Eventos Anais de eventos
COBEM 2021
26th International Congress of Mechanical Engineering
OBLIQUE SHOCK WAVE FOR AIR AT HIGH TEMPERATURE
Submission Author:
Vinícius Lamas von Sohsten , RN
Co-Authors:
Vinícius Lamas von Sohsten, Gabriel Afonso Pichorim, Pedro Paulo Batista de Araújo, Heidi Korzenowski, George Marinho, Paulo Toro
Presenter: Vinícius Lamas von Sohsten
doi://10.26678/ABCM.COBEM2021.COB2021-1661
Abstract
Academically, the oblique shock wave relationships are obtained considering, the inviscid flow (no boundary layer effects) and the airflow behaves as a calorically perfect gas (no high temperature effects). In general, for an aerospace vehicle design using airbreathing propulsion, based on supersonic combustion (scramjet technology), the analytical methodology is applied. The scramjet vehicle flying, in a dense Earth atmospheric air, in hypersonic velocity, oblique shock waves are established, promoting high temperature of the airflow that experiment the oblique shock waves, enough to generate air (oxygen and/or nitrogen) dissociation. Therefore, oblique shock relations for air in thermodynamic equilibrium are developed, and validated by academic literature available and applied to scramjet vehicle, with leading-edge (turning) deflection angle of 20o and 30o, flying at hypersonic velocities, corresponding to Mach numbers 7 and 10, at 30 km altitude. The results for the pressure, temperature and density ratios and flow deflection across the shock wave are presented as function of the shock wave angle and airflow velocities. Oblique shock relations for perfect gas airflow and airflow in thermodynamic equilibrium are compared.
Keywords
Oblique Shock Wave, air in equilibrium, analytical analysis, scramjet inlet
