Special Problem $05$HW$-$A SPC$-$Lance Missile

Lance Missile Boos Thruster

IRFNA $($Oxidizer$)$ Propellant available $=375$ lbm

UDMH $($Fuel$)$ available $=1106$ lbm

OF ratio of Booster Engine I s$3\mathrm{.}4$

And a Chamber Pressure of $1,200$ psi.

Chamber Pressure $=950$ psi

Throat Outer Diameter $=14\mathrm{.}98in.$

Throat Inner Diameter $=8\mathrm{.}13$ inches

Nozzle Exit Outer Diameter $=14\mathrm{.}98in.$

Nozzle exit Inner diameter $=4\mathrm{.}536$ in$.$

Find:

Using any resource available

a$)$ Specific Impulse $($s$)$

b$)$ Characteristic Velocity $($ft$/$s$)$

c$)$ Area of throat $(i{n}^2)$

d$)$ Nozzle area ratio

e$)$ Total mass flow rate $(Ib\frac{m}{s}$

f$)$ Thrust $((b_f)$