TY - JOUR
T1 - Numerical investigation of axisymmetric intake flowfield and performance for scramjet-powered ascent flight
AU - Fujio, Chihiro
AU - Brahmachary, Shuvayan
AU - Ogawa, Hideaki
N1 - Funding Information:
The authors acknowledge the support provided by the Japan Society for the Promotion of Science through the JSPS KAKENHI Grant Number JP 17K20144. Hideaki Ogawa is thankful to RMIT University for the resources enabled by the adjunct appointment.
Funding Information:
The authors acknowledge the support provided by the Japan Society for the Promotion of Science through the JSPS KAKENHI Grant Number JP 17K20144 . Hideaki Ogawa is thankful to RMIT University for the resources enabled by the adjunct appointment.
Publisher Copyright:
© 2021
PY - 2021/4
Y1 - 2021/4
N2 - Air intakes play a crucial role in the operation of scramjet engines, one of the most promising hypersonic airbreathing propulsion technologies for efficient and flexible space transportation, it is thus essential to accurately understand and predict the flowfields for high-performance intake design, especially in varying operating conditions. Axisymmetric intake flowfields are investigated numerically assuming a typical scramjet operation on a constant dynamic pressure ascent trajectory, aiming to achieve scramjet-powered access-to-space. Physical insight into scramjet flowfields at various flight altitudes and Mach numbers have been gained by means of high-resolution simulation to resolve the viscous flowfields. High levels of adaptive mesh refinement have identified detailed flow phenomena including shock reflection, interactions, and boundary layer as well as their aerodynamic and aerothermal effects on pressure and temperature fields. In particular, Mach reflection characterized by a Mach disk has been found to occur at the centerline, even in the operating conditions where regular reflection would result from computational simulation without mesh adaption. The intake performance has been evaluated with respect to the compression efficiency, drag, and exit temperature. The intake drag has been found to decrease at higher Mach numbers at higher altitudes on a constant dynamic pressure trajectory during acceleration due to reduced pressure drag while viscous drag varies little. Rather little influence of varying wall conditions has been observed on the intake drag between the isothermal and adiabatic wall conditions due to counteracting behavior between viscous and pressure drag components.
AB - Air intakes play a crucial role in the operation of scramjet engines, one of the most promising hypersonic airbreathing propulsion technologies for efficient and flexible space transportation, it is thus essential to accurately understand and predict the flowfields for high-performance intake design, especially in varying operating conditions. Axisymmetric intake flowfields are investigated numerically assuming a typical scramjet operation on a constant dynamic pressure ascent trajectory, aiming to achieve scramjet-powered access-to-space. Physical insight into scramjet flowfields at various flight altitudes and Mach numbers have been gained by means of high-resolution simulation to resolve the viscous flowfields. High levels of adaptive mesh refinement have identified detailed flow phenomena including shock reflection, interactions, and boundary layer as well as their aerodynamic and aerothermal effects on pressure and temperature fields. In particular, Mach reflection characterized by a Mach disk has been found to occur at the centerline, even in the operating conditions where regular reflection would result from computational simulation without mesh adaption. The intake performance has been evaluated with respect to the compression efficiency, drag, and exit temperature. The intake drag has been found to decrease at higher Mach numbers at higher altitudes on a constant dynamic pressure trajectory during acceleration due to reduced pressure drag while viscous drag varies little. Rather little influence of varying wall conditions has been observed on the intake drag between the isothermal and adiabatic wall conditions due to counteracting behavior between viscous and pressure drag components.
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U2 - 10.1016/j.ast.2021.106531
DO - 10.1016/j.ast.2021.106531
M3 - Article
AN - SCOPUS:85100002431
SN - 1270-9638
VL - 111
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
M1 - 106531
ER -