Eventos Anais de eventos
COBEM 2021
26th International Congress of Mechanical Engineering
AEROTERMODYNAMIC HEATING IN THE COMPRESSION SECTION OF A SCRAMJET DEMONSTRATOR UNDER BALLISTIC TRAJECTORY
Submission Author:
Ítalo Sabino Arrais Bezerra , RN
Co-Authors:
Ítalo Sabino Arrais Bezerra, Jonatha Wallace da Silva Araújo, Felipe Pinheiro Maia, Ramon Carneiro, Pedro Paulo Batista de Araújo, Paulo Toro
Presenter: Pedro Paulo Batista de Araújo
doi://10.26678/ABCM.COBEM2021.COB2021-1940
Abstract
The crescent demand for more efficient and less expensive propulsion systems for space access vehicles is characterized by the development of advanced propulsion projects in several research centers around the world. The airbreathing propulsion technology based on supersonic combustion (scramjet) is a potentially advantageous alternative in comparison the usual and already consolidated system, the rocket engines. This paper focuses on the analytical investigation of the phenomenon of aerothermodynamic heating in a scramjet vehicle flight during an ascending ballistic trajectory. In this study, the methodology to evaluate the effects of this variation on the aerothermodynamic heating in the compression section of a scramjet demonstrator vehicle along the trajectory is present. The convective heat transfer magnitude was calculated using combined empirical correlations derived from the theories of Fay-Riddell, Lees and van Driest, according to each region of interest, respectively, the point of stagnation of the flow located at the leading-edge of the vehicle, the cylindrical segment outside the stagnation point and the linear ramp surface. The trajectory is vertical and ascending with a speed corresponding to Mach number of 6.8 and altitude varies between 30 to 80 km. Several combinations were considered, varying the temperature on the wall (1000, 1400 and 1800 K) and the curvature radius of the vehicle leading-edge (1, 5 and 10 mm). The present analysis indicates, for the conditions imposed, that the heat transfer magnitude is maximum at the stagnation point and describes characteristic behavior of sinusoidal curves on the cylindrical surface, and constant under the ramps. As indicated by the results, the heat transfer decrease through an upward trajectory and increases due to the effect of increasing wall temperature and the reduction in the curvature radius.
Keywords
Scramjet, Hypersonic Flow, Aerothermodynamics Heating
