[1] A Hadjadj, M Onofri’’Nozzle flow separation’’Shock Waves (2009) 19:163–169 DOI 10.1007/s00193-009-0209-7.
[2] Lawrence, R.A.: Symmetrical and unsymmetrical flow separation in supersonic nozzles. Research Report Number 67-1, Southern Methodist University (1967) .
[3] Verma, S.B.: Study of flow separation in truncated ideal contour nozzle. J. Propuls. Power 18, 1112–1121 (2002).
[4] Nave, L.H., Coffey, G.A.: Sea-level side loads in high-area-ratio rocket engines. AIAA Paper 73-1284 (1973)
[5] Craig A. Hunter,NASA Langley Research Center, Hampton, Virginia 23681’’Experimental Investigation of Separated Nozzle Flows’’JOURNAL OF PROPULSION AND POWER Vol. 20, No. 3, May–June 2004.
[6] Nguyen, A.T., Deniau, H., Girard, S., Alziary de Requefort, T.: Unsteadiness of flow separation and end-effects regime in a thrust optimized contour rocket nozzle. Flow Turbul. Combust. 71, 1–21 (2003).
[7] Hagemann, G., Frey, M., Koschel, W.: Appearance of restricted shock separation in rocket nozzles. J. Propuls. Power 18, 577–584 (2002).
[8] Ostlund, J.: Flow processes in rocket engine nozzles with focus on flow-separation and side-loads. Ph.D. Thesis, Royal Inst. of Tech., Stockholm, TRITA-MEK (2002).
[9] Chen, C.L., Chakravarthy, S.R., Hung, C.M.: Numerical investigation of separated nozzle flows. AIAA J. 32, 1836–1843 (1994).
[10] Gross, A.,Weiland, C.: Numerical simulation of separated cold gasnozzle flows. J. Propuls. Power 20, 509–519 (2004).
[11] Deck, S., Nguyen, A.T.: Unsteady side loads in a thrust-optimized contour nozzle at hysteresis regime.AIAAJ. 42, 1878–1888 (2002).
[12] Nasuti, F., Onofri,M.: Viscous and inviscid vortex generation during start-up of rocket nozzles. AIAA J. 36(5), 809–815 (1998).
[13] Morí˜nigo, J.A., Salvá, J.: Three-dimensional simulation of the self-oscillating flow and side-loads in an over-expanded subscale rocket nozzle. J. Aerosp. Eng. 220(G), 507–523 (2006).
[14] Schmucker, R.H.: FlowProcess inOverexpandedChemical Rocket Nozzles. Part 2: Side Loads due to Asymmetric Separation. NASA TM-77395 (1984).
[15] Jan Östlund, ’’ FLOW PROCESSES IN ROCKET ENGINENOZZLES WITH FOCUS ONFLOW SEPARATION AND SIDE-LOADS’’TRITA-MEK Technical Report 2002:09ISRN KTH/MEK/TR--02/09-SE.
[16] Mattsson, J., Hogman, U., Torngren, L.: A Sub Scale Test Programme on Investigation of Flow Separation and Side Loads in Rocket Nozzles. In: Proceedings of the 3rd European Symposium on Aerothermodynamics for Space Vehicles, pp. 373–378. 24–26 November 1998, ESTEC, ESA SP-426, Noordwijk, The Netherlands (1998).
[17] Reijasse, P., Servel, P., Hallard, R.: Synthesis of the 1998-1999 ONERA Works in the FSCD Working Group. Tech. Rep. RTS 49/4361 DAFE/Y, ONERA, Chatillon Cedex, France (1999).
[18] Frey,M., Stark, R., Ciezki, H.K., Quessard, F., Kwan,W.: Subscale Nozzle Testing at the P6.2 Nozzle Stand. AIAA Paper 2000- 3777, 36thAIAA/ASME/SAE/ASEE Joint Propulsion Conference (2000).
[19] Frey, M., Hagemann, G.: Restricted shock separation in rocket nozzles. J. Propuls. Power 16(3), 478–484 (2000).
[20] Hagemann, G., Frey, M.: Shock pattern in the plume of rocket nozzles: needs for design consideration. Shock Waves 17(6), 387–395 (2008).
[21] Nasuti, F., Onofri, M.: Viscous and Inviscid Vortex Generation During Nozzle Flow Transients. AIAA Paper 96-0076, 34th AIAA Aerospace Sciences Meeting and Exhibit (1996).
[22] Onofri, M., Nasuti, F., Bongiorno, M.: Shock Generated Vortices and Pressure Fluctuations in Propulsive Nozzles. AIAA Paper 98-0777, 36th AIAA Aerospace Sciences Meeting and Exhibit (1998).
[23] Onofri,M., Nasuti, F.: The Physical Origin of Side Loads in Rocket Nozzles. AIAA Paper 99-2587, 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference (1999).
[24] Courant, R., Friedrichs, K.O.: Supersonic Flow and ShockWaves, vol. 21. Springer, Berlin (1999).
[25] Terhardt, M., Hagemann, G., Frey, M.: Flow Separation and Side- Load Behavior of the Vulcain Engine. AIAA Paper 99-2762, 35th AIAA/ ASME/ SAE/ ASEE Joint Propulsion Conference (1999).
[26] Ostlund, J., Jaran, M.: Assessment of Turbulence Models in over expanded Rocket Nozzle Flow Simulations. AIAA Paper 99-2583, 35th AIAA/ ASME/ SAE/ASEE Joint Propulsion Conference
(1999) .
[27] Girard, S., Alziary de Roquefort, T.: Study of flow separation in over expanded rocket nozzles. Fourth French–Russian–Italian– Uzbeck Workshop, Marseille, France (1997).
[28] Deck, S., Guillen, P.: Numerical Simulation of Side Loads in an Ideal Truncated Nozzle. J. Propuls. Power 18(2), 261–269 (2002).
[29] Kwan,W., Stark, R.: Flow separation phenomena in subscale rocket nozzles. AIAA 2002-4229, 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit (2002).
[30] Stark, R., Wagner, B.: Experimental study of boundary layer separation in truncated ideal contour nozzles. ShockWaves, (2009).
[31] Mouronval, A.-S., Hadjadj, A.: Numerical Study of the Starting Process in a Supersonic Nozzle. J. Propuls. Power 21(2), 374–378 (2005).
[32] Ostlund, J., Damgaard, T., Frey, M.: Side-loads phenomena in highly over-expanded rocket nozzles. AIAA Paper 2001-3684 (2001).
[33] Stark, R., Kwan, W., Quessard, F., Hagemann, G., Terhardt, M.: Rocket nozzle cold gas test campaigns for plume investigations. In: Proceeding of the Fourth European Symposium on Aerothermodynamics for Space Vehicles (2001).
[34] Tomita, T., Sakamoto, H., Onodera, T., Sasaki, M., Takahashi, M., Tamura, H., Watanabe, Y.: Experimental evaluation of side-loads characteristics on TP, CTP and TO nozzles. AIAA Paper, 04-3678 (2004).
[35] A.A.Khan and T.R.Shem bharkar, 2008, Viscous flow analysis in a convergent – Divergent nozzle, International Journal of Computational Engineering Research, IJCERonline, India, Volume 3, No. 5, pp. 5-15.
[36] Adamson, T.C., Jr., and Nicholls., J.A., “On the structure of jets from Highly underexpanded Nozzles into Still Air,” Journal of the Aerospace Sciences, Vol.26, No.1, Jan 1959, pp. 16-24.
[37] Lewis, C. H., Jr., and Carlson, D. J., “Normal Shock Location in underexpanded Gas and Gas particle Jets,” AIAA Journal, Vol 2, No.4, April 1964, pp. 776-777.
[38] Martelli, E., Nasuti, F., Onofri, M.: Numerical calculation of FSS/RSS transition in highly over expanded rocket nozzle flows. Shock Waves (2009, submitted).
[39] Perrot, Y., Hadjadj, A.: Numerical simulation of transient nozzle flows. Shock Waves (2009, submitted).
[40] Papamoschou, D., Zill, A., Johnson, A.: Supersonic flow separation in planar nozzles. Shock Waves (2009, this issue).
[41] Verma, S.B.: Shock unsteadiness in a thrust optimized parabolic nozzle. Shock Waves (2009, this issue).
[42] Tomita, T., Takahashi, M., Sasaki, M., Sakamoto, H., Takahashi, M., Tamura, H.: Experimental evaluation of sideloads in LE-7A prototype engine nozzle. Shock Waves (2009).
[43] Nurnberger-Genin, C., Stark, R.: Flow transition in dual bell nozzles. Shock Waves (2009).
[44] Hadjadj, A., Kudryavtsev, A.: Computation and flow visualization in high-speed aerodynamics. Journal of Turbulence 16(6), 1–25 (2005).
[45] CNES(ed.): Proceedings of 2nd FSCD/ATACWorkshop on Nozzle FlowSeparation, ESA/ESTEC, 15–16 November, The Netherlands (2006).
[46] Nasuti, F., Onofri, M.: Shock structure in separated nozzle flows. Shock Waves (2009).
[47] Wang, T.-S.: Transient three-dimensional startup side load analysis of a regeneratively cooled nozzle. Shock Waves (2009).
[48] Deck, S.: Delayed detached eddy simulation of the end-effect regime and side loads in an overexpanded nozzle flow. ShockWaves (2009).
[49] Nguyen, A.T.,Deniau, H.,Girard, S., Alziary deRoquefort,T.:Wall pressure fluctuations in an over-expanded rocket nozzle. AIAA Paper 2002–4001 (2002).
[50] Girard, S.: Etude des charges latérales dans une tuyère supersonique surdétendue. Ph.D Thesis, University of Poitiers, France (1999).
[51] Salmon, J.T., Bogar, T.J., Sajben, M.: Laser Doppler velocimeter measurements in unsteady, separated transonic diffuser flows. AIAA J. 21(12), 1690–1697 (1983).
[52] Sajben, M., Bogar, T.J., Kroutil, J.C.: Forced oscillation experiments in supercritical diffuser flows. AIAA J. 22(4), 465–474 (1984).
[53] Dupont, P., Haddad, C.,Debiève, J.-F.: Space and time organization in a shock-induced separated boundary layer. J. Fluid Mech. 559, 255–277 (2006).
[54] Ganapathisubramani, B., Clemens, N.T., Dolling, D.S.: Effects of upstream boundary layer on the unsteadiness of shock-induced separation. J. Fluid Mech. 585, 369–394 (2007).
[55] C. Pilinski, A. Nebbache, Flow separation in a truncated ideal contour nozzle, J. Turbul. 5 (2004) 014.
[56] A. Nebbache, C. Pilinski, Pulsatory phenomenon in a thrust optimized contour nozzle, Aerosp. Sci. Technol. 10 (2006) 295–308.
[57] Frey, M. and Hagemann, G., ’’Status of Flow Separation Prediction in Rocket Nozzles’’, AIAA 98-3619, 1998 .
[58] Terhardt, M., Hagemann, G., and Frey, M., ’’Flow Separation and Side-Load Behaviour of theVulcain Engine’’, AIAA 99-2762, 1999.
[59] Mattsson, J. (changed name to Östlund 1999), Högman, U., and Torngren, L., ’’A Sub-Scale TestProgramme on Investigation of Flow Separation and Side-Loads in Rocket Nozzles’’, Proceedings ofthe 3rd European Symposium on Aerothermodynamics of Space Vehicles, ESA-ESTEC,Netherlands, November 24-26, 1998.
[60]
Chuan Tian &
Yijia Lu’’Turbulence Models of Separated Flow in Shock Wave Thrust Vector Nozzle’’
Pages 182-192 | Received 27 Mar 2012, Accepted 22 Nov 2012, Published online: 19 Nov 2014 .
[61]M. Sellam,G. Fournier,A. ChpounPh. Reijasse’’Numerical investigation of overexpanded nozzle flows’’January 2014, Volume 24,
Issue 1, pp 33–39.
[62] Habibi Omid, Ebrahimi Reza, KarimiMazraehshahi Hasan, “A review on investigation and analysis of flow separation for supersonic convergent–divergent nozzles”, 18th Int. Conference of Iranian Aerospace Society, Feb.2020.
[63] Guillaume Daviller , Jérôme Dombard , Gabriel Staffelbach , Julien Herpe & Didier Saucereau: Prediction of Flow Separation and Side-loads in Rocket NozzleUsing Large-eddy Simulation, International Journal of Computational Fluid Dynamics, DOI:10.1080/10618562.2020.1786540,2020.
[64] Vladeta Zmijanović, Boško Rašuo, Amer Chpoun’’Flow Separation Modes and Side Phenomena in an Overexpanded Nozzle’’FME Transactions (2012) 40, 111-118,