Abstract
In a solid propellant rocket of a side burning type, the flow rate of the hot combustion gases parallel to the burning surface is approximately proportional to the distance from the leading edge of the propellant. In the present paper, therefore, the erosive burning of the solid propellant is analyzed by the boundary-layer approximation in aerothermochemistry for the case where the velocity, u∞, of the hot combustion gas stream outside the boundary layer increases linearly with the distance, x, from the leading edge of the propellant, i.e., u∞ = Gx, and the effects of the hot gas stream on the burning rate of the propellant are examined.
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