Hostname: page-component-586b7cd67f-2brh9 Total loading time: 0 Render date: 2024-11-27T23:55:32.569Z Has data issue: false hasContentIssue false
  • English
  • Français

Tab location effect on supersonic jet mixing

Published online by Cambridge University Press:  06 June 2018

K. Maruthupandiyan  and
E. Rathakrishnan
K. Maruthupandiyan
Affiliation:
Department of Aeronautical Engineering, Institute of Aeronautical Engineering, Hyderabad, India
E. Rathakrishnan*
Affiliation:
Department of Aerospace Engineering, Indian Institute of Technology Kanpur, Kanpur, India
*
[email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

Aerodynamic mixing of a Mach 2 jet controlled with rectangular flat tab with length equal to the nozzle exit diameter, placed at locations 0.25D, 0.5D and 0.75D, downstream of the nozzle exit, has been studied in the presence of different levels of pressure gradients corresponding to nozzle pressure ratio (NPR) range from 3 to 8. The mixing modification associated with shifted tabs is compared with the mixing caused by the same tab at the nozzle exit (0D). The aerodynamic mixing caused by the mass transporting small-scale vortices shed from the edges of the tab placed at the shifted position is found to be appreciably larger than the tab at nozzle exit, for some levels of pressure gradient. For some other levels of nozzle expansion, mixing caused by the shifted tab is comparable to that of tab at nozzle exit. The waves present in the core of the jet controlled with shifted tab were found to be weaker than that of the jet controlled with tab at nozzle exit. At a marginally underexpanded state corresponding to NPR 8, jet core length reduction caused by the tab at 0.75D is about 39.21%, which is closer to the reduction of 40.2%, caused by the tab at 0D. The corresponding core length reduction for tab at 0.25D and 0.5D are 38.16% and 20%, respectively.

Keywords

Jetshifted tabfavourable pressure gradientcore length
Type
Research Article
Information
The Aeronautical Journal , Volume 122 , Issue 1254 , August 2018 , pp. 1229 - 1243
Copyright
Copyright © Royal Aeronautical Society 2018 

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

REFERENCES

1.Bradbury, L.J.S. and Khadem, A.H. The distortion of a jet by tabs, J Fluid Mechanics, 1975, 70, (04), pp 801–813. Available at: https://doi.org/10.1017/S0022112075002352.Google Scholar
2.Ahuja, K.K. and Brown, W.H. Shear flow control by mechanical tabs, 2nd AIAA Shear Flow Conference, Tempe, AZ, number AIAA, 1989, Paper 89–0994. Available at: https://doi.org/10.2514/6.1989-994.Google Scholar
3.Ahuja, K.K., Manes, J.P., Massey, K.C. and Calloway, A.B. An evaluation of various concepts of reducing supersonic jet noise, AIAA, 1990, Paper 90–3982.Google Scholar
4.Samimy, M., Reeder, M.F. and Zaman, K.B.M.Q. Supersonic jet mixing enhancement by vortex generations, 27th Joint Propulsion Conference Sacramento, CA, 1991, Paper 91–2263. Available at: https://doi.org/10.2514/6.1991-2263.Google Scholar
5.Zaman, K.B.M.Q., Reeder, M.F. and Samimy, M. Supersonic jet mixing enhancement by delta-tabs, 28th Joint Propulsion Conference and Exhibit, 1992, AIAA, Nashville, Tennessee, US, Paper 92–3548. Available at: https://arc.aiaa.org/doi/abs/10.2514/6.1992-3548.Google Scholar
6.Zaman, K.B.M.Q. Streamwise vorticity generation and mixing enhancement in free jets by delta-tabs, 3rd Shear Flow Conference, 1993, AIAA, Orlando, Florida, US, Paper 93–3253. Available at: https://doi.org/10.2514/6.1993-3253.Google Scholar
7.Zaman, K.B.M.Q, Reeder, M.F. and Samimy, M. Control of an axisymmetric jet using vortex generators, Phys Fluids, 1994, pp 778–793. Available at: https://doi.org/10.1063/1.868316.Google Scholar
8.Zaman, K.B.M.Q. Axis switching and spreading of an asymmetric jet: The role of coherent structure dynamics, J Fluid Mech, 1996, pp 1–27. Available at: https://doi.org/10.1017/S0022112096000420.Google Scholar
9.Gretta, W.J. and Smith, C.R. The flow structure and statistics of a passive mixing tab, J Fluids Engineering, 1993, 115, pp 255–263. Available at: https://doi:10.1115/1.2910133.Google Scholar
10.Reeder, M.F. and Zaman, K.B.M.Q. Impact of tab location relative to the nozzle exit on distortion, AIAA, 1994, 34, (1), pp 94–3385. Available at: https://doi.org/10.2514/3.13044.Google Scholar
11.Behrouzi, P. and McGuirk, J.J. Effect of tab parameters on near-field jet plume development, J Propulsion and Power, 2006, 22, (3), pp 576–585. Available at: https://doi.org/10.2514/1.15473.Google Scholar
12.Rathakrishnan, E. Experimental studies on the limiting tab, AIAA, 2009, 47, pp 2475–2485. Available at: https://doi.org/10.2514/1.43790.Google Scholar
13.Lovaraju, P. and Rathakrishnan, E. Effect of cross-wire location on the mixing of underexpanded sonic jets, J Aerospace Engineering (ASCE), 2007, 20, (3), pp 179–185. Available at: https://doi.org/10.1061/(ASCE)0893-1321(2007)20:3(179).Google Scholar
14.Lovaraju, P. and Rathakrishnan, E. Shifted cross-wire for jet flow control, Int Review of Aerospace Engineering, 2008, 1, (1), pp 61–68.Google Scholar
15.Maruthupandiyan, K. and Rathakrishnan, E. Supersonic jet control with shifted tabs, Proc. IMechE Part G: J Aerospace Engineering, 2016, 232, (3), pp 433–447. Available at: https://doi.org/10.1177/0954410016679197.Google Scholar
16.Maruthupandiyan, K. and Rathakrishnan, E. Corrugated shifted limiting tabs effectiveness on supersonic jet mixing, J Aerospace Engineering, 2017. Available at: https://doi.org/10.1061/(ASCE)AS.1943-5525.0000815.Google Scholar
17.Rathakrishnan, E. Instrumentation, Measurements, and Experiments in Fluids, 2nd ed, 2016, CRC Press, Boca Raton, Florida, US.Google Scholar
18.Rathakrishnan, E. Applied Gas Dynamics, 2010, Wiley, Hoboken, New Jersey, US.Google Scholar