533.16 Procedure for numerical solution of equations of laminar-turbulent boundary layer on an axially symmetrical blunt body in a jet of combustion gases of liquid-propellant engine

Gorskiy V. V. (Bauman Moscow State Technical University/JSC MIC NPO Mashinostroyenia), Kovalsky M. G. (JSC MIC NPO Mashinostroyenia)


doi: 10.18698/2309-3684-2018-2-96108

Currently, carbon-based materials are widely used as an ablative thermal protection for high-heat constructional elements in air and space en-gineering. In its turn, forecasting a change in shape of external surfaces of the specified elements with the course of time, which is determined by scorching of thermal protection, cannot be separated from the use of calcula-tion and theoretical procedures, which describe course of different phys-ico-chemical and mechanical processes associated with course of the considered event. Thereby, it is mandatory to approve such procedures through the re-sults of experi-mental studies, conducted in jets inside aerodynamic tunnels.
Among primary evidences of ablation of carbon-based materials is erosion (mass loss), which is usually observed in high-pressure gas flows. Meanwhile, it is required to carry out studies on large-scale models in the course of development tests, and that had de-termined the wide use of under-expanded jets of combustion gases of liquid-propellant rocket engines (LPE) for simulation of erosion of thermal protection.
Among the basic problems, encountering during solution of this kind of tasks, is calcu-lation of laminar-turbulent heat exchange in the conditions of gradient flow past blunt-ed point of the tested model by a diverging gas jet. This article is dedicated to the solu-tion of this problem and includes the modified version of semi-empirical model of ap-parent turbulent viscosity, approved by the results of experimental studies. This article shows that the use of this method makes it possible to specify significantly thermal con-di-tions of the model in comparison with the use of effective length method, which is used universally in practical work.

[1] Gorsky V.V., Nosatenko P.Ya. Matematicheskoe modelirovanie protsessov tep-lo- i massoobmena pri aerotermokhimicheskom razrushenii kompozitsionnykh teplozashchitnykh materialov na kremnezemnoy osnove [Mathematical model-ing the heat and mass transfer processes in the aerothermochemical destruc-tion of composite thermal shield materials based on silica]. Moscow, Nauch-nyy mir Publ., 2008, 256 p.
[2] Gorskij V.V., Resh V.G. The study of carbon matherial’s aerothermochemical destruction in combustion products of liquid-propellant rocket engines. 29th Congress of the International Council of the Aeronautical Sciences, Saint Pe-tersburg, 2014, vol. 1–6, pp. 841–849.
[3] Gorskii V.V.. Cosmonavtika i raketostroenie – Space and rocket science. 2017. №3. P. 90.
[4] Gorskii V.V., Pugach M.A. Nauka i tekhnologii. Izbrannye Trudy Vserossiyskoi konferencii po problemam nauki I tekhnologii – Science and technology. Se-lected works of the all-Russian conference on science and technology. Mos-cow, RAS, 2014. P. 27-56.
[5] Горский В.В., Ковальский М.Г. Matematicheskoe modelirovanie i chislennye menody – Mathematical modeling and Computational Methods, 2017, no. 2, p. 65–80.
[6] Withopf J.F., Hall J.R. Raketnaya tekhnika i kosmonavtika – Rocket and space technology. 1972. Т.10, № 10. P. 71.
[7] Widhopf G.F. Laminar, transitional and turbulent Heat Transfer Measurement on a yawed Blunt conical Nose tip. TR-0172 (S2816-60), 3, Aug, 1972, the aer-ospace Corp., San Bernardino, Calif.
[8] Loitsyansky L.G. Mekhanika zhidkosty i gaza [Fluid and gas mechanics]. Mos-cow, Drofa Publ. 2003. 840 p.
[9] Trusov, B. Simulation of chemical and phase equilibria at high temperatures. (ASTRA-4 / pc). Technical description of the program. Moscow, center of soft-ware systems of MSTU. N. Uh. Bauman. 1992.
[10] Zemlyansky B.A., Lunev V.V., Vlasov V.I., Gorshkov A.B., Zalogin G.N. Kon-vektivnyy teploobmen letatelnykh apparatov [Aircraft convective heat ex-change]. Moscow, Fizmatlit Publ., 2014, 380 с.
[11] Cebeci T., Smith A.M.O. Analysis of turbulent boundary layers. New York, San Francisco, London. Academic Press. 1974. 404p.
[12] Anderson A.D. Surface roughness effect. Boundary layer transition data corre-lation and analysis. Passive Nosetip Technology (PANT) Program. 1974. Part III, SAMSO TR-74-86.
[13] Phinney R.E. Mechanism for heat-transfer to a rough blunt body. Letters in heat and mass transfer. 1974. Vol. 1, № 2. P. 181.
[14] Powars C.A. Roughness effects augment heating data correlation and analysis. Passive Nose tip Technology (PANT) Program. 1974. V. XI. SAMSO TR-74-86.

Горский В.В., Ковальский М.Г. Методика численного решения уравнений ламинарно-турбулентного пограничного слоя на осесимметричном затупленном теле в струе продуктов сгорания ЖРД. Математическое моделирование и численные методы, 2018, № 2, с. 96–108.

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