In contrast with previously known methods of calculating the volume of rocket combustion chambers which are concerned with a ‘characteristic length’ to be determined experimentally for each fuel and for each injection system, it will be shown that there is available: (a) a generally valid qualitative theoretical relationship between the combustion chamber volume VC and any desired combustion pressure, mass flow, fuel and combustion chamber shape. (b) a generally valid relationship, for practical design purposes, between the combustion chamber volume VC and any desired combustion pressure, mass flow, fuel and combustion chamber shape. Further, the theoretical results will be compared, by means of examples, with combustion chambers which have been tested in practice. Moreover, the important fact will be indicated that the formula proposed in this article must, in principle, also be applicable to the calculation of the volume of the gas turbine combustion chamber.
Himpan, I.J. and Paris (1950), "The Calculation of the Volume of Rocket Combustion Chambers: Formulae Giving Generally Valid Theoretical and Practical Relationships Between Volume and Other Characteristics", Aircraft Engineering and Aerospace Technology, Vol. 22 No. 7, pp. 191-193. https://doi.org/10.1108/eb031919
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