International Journal of Aerospace Engineering

Review Article

Approaches to Low Fuel Regression Rate in Hybrid Rocket Engines

Table 1

Values of and to be used in (3) ( in m/s and in kg/m² s).


Legend	System	Propellants			Note	Reference	(kg/m²/s)

	Fuel/additives
B	Pure HTPB	GOX/HTPB		0.681	—	[4]	35–280
W	Paraffin	GOX/Wax		0.690	—	[5]	20–120
WAl	Paraffin/13% Silbal	GOX/fuel		0.766	—	[6]	150–300
C	Cryo	GOX/CH4		0.830	—	[7]	3–30
S1	Pure HTPB	GOX/fuel	—	—	baseline, [8, Figure 11]	[8]	80–150
S12	HTPB/13% Al325	GOX/fuel	—	—	[8, Figure 11]	[8]	80–120
S13	HTPB/13% ALEX	GOX/fuel	—	—	coated, [8, Figure 11]	[8]	70–120
Hb	Pure HTPB	GOX/HTPB		0.530	baseline	[9]	50–400
HAl	HTPB/Al	GOX/fuel		0.930	—	[9]	50–400
HAP	HTPB/AP	GOX/fuel		0.710	—	[9]	50–400
HAPAl	HTPB/Al/AP	GOX/fuel		0.97	—	[9]	50–400

	Swirl/grain geometry
VX	Vortex	GOX/HTPB		0.540	—	[10]	60–110
V	End-burning + Swirl	GOX/PMMA		0.778	—	[11]	40–60
Vb	End-burning + Swirl	GOX/PMMA		0.749	no swirl	[11]	40–60
V	End-burning + Swirl	GOX/PMMA		0.641	—	[11]	10–20
Vb	End-burning + Swirl	GOX/PMMA		0.581	no swirl	[11]	10–20
RU	Radial	GOX/HTPB		0.570	upper disk	[12]	30–70
RL	Radial	GOX/HTPB		0.700	lower disk	[12]	30–70
CA	CAMUI	GOX/PE		0.800	(11),	[13]	200–700