Search Results for “flow separation” – Collected book of scientific-technical articles https://journal.yuzhnoye.com Space technology. Missile armaments Thu, 04 Jun 2026 08:18:21 +0000 en-GB hourly 1 https://journal.yuzhnoye.com/wp-content/uploads/2020/11/logo_1.svg Search Results for “flow separation” – Collected book of scientific-technical articles https://journal.yuzhnoye.com 32 32 10.2.2018 Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests https://journal.yuzhnoye.com/content_2018_2-en/annot_10_2_2018-en/ Thu, 07 Sep 2023 11:29:45 +0000 https://journal.yuzhnoye.com/?page_id=30766
It was planned to start the engine with water-cooled nozzle extension without vacuumizing and without gad dynamic pipe, which conditioned operation with flow separation at the output edge of water-cooled nozzle extension. Therefore, the calculation of flow in the nozzle with water-cooled extension, flow separation place, and thermal load on watercooled nozzle extension during operation in ground conditions is an important task. The gas dynamic analysis of the nozzle with water-cooled extension showed the importance of using the turbulent flow model k-ω SST for the flows with internal separation of boundary layer and with flow separation at nozzle section. The use the flow model k-ω SST for calculation of nozzle with flow separation or with internal transitional layer allows adequately describing the flow pattern, though, as the comparison with experimental data showed, this model predicts later flow separation from the wall than that obtained in the tests.
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10. Calculation of Gas Flow in High-Altitude Engine Nozzle and Experience of Using Water-Cooled Nozzle Head during Tests

ISSN: 2617-5525

e-ISSN: 2617-5533

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2018 (2); 83-93

DOI: https://doi.org/10.33136/stma2018.02.083

Language: Russian

Annotation: At Yuzhnoye State Design Office, the Cyclone-4 launch vehicle 3rd stage engine has been developed and is under testing. For adjustment of the engine and test bench systems, in the first firing tests the radiation-cooled nozzle extension was replaced with a steel water-cooled one. It was planned to start the engine with water-cooled nozzle extension without vacuumizing and without gad dynamic pipe, which conditioned operation with flow separation at the output edge of water-cooled nozzle extension. Therefore, the calculation of flow in the nozzle with water-cooled extension, flow separation place, and thermal load on watercooled nozzle extension during operation in ground conditions is an important task. Selection of turbulent flow model has a noticeable impact on prediction of flow characteristics. The gas dynamic analysis of the nozzle with water-cooled extension showed the importance of using the turbulent flow model k-ω SST for the flows with internal separation of boundary layer and with flow separation at nozzle section. The use the flow model k-ω SST for calculation of nozzle with flow separation or with internal transitional layer allows adequately describing the flow pattern, though, as the comparison with experimental data showed, this model predicts later flow separation from the wall than that obtained in the tests. The calculation allows obtaining a temperature profile of the wall and providing the recommendations for selection of pressure measurement place in the nozzle extension for the purpose of reducing sensors indication error. With consideration for the special nature of the nozzle extension wall temperature field, the cooling mode was selected. The tests of RD861K engine nozzle with water-cooled extension allow speaking about its successful use as a required element for testing engine start and operation in ground conditions without additional test bench equipment.

Key words: turbulent flow, flow separation, cooling, technological extension

Bibliography:
1. Massiet P., Rocheque E. Experimental Investigation of Exhaust Diffusors for Rocket Engines. Investigation of Liquid Rocket Engines. М., 1964. P. 96-109.
2. Mezhevov A. V., Skoromnov V. I., Kozlov A. V. et al. Introduction of Radiation Cooling Nozzle Head of Made of Carbon-Carbon Composite Material on DM-SL Upper Stage 11D58M Main Engine. News of Samara Aerospace University. No. 2 (10). 2006. P. 260-264.
3. Fluent. Software Package, Ver. 6.2.16, Fluent Inc., Lebanon, NH, 2004.
4. Wilcox D. C. Turbulence Modeling for CFD. DCW Industries, Inc. La Canada, California, 1998. 460 р.
5. Andersen D., Tannehill J., Platcher R. Computational Hydromechanics and Heat Exchange: in 2 volumes М., 1990. 384 p.
6. Rodriguez C. G., Culter, A. D. Numerical Analysis of the SCHOLAR Supersonic Combustor, NASA-CR-2003-212689. 2003. 36 р.
7. Rajasekaran A., Babu V. Numerical Simulation of Three-dimensional Reacting Flow in a Model Supersonic Combustor. Journal of Propulsion and Power. Vol. 22. No. 4. 2006. Р. 820-827. https://doi.org/10.2514/1.14952
8. Spalart P., Allmaras S. A one-equation turbulence model for aerodynamic flows: Technical Report. American Institute of Aero-nautics and Astronautics. AIAA-92-0439. 1992. Р. 5-21. https://doi.org/10.2514/6.1992-439
9. Launder B. E., Spalding D. B. Lectures in Mathematical Models of Turbulence. London, 1972. Р. 157-162.
10. Rajasekaran A., Babu V. Numerical Simulation of Three-dimensional Reacting Flow in a Model Supersonic Combustor. Journal of Propulsion and Power. Vol. 22. No. 4. 2006. Р. 820-827. https://doi.org/10.2514/1.14952
11. Ten-See Wang. Multidimensional Unstructured Grid Liquid Rocket-Engine Nozzle Performance and Heat Transfer Analysis. Journal of Propulsion and Power. Vol. 22. No. 1. 2006. 21 р. https://doi.org/10.2514/1.14699
12. Hyun Ko, Woong-Sup Yoon. Performance Analysis of Secondary Gas Injection into a Conical Rocket Nozzle. Journal of Propulsion and Power. Vol. 18, No. 3. 2002. Р. 585-591. https://doi.org/10.2514/2.5972
13. Wilson E. A., Adler D., Bar-Yoseph P. Thrust-Vectoring Nozzle Performance Mode-ling. Journal of Propulsion and Power. Vol. 19, No. 1. 2003. Р. 39-47. https://doi.org/10.2514/2.6100
14. Gross A., Weiland C. Numerical Simulation of Hot Gas Nozzle Flows. Journal of Propulsion and Power. Vol. 20, No. 5. 2004. Р. 879-891. https://doi.org/10.2514/1.5001
15. Gross A., Weiland C. Numerical Simulation of Separated Cold Gas Nozzle Flows. Journal of Propulsion and Power. Vol. 20, No. 3. 2004. Р. 509-519. https://doi.org/10.2514/1.2714
16. Deck S., Guillen P. Numerical Simulation of Side Loads in an Ideal Truncated Nozzle. Journal of Propulsion and Power. Vol. 18, No. 2. 2002. Р. 261-269. https://doi.org/10.2514/2.5965
17. Östlund J., Damgaard T., Frey M. Side-Load Phenomena in Highly Overexpanded Rocket Nozzle. Journal of Propulsion and Power. Vol. 20, No. 4. 2004. Р. 695-704. https://doi.org/10.2514/1.3059
18. Goldberg U. C. Separated Flow Treatment with a New Turbulence Model. AIAA Journal. Vol. 24, No. 10. 1986. Р. 1711-1713. https://doi.org/10.2514/3.9509
19. Golovin V.S., Kolchugin B.A., Labuntsov D.A. Experimental Investigation of Heat Exchange and Critical Heat Loads at Water Boiling in Free Motion Conditions. 1963. Vol. 6, No 2. p. 3-7.
20. Mikheyev М. А., Mikheyeva I. M. Heat-Transfer Principles. 2nd edition stereotyped. М., 1977. 343 p.
21. Kutateladze S. S., Leontyev A. I. Heat-Mass Exchange and Friction in Turbulent Boundary Layer. М., 1972. 341 p.
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11.1.2016 Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation https://journal.yuzhnoye.com/content_2016_1/annot_11_1_2016-en/ Tue, 23 May 2023 13:06:36 +0000 https://journal.yuzhnoye.com/?page_id=27621
Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation ISSN: 2617-5525 e-ISSN: 2617-5533 Authors: Ushkin M. quot;Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation," Космическая техника. V., Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation, Космическая техника. Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation. Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation. (2016) Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation, Космическая техника. "Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation." Космическая техника. Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation.
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11. Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation

ISSN: 2617-5525

e-ISSN: 2617-5533

Organization:

Yangel Yuzhnoye State Design Office, Dnipro, Ukraine

Page: Kosm. teh. Raket. vooruž. 2016 (1); 68-75

Language: Russian

Annotation: The factors are considered that have an impact on the value and behavior of SRM flow rate and thrust characteristics after stage separation (in the leg of deep decay). It is shown that thrust behavior in the leg of deep decay is determined by two main processes: afterburning of solid propellant charge residues within the first 3-5 s and mass input of internal thermal protection coating destruction products within the following several tenths of second. The dependences are proposed for design evaluation of SRM intra-ballistic and flow rate/thrust characteristics.

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11.1.2016 Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation
11.1.2016 Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation
11.1.2016 Methodology of Design Evaluation of Main SRM Flowrate-Thrust Characteristics after Stage Separation
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Сollected book of scientific-technical articles https://journal.yuzhnoye.com/ Thu, 04 May 2023 07:56:30 +0000 https://enovathemes.com/samatex2/?page_id=41
Design and development of components of space launch vehicles and combat missiles (liquid-propellant and solid-propellant rocket engines, propulsion systems, control systems, separation systems, payload equipment, etc.) Design and development of components for ground-based systems (facilities, fueling systems, prelaunch processing systems, etc.) Design and development of spacecraft and their components.
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The collection of scientific and technical articles Space Technology. Missile Armaments is a specialized professional publication that publishes new results of theoretical and experimental research and development in the field of aviation and space rocket technology.

The subject area of the Collection corresponds to the Mechanical Engineering and Machine-Building cluster (G8 Materials Science, G9 Applied Mechanics, G10 Metallurgy, G11 Industrial Engineering, and G12 Aviation, Rocket, and Space Technology).

The scope of the Collection covers the development and operation of state-of-the-art military missile and space launch systems, spacecraft, and satellite systems, as well as their components, including:

  • Design and development of missile and ground-based systems.
  • Design and development of components of space launch vehicles and combat missiles (liquid-propellant and solid-propellant rocket engines, propulsion systems, control systems, separation systems, payload equipment, etc.)
  • Design and development of components for ground-based systems (facilities, fueling systems, prelaunch processing systems, etc.)
  • Design and development of spacecraft and their components.
  • Problems of aerodynamics, heat and mass transfer, flight theory, loading, and structural strength.
  • Problems of efficiency, reliability, safety, and economic feasibility of space launch systems.
  • Other aspects that are directly related to the development and operation of space launch systems.
  • Other topics corresponding to the Mechanical Engineering and Manufacturing

 

The target audience is scientists, postgraduate students, and specialists whose scientific interests include achievements in aviation, rocket, and space technology (G12) and other specialties within the Mechanical Engineering and Machine-Building cluster (G8, G9, G10, and G11).

The Collection is included in the List of Scientific Professional Publications of Ukraine (category B) in accordance with Order No. 1188 of the Ministry of Education and Science, dated September 24, 2020 (Appendix 5).

The Collection is registered in the unified open scientific identification system ROR (Research Organization Registry).

The collection of scientific and technical articles Space Technology. Missile Armaments has been published since April 1979. It is currently published in printed (ISSN 2617-5525) and identical in content, full-text electronic forms (e-ISSN 2617 5533).

About the collected articles

ISSN 2617-5525 (Print); e-ISSN 2617-5533 (Online)

obl1

ISSN 2617-5525 (Print);
e-ISSN 2617-5533 (Online)

Publisher and founder: Yuzhnoye State Design Office, EDRPOU code 14308304.

Publication DOI: 10.33136/stma

Publication languages: Ukrainian, English.

Periodicity: twice a year.
In 2023-2024, taking into account the announcement of martial law in Ukraine, the Collection was issued once a year.
In 2025, the editorial and publication process was stabilized, and the Collection resumed publication every six months.

State registration of the printed media in the National Council of Ukraine on Television and Radio Broadcasting: media identifier – R30-01817 of 04.12.2023.

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