Journal of Applied Science and Engineering

Published by Tamkang University Press

1.30

Impact Factor

2.10

CiteScore

Bo Sun This email address is being protected from spambots. You need JavaScript enabled to view it.1 and Zhuo Chang-fei1

1Department of Aerospace Engineering, Nanjing University of Science and Technology, China P.R.C


 

Received: August 19, 2019
Accepted: January 6, 2020
Publication Date: June 1, 2020

Download Citation: ||https://doi.org/10.6180/jase.202006_23(2).0010  

ABSTRACT


The typical features of asymmetric flow in supersonic ducts and Coanda effect which attaches a jet to an adjacent solid surface are summarized. Based on these similar features and six typical flow patterns in nozzles, the Coanda effect is employed to analyze the asymmetric SBLI (Shock/Boundary Layer Interactions) qualitatively and allows to give a preliminarily reasonable explanation. The evolution roadmap of flow pattern in 2-D ramp and axisymmetric nozzles is summed up. The results show that the entrainment of mainstream shear layer on separation flow caused by SBLI should be the predominant reason for flow asymmetry, which is the manifestation of Coanda effect in confined SBLI. Flow asymmetry will disappear when the Coanda effect breaks down due to strong SBLI causing large separations. When asymmetric SBLI appears, two flow patterns are possible: one has Restricted Shock Separation (RSS) on both sides; the other one has RSS on one side and Free Shock Separation (FSS) on the other side. Asymmetry flipping in nozzle flow experiments from one run to the next is a result of randomicity of the Coanda effect. The flow pattern with RSS on both sides and high confinement level maybe a probable cause for asymmetry flipping unsteadiness in one test run.


Keywords: Asymmetry; Shock/Boundary Layer Interactions; Coanda effect


REFERENCES


 

  1. [1]  B. F. Carroll, J. C. Dutton, A Numerical and Experimental Investigation of Multiple Shock Wave/Turbulent Boundary Layer Interactions in a Rectangular Duct, Department of Mechanical and Industrial Engineering, Univ. of Illinois at Urbana-Champaign, Urbana, IL, Rept. UILU-ENG-88-4015 ,1988.
  2. [2]  A. Hadjadj, M. Onofri, Nozzle flow separation, Shock Waves, 19 (2009) 163–169.
  3. [3]  T. Gawehn, A. Gülhan, N. S. Al-Hasan, G. H. Schnerr, Experimental and numerical analysis of the structure of pseudo-shock systems in Laval nozzles with parallel side walls, Shock Waves, 20 (2010) 297–306.
  4. [4]  D, Papamoschou, A. Zill, A. Johnson, Supersonic flow separation in planar nozzles, Shock Waves, 19 (2009) 171–183.
  5. [5]  T. Ikui, K. Matsuo, M. Nagai, M. Honjo, Oscillation phenomena of pseudo-shock waves, Bulletin of the JSME, 17 (1974) 1278-1285.
  6. [6]  B. F. Carroll, J. C. Dutton, Characteristics of multiple shock wave/turbulent boundary-layer interactions in rectangular ducts, Journal of Propulsion and Power, 6 (1990) 186-193.
  7. [7]  L.Q. Sun, H. Sugiyama, K. Mizobata, R. Minato,  A. Tojo, Numerical and experimental investigations on Mach 2 and 4 pseudo-shock wave in a square duct, Trans. Japan. Soc. Aero. Space Sci., 47 (2004) 124-130 .
  8. [8]  H. Sugiyama, Y. Tsujiguchi, T. Honma, Structure and oscillation phenomena of pseudo-shock waves in a straight square duct at Mach 2 and 4, AIAA 2008-2646, 2008.
  9. [9]  R.A. Lawrence, Symmetrical and unsymmetrical flow separation in supersonic nozzles, Research Report Number 67-1, Southern Methodist University ,1967.
  10. [10] D. Papamoschou, A. Zill, Fundamental investigation of supersonic nozzle flow separation, AIAA Paper 2004-1111, 2004.
  11. [11] E. Shimshi, G. Ben-Dor, A. Levy, A. Krot- hapalli, Experimental investigation of asymmetric and unsteady flow separation in high Mach number planar nozzles, Proceedings of the 28th International Symposium on Shock Waves, Manchester, 17 – 22 July, 2011.
  12. [12] A. Bourgoing, Ph. Reijasse, Experimental analysis of unsteady separated flows in a supersonic planar nozzle, Shock wave, 14 (2005) 251–258.
  13. [13] Q. Xiao, H.M. Tsai, D. Papamoschou, Numerical investigation of supersonic nozzle flow separation, AIAA J, .45 (2007) 532–541.
  14. [14] P. J. K. Bruce, H. Babinsky, B. Tartinville, C. Hirsch, Corner effect and asymmetry in transonic channel flows, AIAA J., 49 (2011) 2382-2392.
  15. [15] E. V. Myshenkov, E. V. Myshenkova, Hysteresis phenomena in a plane rotatable nozzle, Fluid Mechanics, 45 (2010) 667-678.
  16. [16] T-S Wang, Transient two-dimensional analysis of side load in liquid rocket engine nozzles, AIAA 2004-3680, 2004.
  17. [17] P.W. Carpenter, P.N. Green., The aeroacoustics and aerodynamics of high-speed Coanda devices, J. Sound & Vibration, .208 (1997) 777-801.
  18. [18] Takafumi Nishino, Seonghyeon Hahn, Karim Shariff., Large-eddy simulations of a turbulent Coanda jet on a circulation control airfoil, Phys. Fluids, 22 (2010) 125105.
  19. [19] C. Allery, S. Guerin, A. Hamdouni, A. Sakout, Experimental and numerical POD study of the Coanda effect used to reduce self-sustained tones, Mechanics Research Communications, 31 (2004) 105–120.
  20. [20] R. Neuendorf, I. Wygnanski, On a turbulent wall jet flowing over a circular cylinder, Journal of Fluid Mechanics, 381 (1999) 1–25.
  21. [21] B. G. Newman, The deflection of plane jets by adjacent boundaries–Coanda effect, Boundary Layer and Flow Control, edited by G. V. Lachmann, Vol. 1, Pergamon Press, Oxford, pp. 232–264 ,1961.
  22. [22] K.C. Cornelius, G.A. Lucius,, Physics of Coanda jet detachment at high-pressure ratio, J. AIRCRAFT, 31 (1994) 591-596.
  23. [23] S. Matsuo, T. Setoguchi, T. Kudo, Study on the characteristics of supersonic Coanda jet, J. of Thermal Science, 7 (1998) 165-175.
  24. [24] J. Ostlund and B. Muhammad-Klingmann, Supersonic flow separation with application to rocket engine nozzles, Applied Mechanics Reviews, 58 (2005) 143-177.
  25. [25] A. T. Nguyen, H. Deniau, S. Girard, T. Roquefort, Unsteadiness of flow separation and end-effects regime in a thrust-optimized contour rocket nozzle, Flow, Turbulence and Combustion, 71 (2003) 161–181.
  26. [26] Y. Koichi, M. Tsuyoshi, T.Yoshinobu, W. Yasuhide, Y. Kazuhiko, A Study of an asymmetric flow in an overexpanded rocket nozzle, Journal of Fluid Science and Technology, 2 (2007) 400-409.
  27. [27] A. Bourgoing, P.H. Reijasse, Experimental investigation of an unsteady and asymmetrical supersonic separated flow, 8th Aerodynamic Session Symposium, Toronto, 29 April–2 May 2001.
  28. [28] R. L. Simpson , Turbulent Boundary-Layer Separation, Ann. Rev. Fluid Mech. , 21(1989) 205-234.
  29. [29] M. Frey, G. Hagemann, Flow separation and side-loads in rocket nozzles, AIAA Paper 99-2815, 1999.
  30. [30] J. M. Davin, R. E. Petersen, An experimental investigation of unstable asymmetric jet separation in a supersonic converging -diverging nozzle, AIAA 1979-1256, 1979.
  31. [31] C.A. Hunter, Experimental, theoretical and computational investigation of separated nozzle flows, AIAA Paper 98-3107, 1998.
  32. [32] A. Nebbache, Ph. Reijasse, F. Bouvier, Symmetrical and asymmetrical separated nozzle flow, 6th International Symposium on Launchers Technologies, Munich, Germany, 8-11 November, 2005.
  33. [33] E. Martelli, F. Nasuti, M. Onofri, Numerical calculation of FSS/RSS transition in highly overexpanded rocket nozzle flows, Shock Waves, 20 (2010) 139–146.
  34. [34] T-S Wang, Transient three-dimensional startup side load analysis of a regeneratively cooled nozzle, Shock Waves, 19 (2009) 251–264.
  35. [35] D.S. Dolling, Fifty years of shock-wave /boundary-layer interaction research: what next? AIAA J., 39 (2001), 1517–1531.
  36. [36] S. Piponniau, J.P. Dussauge, J.F. Debieve, P. Dupont, A simple model for low-frequency unsteadiness in shock induced separation,  J. Fluid Mech., 629 (2009) 87–108.
  37. [37] C-P Wang, C-F Zhuo. Model for Asymmetry of Shock/Boundary Layer Interactions in Nozzle Flows. Transactions of Nanjing University of Aeronautics and Astronautics, 2018, 35(1):146-153.
  38. [38] S. B. Verma, C. Manisankar. Origin of flow asymmetry in planar nozzles with separation. Shock Waves (2014) 24:191–209.