Open Access Open Access  Restricted Access Subscription or Fee Access

Flow-Field and Performance Study of Coaxial Supersonic Nozzles Operating in Hypersonic Environment

Mohammad Saeed Samara(1*), Ashish Vashishtha(2), Yasumasa Watanabe(3), Kojiro Suzuki(4)

(1) Department of Advanced Energy, The University of Tokyo, Japan
(2) Department of Aerospace, Mechanical and Electronic Engineering, Institute of Technology Carlow, Ireland
(3) Department of Aeronautics and Astronautics, Graduate School of Engineering, The University of Tokyo, Japan
(4) Department of Advanced Energy, The University of Tokyo, Japan
(*) Corresponding author


DOI: https://doi.org/10.15866/irease.v13i1.18282

Abstract


The integration of multiple propulsion systems in a coaxial configuration is one of the challenges to realize hypersonic passenger transportation. This study is an attempt to understand the performance of two co-axial jets exiting from the base of slender body, operating in single and dual operation mode in freestream hypersonic flow environment. In addition, the effects on performance by adding a different length common channel to both co-axial jets are studied. In the first part of this study, the experiments have been performed for small slender body kept in hypersonic Mach 7 flow, which consists of two inner high-pressure chambers and two co-axial nozzles at the base: central nozzle (Mach 4) and surrounding nozzle (Mach 2.8) along with extended common region, termed as common channel. Schlieren images have been captured for single and dual operation modes. Axisymmetric numerical simulations have been performed for further understanding of the flow interactions and have been qualitatively validated with experimental images. In the second part, the parametric study has been performed using numerical simulations for resized model with various exit Mach numbers for central and surrounding jets along with effect of no common channel and with common channel for various operation modes. One of the findings of the study is that dual jets should operate and exit at same plane (no common channel) with the same exit area (each nozzle with half of total available exit area) in order to have higher total thrust from both jets than the sum of individual jets operating in single operation mode. For higher central jet Mach numbers, the corresponding surrounding jet Mach number will be lower, and in dual operation mode (without common channel), the total thrust will be the same or lower than the sum of the individual jet operations. Regarding the effect of common channel, it has been found out that the introduction of the extended short or long common channel in dual mode operation does not have significant effect on thrust, while the jet flow field is strongly affected by the common channel presence. In single operation mode, for Mach 2 central-jet, the thrust performance decreases 12.2-14.6 % in presence of short and long (29.5 mm and 59 mm) common channel, while for Mach 2 surrounding jet, the thrust performance increases by 15-17.4 % in presence of common channel.
Copyright © 2020 Praise Worthy Prize - All rights reserved.

Keywords


Hypersonic Flow; Supersonic Jets; CFD; Wind Tunnel Experiment; Co-Axial Nozzles

Full Text:

PDF


References


Peter W. Merlin: Design and Development of the Blackbird: Challenges and Lessons Learned, AIAA 2009-1522, 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition, Orlando, Florida, 05 January 2009 - 08 January 2009.
https://doi.org/10.2514/6.2009-1522

U.B. Mehta, M.J. Aftosmis, J.V. Bowles, S.A. Pandaya, Skylon Aerodynamics and SABRE Plumes, AIAA-2015-3605, 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Glasgow, Scotland, 6-9 July 2015.
https://doi.org/10.2514/6.2015-3605

E. Rathakrishnan, Applied Gas Dynamics, second ed. (John Wiley & Sons NJ., USA, 2019, pp 505-509).

H. Sharma, A. Vashishtha, E. Rathakrishnan, P. Lovaraju, Experimental study of overexpanded co-flowing jets, The Aeronautical Journal 112(1135), 2008, 537-546.
https://doi.org/10.1017/s0001924000002499

Mohana Murali, R., Aravindh Kumar, S., Rathakrishnan, E., Characteristics of Parallel and Inward Canted Sonic Twinjets, (2018) International Review of Aerospace Engineering (IREASE), 11 (4), pp. 138-145.
https://doi.org/10.15866/irease.v11i4.15497

Belkacem, S., Beghidja, A., Numerical Investigation of Coaxial Turbulent Jet, (2019) International Review of Mechanical Engineering (IREME), 13 (2), pp. 78-86.
https://doi.org/10.15866/ireme.v13i2.16668

T.A. Edwards, Numerical investigation of hypersonic exhaust plume/afterbody flow fields, 10th Australasian Fluid Mechanics Conference, Proc. Vol. 2, 1989, pp 15.29-15.32.

B.W. Oudheusden, F. Scarano, PIV Investigation of Supersonic Base-Flow–Plume Interaction, Topics in Applied Physics Volume 112, 2008, pp 449-458.
https://doi.org/10.1007/978-3-540-73528-1_25

S. Stephan, R. Radespiel, Propulsive jet Simulation in a Hypersonic Ludwieg Tunnel, DLR Report, 2012, Document ID: 28313.

C.W. Clifton A.D. Cutler, A supersonic Argon/Air Coaxial Jet Experiment for Computational Fluid Dynamics Code Validation, NASA Technical Report, NASA/CR-2007-214866.

R.A. Baurle, J.R. Edwards, Hybrid Reynolds-Averaged / Large Eddy Simulations of a Co-axial Supersonic Free-Jet Experiments, AIAA-2009-129, 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition, Orlando, Florida, 05 January 2009 - 08 January 2009.
https://doi.org/10.2514/6.2009-129

K.B.M.Q. Zaman, I.M. Milanovic, A.F. Fagan, C.J. Miller, Experimental and computational study of tones occurring with a co-axial nozzle, International Journal of Aeroacoustics, Vol 18, issue 2-3, 2019, pp. 189-206.
https://doi.org/10.1177/1475472x19834522

S.E. Cliff, M.F.Denison, S.M. Yekta, D.E. Morr, D.A. Durston, Wind Tunnel Model Design for Sonic Boom Studies of Nozzle Jet with Shock Interaction, AIAA-2016-2035, 54thAIAA Aerospace Science Meeting, Sci-tech, January 2016, California, USA.
https://doi.org/10.2514/6.2016-2035

V. S. Ivanov, S. M. Frolov, V. I. Zvegintsev V. S. Aksenov , I. O. Shamshin , D. A. Vnuchkov, D. G. Nalivaichenko , A. A. Berlin, V. M. Fomin, A. N. Shiplyuk and N. N. Yakovlev: Hydrogen-Fueled Detonation Ramjet Model: Wind Tunnel Tests, AIP Conference Proceedings, 2027, 030041 (2018).
https://doi.org/10.1016/j.ijhydene.2018.02.187

P.V. Bulat, O.N.Zasuhin, and V.N. Uskov, On classification of flow regimes in a channel with sudden expansion. Thermophysics and Aeromechanics, 2012, vol. 19, No. 2. pp 233-246.
https://doi.org/10.1134/s0869864312020072

G. C. Layek, C. Midya, S. Mukhopadhyay: Effects of Suction and Blowing on Flow Separation in a Symmetric Sudden Expanded Channel. Nonlinear Analysis: Modelling and Control, 2008, Vol.13, No.4, pp 451-465.
https://doi.org/10.15388/na.2008.13.4.14551

O. Imamura, T. Watanuki, K. Suzuki, Kashiwa Wind Tunnel Working Group (Univ. of Tokyo), Flow characteristics of UT-Kashiwa Hypersonic Wind Tunnel, Proceedings of 39th Fluid Dynamics Conference/Aerospace, Numerical Simulation Symposium 2007, JAXASP-07-016, pp 50-55.

M. Martini, A. Smoraldi, L. Cutrone, M. Zanchetta, R. Varvill, Analysis of Lapcat A2 Vehicle Scimitar Engine Nozzle, XXII Conference of Italian Association of Aeronautics and Astronautics, Napoli 9-12 September 2013.

K. E. Tatum, L D. Huebner, Exhaust Gas Modelling Effects on Hypersonic Powered Simulation at Mach 10, AIAA-95-6068, International Aerospace Planes and Hypersonic Technologies, 1995, TN, USA
https://doi.org/10.2514/6.1995-6068

M.S. Liou, A sequel to ASUM, Part II: ASUM+ -up for all speeds”, Journal of Computational Physics, Vol.214, No.1, 2006, pp 137-170.
https://doi.org/10.1016/j.jcp.2005.09.020

C. Hirsch, Numerical Computation of Internal and External Flows Vol.1: Fundamental of Computational Fluid Dynamics, second ed. (John Wiley and Sons, 2007, Singapore).


Refbacks

  • There are currently no refbacks.



Please send any question about this web site to info@praiseworthyprize.com
Copyright © 2005-2021 Praise Worthy Prize