Abstract
straight-through flow combustion chamber, can be extended, with some reservations, to include the process occurring in a ramjet combustion chamber. The presence of a set of stabilizers used in a real combustion chamber, stabilizers operating under identical conditions, does not prevent us from considering one of the elements, with a single stabilizer, as a simple straight-through combustion chamber. The most suitable scheme will indeed involve just such a flat element, for if the chamber has a row of concentric stabilizers, the ratio of the cross section of one chamber element to the length of the stabilizer periphery is quite small, and the curvature of the stabilizer can be neglected. The conclusions remain valid also in the case of a combustion process distributed in depth, although the calculation becomes more complicated in this case.
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