In a typical model rocket (Estes Alpha III) the Estes C6 solid rocket engine provides a total impulse of 8.5 N-s. Assume that total rocket mass at launch is 54 g and that it has a rocker engine of mass 20g that burns evenly for 1.5s. The rocket diameter is 24mm. Assume a constant burn rate of the propellant mass (11g), a rocket exhaust speed 800m/s, vertical ascent, and drag coefficient cw = 0.75. Determine
The speed and altitude at engine burnout,
Maximum height and time it occurs,
Maximum acceleration,
Total flight time, and
Speed at ground impact.
Produce a plot of altitude and speed versus time. For simplicity, because the propellant mass is only 20% of the total mass, assume a constant mass during rocket burning.