Eventos Anais de eventos
ENCIT 2022
19th Brazilian Congress of Thermal Sciences and Engineering
AERODYNAMIC HEATING CALCULATION FOR A HYPERSONIC AIRBREATHING PROPULSION SYSTEM AT MACH NUMBER 7
Submission Author:
Felipe Jean da Costa , SP , Brazil
Co-Authors:
Felipe Jean da Costa, Gustavo Jean da Costa, Alana Brito
Presenter: Felipe Jean da Costa
doi://10.26678/ABCM.ENCIT2022.CIT22-0569
Abstract
The Hypersonic Airbreathing Propulsion System, designed at the Brazilian Aerospace Startup BRENG Engineering and Technology, is a technological demonstrator endowed with Scramjet Engine to fly in the Earth’s atmosphere at 30 km altitude at speeds corresponding to the Mach number 7.Considering the high speed flight regime, the originated shockwaves and the viscous forces yield the phenomenon called aerodynamic heating under the aerospace vehicle airframe, causing the friction between the fluid filaments and the body or compression at the stagnation regions of the leading edge that converts the kinetic energy into heat within a thin layer of air which blankets the body. The temperature inside this mentioned layer increases with the square of the speed and is concentrated in the boundary-layer, where heat will flow readily from the boundary-layer to the hypersonic aerospace vehicle structure. Fay and Riddell and Eckert methods are applied to evaluate at the stagnation point and over the flat plate segments for the model, in order to calculate the aerodynamic heating allowing to determine the thermal field over the model's surface from the leading edge to the trailing edge of the proposed Hypersonic Airbreathing Propulsion System for Mach number 7 condition.
Keywords
Aerodynamic heating, hypersonic airbreathing propulsion, Scramjet
