(b) The following parameters characterise a liquid-fuelled rocket engine: stagnation pressure P0=100bar; stagnation temperature T0=3300K; nozzle exit diameter DE=1.0m; throat diameter =0.1m; gas constant R=692Jkg1K1; ratio of specific heats cp/cV==1.25. Using the isentropic tables provided or otherwise, estimate the following: static pressure at the exit plane, exit Mach number, mass flow rate, and gross thrust at vacuum conditions. (b) The following parameters characterise a liquid-fuelled rocket engine: stagnation pressure P0=100bar; stagnation temperature T0=3300K; nozzle exit diameter DE=1.0m; throat diameter =0.1m; gas constant R=692Jkg1K1; ratio of specific heats cp/cV==1.25. Using the isentropic tables provided or otherwise, estimate the following: static pressure at the exit plane, exit Mach number, mass flow rate, and gross thrust at vacuum conditions