Answer Happy

The mass flow rate of LOX in a hybrid rocket engine is 100 kg/s. For the grain geometry

(internal burning grain), the burn rate is given as 𝑟̇ = 𝑎𝐺𝑜𝑥

𝑛

, where a = 4.34×10-5 m2/kg0.5 and

𝐺𝑜𝑥 = 4𝑚̇ ox/πdp

2

is the mass flux through the port. What should be the value of n such that the

burn rate of the rocket is independent of the diameter of the port? What should be the length of

the fuel grain if the overall ratio of oxidizer mass flow rate to fuel mass flow rate is to be

maintained at 9? The throat diameter of the rocket is 0.2 m, the chamber temperature Tc = 3300

K, γ = 1.2 and molecular weight of the exhaust gases is 26, calculate the chamber pressure. The

density of the fuel grain is 930 kg/m3

. If the thrust coefficient, CF of the nozzle is 2, what is the

thrust produced by the hybrid rocket engine?
The mass flow rate of LOX in a hybrid rocket engine is 100 kg/s. For the grain geometry

(internal burning grain), the burn rate is given as 𝑟̇ = 𝑎𝐺𝑜𝑥

𝑛

, where a = 4.34×10-5 m2/kg0.5 and

𝐺𝑜𝑥 = 4𝑚̇ ox/πdp

2

is the mass flux through the port. What should be the value of n such that the

burn rate of the rocket is independent of the diameter of the port? What should be the length of

the fuel grain if the overall ratio of oxidizer mass flow rate to fuel mass flow rate is to be

maintained at 9? The throat diameter of the rocket is 0.2 m, the chamber temperature Tc = 3300

K, γ = 1.2 and molecular weight of the exhaust gases is 26, calculate the chamber pressure. The

density of the fuel grain is 930 kg/m3

. If the thrust coefficient, CF of the nozzle is 2, what is the

thrust produced by the hybrid rocket engine?