05 - Propulsion
EXPERIMENTAL STUDY ON THE CHARACTERISTICS OF SONIC GAS INJECTION INTO SUPERSONIC CROSSFLOW WITH MA2.0 AND MA3.0
C.-H. Liang¹, M.-B. Sun¹, Y.-X. Yang¹, Y. Liu, China Aerodynamics Research and Development Center, China; T.-Y. Wang¹, G.-W. Ma¹, F. Li¹, C. Wang¹; ¹National University of Defense Technology, China
With the development of the aerospace industry, hypersonic propulsion has always been a concern of experts and scholars. Transverse injection into a supersonic stream is one of the most fundamental canonical flows for supersonic propulsion community. With the flying speed of the hypersonic aerocraft changing, the inflow Mach number of the scramjet differs. This paper compared the characteristics of sonic gas injection into a supersonic crossflow with different Mach numbers (Ma2.0 and Ma3.0). rnNanoparticle-based Planar Laser Scattering (NPLS) experiments were conducted to visualize the flow field on several slices, while oil flow techniques were employed to obtain the fraction characteristics in the near wall region.