Ana Maria Pereira LARA, Israel REGO, Lucas A. G. Ribeiro, Pedro P. B ARAÚJO, Lucas Galembeck, Dermeval CARINHANA JR, Tiago ROLIM
DOI Number: 10.60853/b7dm-xc15
Conference number: HiSST-2024-00101
The scramjet engine is a hypersonic airbreathing propulsion system based on supersonic combustion. The engine model consists of an inlet composed by a blunt leading edge region and three compression ramps (compression section), by the combustion and expansion sections. The model was designed to operate at hypersonic speeds in the stratosphere. Scramjets are ideal as engines for hypersonic flights, so they are subjected to high heat transfer loads, specifically on the leading edge. Thus, this paper applies Fay and Riddell’s theory, Lees´s theory and Eckert’s theory to study the aerodynamic heating at the stagnation point, blunt region and flat regions of the engine model, respectively. Four models have been considered for the determination of the thermodynamic properties and for the calculation of the heat flux, being: calorically perfect gas without and with boundary layer effects, thermodynamic equilibrium gas without and with boundary layer effects. The highest values of heat flux were found at the stagnation point. The use of a blunt region was efficient for the reduction of the heat flux coming at the stagnation point (about 96% of reduction). The greatest increases in the heat flux in the flat regions were due to the differences between the laminar and turbulent flow regimes and due to the passage of the flow through the reflected shock wave (input of the isolator). The lowest heat flux values were found in the flat regions while the flow was still laminar (1st ramp of compression and up to about half of the 2nd ramp of compression).