Measurements have been made of the lift, pitching moment and center of pressure of delta wing-body combinations at supersonic Mack number 1.88. Conical nose bodies, with cylindrlcal body lengths of 75mm and 150mm, and with delta wing aspect ratios varying systematically from 0.67 to 3.33, were investigated. The purpose of this study was to describe in a systematic manner the variation of the wing-body combination aerodynamic characteristics with aspect ratio and body length. These data are in reasonable agreement with the theoretical values predicted by G.K. Morikawa, F.H. Tsien and T. Nonweiler.

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This paper presents the method of simplification of strain energy formula by using the fundamental equations and restrained conditions, both of which are derived by variational calculus of strain energy formula. By this method, total strain energy can easily be calculated and arbitrary constant contained in solution is determined without troublesome work.

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In order to obtain a perfect nozzle, which provides maximum thrust with a given expansion ratio, a new concept of nozzle design is presented.
Primary efflux from a convergent nozzle into the secondary flow atmosphere, and pressure distribution in the axial direction of the secondary flow, is arranged to give the primary flow the ideal wall pressure distribution of a perfect nozzle.
The secondary flow presents a cushioning action to the primary flow to prevent irregular expansion or shock waves, and provides a lubricating effect to reduce wall friction.
The secondary nozzle wall shape and the optimum secondary pressure are computed.
A similar idea has been utilized in the tail nozzle of the F-104 fighter in the form of a double convergent nozzle.
Experiments were conducted to investigate the flow by means of Schlieren pictures, and to measure the thrust of a model nozzle.

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