Investigation of Dual-Vortical-Flow Hybrid Rocket Engine without Flame Holding Mechanism

Table 2

Boundary settings for numerical analysis.

Boundaries		Flow condition	Thermal condition
Fuel	—	Flow rate (pyrolysis), normal to the wall	T > Tpyrolysis (820 K)
	—	No slip	T < Tpyrolysis
Inlet	—	Fixed total pressure (40 atm)	300 K
Outlet	—	Supersonic-free expansion	N/A
Wall	—	No slip	Adiabatic