Jessen FC, Peters MT, (1963) Comparison between swivelling nozzles with split lines upstream and downstream of the throat. Defense Technical Information Center, AD0339867.
 Thiokol Chemical Corporation (1970) TVC system study program. NASA Lewis research center, Accession Number: N70 36359.
 Ikaza D (2000) Thrust vectoring nozzle for modern military aircraft. NATO R&T Organization Symposium, Braunschweig, Germany.
 Lee SN, Baek SW (2009) Thrust vector control by flexible nozzle and secondary fluid injection. ICCES 10(4): 81–90.
 Ciucci A, Laccarino G, Amato M (1998) Numerical investigation of 3D two phase turbulent flow in solid rocket motors. Italian Aerospace Research Center, AIAA: 98–3966.
. Hui-man M, Si-ai F, Han-ping C (2005) Numerical study of unsteady flow in thrust vectoring nozzle. International Journal of Turbo and Jet Engines 22 31–0.
 Strome RK, USAF Lt (1969) Test firing of supersonic split-line nozzle. Air force rocket propulsion laboratory,technical report AFRPL-TR-69-203.
 Balakrishna B, Indana S, Reddy RP (2013) Investigation of supersonic flow through conical nozzle with various angles of divergence. International Journal of Mechanical Engineering 2(1): 9-16.
 Yakhot V, Orszag SA, Thangam S, Gatski TB & Speziale CG (1992), Development of turbulence models for shear flows by a double expansion technique, Physics of Fluids A, 4(7), 1510-1520.
 Kader B (1981) Temperature and concentration profiles in fully turbulent boundary layers. Int J Heat Mass Transfer 24: 1541–1544.
 Barth TJ, Jespersen D (1989) The design and application of upwind schemes on unstructured meshes. Technical Report AIAA-89-0366. AIAA 27th Aerospace Sciences Meeting, Reno, Nevada.
 Liou MS (1996) A sequel to AUSM: AUSM+. Journal of Computational Physics 129: 364–382.
 Ellison JR (1970) Evaluation of Titan III AFT closure insulation. Air force rocket propulsion laboratory technical report AFRPL-TR-70-89.