org/10.2514/1.55029},
volume = {49},
year = {2011}
}
Download

RIS format (EndNote, RefMan)

TY  - JOUR
AB  - An experimental and computational study of a Mach 1.4 transonic shock wave in a parallel-walled duct subject to downstream pressure perturbations in the frequency range of 16–90 Hz has been conducted. The dynamics of unsteady shock motion and aspects of the unsteady transonic shock and turbulent tunnel-floor boundary-layer interaction have been investigated. The numerical computations were performed using an unsteady Reynoldsaveraged Navier–Stokes scheme. It is found that the (experimentally measured) shock dynamics are generally well replicated by the numerical scheme, especially at relatively low (40 Hz) frequencies. However, variations in shock/boundary-layer interaction structure during unsteady shock motion observed in experiments are not always well predicted by the simulation. Significantly, the computations predict variations in shock/boundary-layer interaction size due to shock motion that are much larger and in the opposite sense to the variations observed in experiments. Comparison of the unsteady results from the present study with steady (experimental) results from the literature suggests that unsteady Reynolds-averaged Navier–Stokes code used in the present study models the unsteady shock/boundary-layer interaction behavior as quasi-steady, whereas experiments suggest that it is more genuinely unsteady. Further work developing numerical methods that demonstrate a more realistic sensitivity of shock/ boundary-layer interaction structure to unsteady shock motion is required.
AU  - Bruce,PJK
AU  - Babinsky,H
AU  - Tartinville,B
AU  - Hirsch,C
DO  - 10.2514/1.55029
EP  - 1720
PY  - 2011///
SP  - 1710
TI  - Experimental and Numerical Study of Oscillating Transonic Shock Waves in Ducts
T2  - AIAA Journal
UR  - http://dx.doi.org/10.2514/1.55029
UR  - http://hdl.handle.net/10044/1/15334
VL  - 49
ER  -
Download