Hostname: page-component-cd9895bd7-jn8rn Total loading time: 0 Render date: 2024-12-23T02:30:59.907Z Has data issue: false hasContentIssue false
  • English
  • Français

Comparison of experimental and numerical investigation on a jet in a supersonic cross-flow

Published online by Cambridge University Press:  03 February 2016

A. Kovar  and
E. Schülein
A. Kovar
Affiliation:
German Aerospace Centre (DLR), Göttingen, Germany
E. Schülein
Affiliation:
German Aerospace Centre (DLR), Göttingen, Germany
Get access Rights & Permissions [Opens in a new window]

Abstract

Flow interaction of three different jet configurations ejecting air from a flat plate into a supersonic cross flow were investigated experimentally and numerically. The test conditions encompassed a jet pressure ratio of Poj, P∞ = 100 at a Mach number of M∞ = 5 and Reynolds number of about Re∞ = 25 × 106 based on the length of the flat plate. The investigated test cases are: a) single jet; b) four jets positioned in-line in main flow direction; c) four jets positioned side-by-side in spanwise direction. The prediction of the overall flow phenomena as occurring within the interaction area was in fair agreement with the experiments, although quantitatively differences occur that will be discussed in the paper.

The results of the comparison are presented and the experimental data are used to validate the applied code.

Type
Research Article
Information
The Aeronautical Journal , Volume 110 , Issue 1108 , June 2006 , pp. 353 - 360
Copyright
Copyright © Royal Aeronautical Society 2006 

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. Margason, R.J., Fifty years of jet in cross flow research, AGARD-CP-534, Computational and Experimental Assessment of Jets in Cross Flow, Symp. In Winchester, UK, 19-22 April 1993.Google Scholar
2. Heyser, A. and Maurer, F., Experimentelle Untersuchungen an festen Spoilern und Strahlspoilern bei Machschen Zahlen von 0.6 bis 2.8, Z. flugwiss. 1962, 10, Heft 4/5, S. 110–130.Google Scholar
3. Spaid, F.W. and Zukoski, E.E., A study of the interaction of gaseous jets from transverse slots with supersonic external flows, AIAA J, 1966, 6, (2), pp 205–212.Google Scholar
4. Ludwieg, H., Hottner, T.H. and Grauer-Carstensen, H., Der Rohrwindkanal der aerodynamischen Versuchsanstalt Göttingen, Germany. Jahrbuch der DGLR, 1969, S. pp 52–58.Google Scholar
5. Schülein, E. and Zheltovodov, A., Documentation of experimental data for hypersonic 3-D shock waves/turbulent boundary layer interaction flows, 2001, internal report IB 223-99 A 26, DLR, Göttingen, Germany.Google Scholar
6. Gerhold, T. and Evans, J., Efficient computation of 3D-flows for complex configurations with the DLR TAU-Code using automatic adaptation, Notes on Numerical Fluid Mechanics, 1999, 72, Vieweg.Google Scholar
7. Schwamborn, D., Gerhold, T., and Hannemann, V., On the Validation of the DLR TAU-Code, Notes on Numerical Fluid Mechanics, 1999, 72, Vieweg.Google Scholar
8. Spalart, P.R. and Allmaras, S.R., A one-equation turbulence model for aerodynamic flows, 30th Aerospace Sciences Meeting & Exhibit, 6–9 January 1992, Reno, USA, AIAA-92-0439.Google Scholar
9. Knight, D.D. and Degrez, G., Shock wave boundary-layer interactions in high Mach number flows – A Critical Survey of Current Numerical Prediction Capabilities, AGARD AR-319, 1998, 2.Google Scholar
10. Kovar, A. and Schülein, E., Study of supersonic flow separation induced by side jets and its control, accepted for publication in Notes on Numerical Fluid Mechanics and Multisidisciplinary Design – New Results in Numerical and Experimental Fluid Mechanics V, 2006, 14th STAB/DGLR Symposium Bremen, ZARM, Germany 2004.Google Scholar
11. Romeo, D.J., Aerodynamic interaction effects ahead of rectangular sonic jets exhausting perpendicularly from a flat plate into a Mach number 6 Free Stream, Technical Note D-1800, 1963, National Aeronautics and Space Administration (NASA), Washington, USA.Google Scholar
12. Maurer, F., Three-dimensional effects in shock-seperated flow Regions ahead of lateral control-jets issuing from slot nozzles of finite length, AGARD-CP-4, Part 2, Flow Separation, 1966, pp 605–634 Google Scholar
13. Schülein, E., Krogmann, P. and Stanewsky, E., Documentation of two-dimensional impinging shock/turbulent boundary-layer interaction flow, Internal Report IB 223-96 A 49 of the DLR, 1996.Google Scholar
14. Ziegler, H. and Wooler, P.T., Multiple jets exhausting into a cross flow, J Aircr, 1971, 8, (6).Google Scholar