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High-Speed Supersonic and Hypersonic Engines
Published in Ahmed F. El-Sayed, Aircraft Propulsion and Gas Turbine Engines, 2017
Hypersonic flight is identified as flight with a Mach number exceeding 5 [14]. The main problem of that speed range is the very large wave drag. To minimize this, both the aircraft and engine must be completely reconfigured. Until now, apart from in research work, no civil aircraft can fly at hypersonic speeds. Only rockets can.
Thermal Protective Properties of the Allomyrina dichotoma Beetle Forewing for Thermal Protection Systems
Published in Heat Transfer Engineering, 2019
Vinh Tung Le, Ngoc San Ha, Nam Seo Goo
During flight, hypersonic aircraft experience significant aerodynamic heating as well as aerodynamic loads due to their hypersonic speed. Therefore, such aircraft need a thermal protection system (TPS) that can withstand both thermal and aerodynamic loads to reduce structural damage, especially at the leading edges and nose cone. So far, some prominent TPSs have been proposed and investigated by many researchers [1]–[4], but the demand for a novel and highly efficient design for a TPS remains high. Nature provides many examples of lightweight, high-strength, and high-thermal resistant composite structures that evolution has optimized through a long ecosystem history.
Aerothermodynamic design and performance analysis of modified nose cones for space reentry vehicles
Published in International Journal of Ambient Energy, 2022
Raja Muthu, S. Siva Lakshmi, Santhoshini Babu
The solver used is density-based formulation since the problem is a compressible flow (hypersonic velocity model). The Mach number for simulation is chosen as 5 (hypersonic speed). SST k–ω (shear stress transport k–omega) turbulence model is chosen (Deepak, Vinu, and Chandran 2017). It is a hybrid two equation model combining the Wilcox k–ω and the k–ϵ models. The k–ϵ model predicts well far from the boundaries (wall) and k–ω model predicts well near wall.
A parametric study on the design factors influencing the thermal performance of nickel alloy C263 sandwich panels
Published in Australian Journal of Mechanical Engineering, 2023
T. Mahender, I. Balasundar, T. Raghu
As there is an ever increasing demand to enhance the speed of aero-engines used for military as well as civil applications, advanced engines such as ramjets, scramjets, etc., are being developed and evaluated (Kerrebrock 1992). The speeds of these advanced engines are usually denoted in Mach number (M). A scramjet, air-breathing engine that moves at supersonic (1.2 ≤ M ≤ 5.0) and hypersonic speeds (5 ≤ M ≤ 10) are currently developed to meet a wide variety of applications (Segal 2009). Vehicles are subjected to severe and complex environment flying at such high speeds that result in aero-dynamic loading and aero-thermal heating, and hence a thermal protection system is required to safeguard the structure and other components during the entire flight duration which usually ranges from few seconds to minutes. Generally, in a thermal protection system, a material or a combination of materials work together to safeguard the vehicle from adverse conditions (Dorsey et al. 2002; Duffa 2013; Blosser 2002; Blosser et al. 1998; Gorton, Shideler, and Webb 1993; Blosser et al. 2004). The function of these thermal protection systems (TPS) is to block, absorb and/or radiate excessive heat generated while the vehicle is in cruise, protect the airframe and maintain the associated components present inside the vehicle within a specified temperature limit of 320 ± 5 K. Numerous types of TPS are used for a variety of applications e.g., flexible insulation blankets (FIB), ablative heat shields mostly used in re-entry vehicles, fused silica tiles and metallic sandwich panels (Dorsey et al. 2002; Duffa 2013; Blosser 2002; Blosser et al. 1998; Gorton, Shideler, and Webb 1993; Blosser et al. 2004). Selection of TPS for a particular application depends on several factors such as the vehicle speed, quantum of heat generated during the flight, etc. However, the main objective behind selecting a TPS would be based on their weight/density or areal density and their thermal insulation capability (Dorsey et al. 2002; Duffa 2013; Blosser 2002; Blosser et al. 1998; Gorton, Shideler, and Webb 1993; Blosser et al. 2004).