TY - GEN
T1 - Influence of surface temperature on aerodynamics and aerothermodynamics of an inflatable decelerator
AU - Guo, Jinghui
AU - Lin, Guiping
AU - Bu, Xueqin
AU - Fu, Shiming
AU - Chao, Yanmeng
N1 - Publisher Copyright:
© 2017 IEEE.
PY - 2017/9/14
Y1 - 2017/9/14
N2 - Regarding the hypersonic flow over an Earth-reentry inflatable decelerator from 80 km to 50 km altitude, the influence of surface temperature on the aerodynamics and aerothermodynamics of the vehicle were investigated. By applying surface radiative equilibrium condition and several fixed surface temperatures (300 K to 2000 K) as boundary conditions, a system of Navier-Stokes equations incorporating turbulent effects was numerically solved based on finite volume method. The results show that the surface pressure on the forebody and afterbody demonstrates almost coincident distribution at different surface temperatures. With the surface temperature rising, the shear stress on the forebody and afterbody presents most augmentation by 47.35% and 40.77% respectively. The axial force coefficient decreases while the normal force coefficient and pitch moment coefficient increase with a maximum difference of 9%. Additionally, the surface heat flux varies differently on each surface region with the surface temperature rising whereas the total heat load decreases, and the maximum discrepancy of heat flux exceeds 10% on the nose, cone body and centerbody bottom.
AB - Regarding the hypersonic flow over an Earth-reentry inflatable decelerator from 80 km to 50 km altitude, the influence of surface temperature on the aerodynamics and aerothermodynamics of the vehicle were investigated. By applying surface radiative equilibrium condition and several fixed surface temperatures (300 K to 2000 K) as boundary conditions, a system of Navier-Stokes equations incorporating turbulent effects was numerically solved based on finite volume method. The results show that the surface pressure on the forebody and afterbody demonstrates almost coincident distribution at different surface temperatures. With the surface temperature rising, the shear stress on the forebody and afterbody presents most augmentation by 47.35% and 40.77% respectively. The axial force coefficient decreases while the normal force coefficient and pitch moment coefficient increase with a maximum difference of 9%. Additionally, the surface heat flux varies differently on each surface region with the surface temperature rising whereas the total heat load decreases, and the maximum discrepancy of heat flux exceeds 10% on the nose, cone body and centerbody bottom.
KW - aerodynamics
KW - aerothermodynamics
KW - computational fluid dynamics
KW - inflatable decelerator
KW - surface temperature
UR - https://www.scopus.com/pages/publications/85032371138
U2 - 10.1109/ICMAE.2017.8038690
DO - 10.1109/ICMAE.2017.8038690
M3 - 会议稿件
AN - SCOPUS:85032371138
T3 - 2017 8th International Conference on Mechanical and Aerospace Engineering, ICMAE 2017
SP - 463
EP - 471
BT - 2017 8th International Conference on Mechanical and Aerospace Engineering, ICMAE 2017
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 8th International Conference on Mechanical and Aerospace Engineering, ICMAE 2017
Y2 - 22 July 2017 through 25 July 2017
ER -