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For a given model rocket engine and aerodynamic characteristics,
this HP Prime program determines the optimal launch mass of a single-stage
model rocket which maximizes total altitude (Bengen's maxima).

The data required for this program is provided by the user using the following
example of "hard-wired" information. Please note the proper units of each input.

// launch site altitude (meters)

altsite := 100.0;

// launch site temperature (degrees f)

tempsite := 70.0;

// thrust duration (seconds)

tduration := 1.2;

// total impulse (newton-seconds)

impulse := 5.0;

// propellant mass (grams)

mprop := 8.33;

// reference diameter (millimeters)

fdia := 18.0;

// drag coefficient (non-dimensional)

cd := 0.321;