A chemical rocket is being designed to operate at sea level with Hydrazine (N_2H

Question

A chemical rocket is being designed to operate at sea level with Hydrazine (N_2H_4) and Hydrogen Peroxide (H_2O_2) as fuel and oxidizer (see page 119 in our textbook). The chamber pressure will be 4.5 MPa. Assume that the propellants are stored at 25 degree C. Combustion products can initially be assumed to be water vapor and molecular nitrogen only. What would the mass ratio of fuel and oxidizer be for a stoichiometric mixture? Now relying on CEA to calculate proper chemistry: Calculate the combustion temperature. State the optimum nozzle expansion ratio (exit area/throat area) at sea level. Give values for the characteristic velocity (C*) and thrust coefficient (CF). Show the actual gas mixture at the nozzle throat and compare to the ideal case (complete combustion). If the same rocket is now operating at 80,000 feet above sea level, what thrust penalty occurs due to the mismatched nozzle? (i.e. compare the baseline to a resized/optimized nozzle).

Explanation / Answer

we have N2H4 as fuel and H2O2 as oxydiser.we have H2O and N2 as our final product of reaction.our reaction is

N2H4+2H2O2----->4H2O+N2 mass of fuel(N2H4)=32amu

mass of oxydiser(H2O2)=34amu

hence our stoichimetric ratio would be , mass of fuel(N2H4) / 2*(mass of oxydiser[H2O2]

= 32 / 2*(34)

=32 / 68 = 0.470

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