Arocket engine uses a h2-o2 mixture as a propellant. the mean molar mass of the propellant is 11.58 kg/kmol with ratio of specific heats g = 1.22. the stagnation pressure at the throat of the nozzle is 8.26 mpa and the static temperature at the throat is 3305 k. the throat area at = 750.4 cm2 . the ratio of the exit plane area to the throat area is 39.8 and the static pressure at the exit plane of the nozzle is 18.1 kpa. (a) calculate the mass flow rate of propellant throug

Which statement explains which component is likely to be more powerful in explaining a scientific phenomenon? a) component c, because a theory is often passed on possibility and not certainty b) component d, because a hypothesis is often based on possibility not certainty c) component c, because the ability to explain several occurrences in the natural world is a characteristic of a hypothesis d) component d, because the ability to explain several occurrences in the natural world is a characteristic of a theory