Path: StraightLine/StraightLine
% Payload fraction demo for a variety of reference missions Find the mass-optimal exhaust velocity for a Jupiter mission given other engine parameters. Our nominal engine has a specific power of 1000 W/kg, a thrust efficiency of 0.4, and a tank structural fraction of 0.05. Our exhaust velocity is in the neighborhood of 100 to 150 km/s. Changing the specific power or efficiency will have a large effect on the payload fraction. See also: ComputePayloadFraction, OptimalExhaustVelocity, Straight2DStructure