Analysis of the liquid-metal turbojet cycle for propulsion of nuclear powered aircraft

Wachtl, William. W., Rom, Frank E.
naca-rm-e51d30
1951


An analysis of the nuclear powered liquid-metal turbojet cycle is presented for a wide range of engine operating conditions at flight Mach numbers of 0.9 and 1.5, and at altitudes of 30,000 and 50,000. Airplane gross weight and reactor heat release is presented for typical values of airplane lift-drag ratio, structure to gross weight ratio, and sum of reactor, shield, payload, and auxiliary weights. The effect of varying these assumptions and of including nacelle drag is shown along with the effect of flight conditions.

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