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Very hard to answer directly. That spacecraft could be reusable has many origins from Tsilokowski to Goddard, the Amerika Bomber to the DynaSoar. One can argue that the lifting body shapes of the X-planes were test articles for the later NASA program.

Most important is that under current propellants, at least 70% of the mass needed to achieve escape velocity is fuel. Second to that is re-usability and a big part of that is the velocity at reentry due to heating. Ballistic trajectories are high in thermodynamic values and different shapes, while more shallow angles allow for lower heating and more aerodynamic designs. Case in point, the Apollo heat shields were one off, hand injected phenolic while what became the space shuttle orbiter shields were silicon tiles for a lower temperature. This also meant that the orbiter would never reach beyond lower Earth orbits.

Several approaches were applied such as single stage to orbit (above mass ratio problem), a reusable booster stage that was recovered by flying back or as in reality solid rocket boosters recovered at sea, and the orbiter flying back to a runway. The cargo bay dimensions were laid down as the size of a railroad box literally. That required the size to be equivalent to a DC-8. Budget cuts under Nixon, Ford and Carter drove the rest.

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