Hostname: page-component-5c6d5d7d68-wtssw Total loading time: 0 Render date: 2024-08-07T04:05:37.821Z Has data issue: false hasContentIssue false
  • English
  • Français

Industry applications of advanced flow diagnostics experience in the BAE Systems ground effects rig

Published online by Cambridge University Press:  03 February 2016

P. Curtis
P. Curtis*
Affiliation:
BAE Systems, Farnborough, UK
Get access Rights & Permissions [Opens in a new window]

Abstract

This paper reviews some of the work performed on the ground effects rig at BAE Systems in Warton, the now unique facility for modelling dynamic vertical landings and measuring hot gas ingestion. The paper discusses the flow diagnostic tools which have been used in recent times, up to the complexity of 3D PIV, and uses examples from the F-35 JSF programme to illustrate these. The paper hopefully demonstrates the difficulties of using these tools, as well as the benefits they can bring to a development programme.

The ground effects rig is a facility designed to measure temperature rise in aircraft intakes during vertical manoeuvres close to the ground. It is a complex facility that comes as close as possible to accurately modelling the flowfields around an aircraft moving both vertically and horizontally near the ground, with the ability to model dynamic pitch and roll at the same time.

Standard instrumentation for the models consists of rapid response thermocouples mounted in a rake at the engine face. 45 thermocouples of 0·05mm diameter with a time constant of about 10ms are used.

Although, with its standard instrumentation, the rig can measure how much hot gas gets to the engine face, it doesn’t show how it got there, or where it came from, which is the knowledge required to improve the design. Hence there is a need for flow diagnostics.

Type
Research Article
Information
The Aeronautical Journal , Volume 109 , Issue 1093 , March 2005 , pp. 119 - 127
Copyright
Copyright © Royal Aeronautical Society 2005 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Palmer, P.. BAE Systems Wind Tunnel Department STOVL Test Capabilities, International Powered Lift Conference proceedings, American Helicopter Society, October 2000.Google Scholar
2. Curtis, P.. The influence of ground boundary layer on hot gas ingestion characteristics, November 2002, AIAA-2002-5983.Google Scholar
3. Cox, M. and Abbott, W.A.. Studies of flow fields created by single vertical jets directed downwards upon a horizontal surface, October 1964, NGTE Memo M.390.Google Scholar
4. Abbott, W.A.. Estimation of intake temperatures during V/STOL operation from model tests, March 1966, NGTE Note NT.600.Google Scholar
5. Milford, C.M.. Scaling factors for hot gas recirculation, August 1981, BAe-KAD-N-GEN-2787.Google Scholar
6. Milford, C.M.. Further consideration of recirculation temperature scaling laws, June 1982, BAe-KAD-N-GEN-2844.Google Scholar
7. Blogg, K.M.. Model to full-scale temperature scaling for STOVL aircraft model testing, International Powered Lift Conference proceedings, October 2000, American Helicopter Society.Google Scholar
8. Gerhold, M.N. and Buchholz, M.. Design and test of the X-35B hover pit, November 2002, AIAA-2002-6005.Google Scholar
9. Dantec Dynamics FlowMap, 3D PIV System Description (www.dantec-dynamics.com/download/pdf_files/pi200104.pdf).Google Scholar
10. Tubby, P. and Hurst, D.. Particle image velocimetry (PIV) AGF Test Results, BAES-ASE-WTT-RP-JSF-DEP-030053-1, May 2003.Google Scholar