Modeling the effect of asymmetric flow on the process of overburning a blunted wedge made of carbon-carbon composite material during high-speed flight with a given angle of attack

Аuthors

Gorsky V. V.^{1, 2}, Brodsky M. Y.^1*, Nikitin A. A.³

1. Military industrial corporation «NPO Mashinostroyenia», 33, Gagarina str., Reutov, Moscow region, 143966, Russia
2. Bauman Moscow State Technical University, MSTU, 5, bldg. 1, 2-nd Baumanskaya str., Moscow, 105005, Russia
3. JSC Concern “Morinformsystem-Agat”, Moscow, Russian Federation

*e-mail: m.yu.brodskij@vpk.npomash.ru

Abstract

At the present stage of technology development, when designing high-speed aircraft, there is an objective need to equip them with ablative thermal protection. In this case, the trajectories of highspeed aircraft usually contain areas where the flight is carried out with non-zero angles of attack. In this regard, it is of particular interest to conduct a study of the effect of asymmetric flow on the ablation of carbon-carbon composite materials on the edges of aerodynamic surfaces at high supersonic flight speeds. One of the problems solved in the design of aircraft capable of long term high-speed flight in dense layers of the Earth's atmosphere is the intensive aerodynamic heating of their structural elements. As the enthalpy of deceleration of the incoming flow increases with increasing flight speed, the aircraft construction materials are exposed to increasingly intense heat fluxes, resulting in their ablation. The ablation process during flight modifies the geometry of the aircraft, determining its current shape at each moment of time.The purpose of the study conducted in this article is to analyze the evolution of the geometry of a heat-loaded structural element, which initially has the shape of a blunted wedge made of carbon-carbon composite material, which is burned for a long time during flight with constant values of altitude, speed and angle of attack. It is known that the ablation rate of the material at different points of the aircraft surface is not the same and depends on local pressure values and the intensity of heat fluxes determined by the flow process. Decisive influence the heat exchange on the surface of the aircraft is influenced by processes occurring in a relatively thin boundary layer. The transition from a laminar to a turbulent layer leads to a significant increase in the intensity of heat supply to the surface of the apparatus, as a result of which. The gasification of the material is becoming more intensive. This article is based on the results of previous work of the scientific school of the MIC NPO of Mechanical Engineering. The models and techniques used are based on the results of fundamental experiments and have been tested by practice.

Keywords:

asymmetric flow, blunted wedge, overgrown shape of the body flying at an angle of attack, laminar-turbulent heat exchange, cccm

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