Advanced Nozzle

J OURNAL OF P ROPULSION AND P OWER Vol. 14, No. 5, September – October 1998

Advanced Rocket Nozzles
Gerald Hagemann* DLR, German Aerospace Research Center, Lampoldshausen 74239, Germany Hans Immich† Daimler – Benz AG, Munich 81663, Germany Thong Van Nguyen‡ GenCorp Aerojet, Sacramento, California 95813 and Gennady E. Dumnov§ Keldysh Research Center, Moscow 125438, Russia
Several nozzle concepts that promise a gain in performance over existing conventional nozzles are discussed in this paper. It is shown that signi cant performance gains result from the adaptation of the exhaust ow to the ambient pressure. Special attention is then given to altitude-adaptive nozzle concepts, which have recently received new interest in the space industry. Current research results are presented for dual-bell nozzles and other nozzles with devices for forced ow separation and for plug nozzles with external freestream expansion. In addition, results of former research on nozzles of dual-mode engines such as dual-throat and dual-expander engines and on expansion – de ection nozzles are shown. In general, ow adaptation induces shocks and expansion waves, which result in exit pro les that are quite different from idealized one-dimensional assumptions. Flow phenomena observed in experiments and numerical simulations during different nozzle operations are highlighted, critical design aspects and operation conditions are discussed, and performance characteristics of selected nozzles are presented. The consideration of derived performance characteristics in launcher and trajectory optimization calculations reveal signi cant payload gains at least for some of these advanced nozzle concepts.

Nomenclature
A F h I l m Ç p r ¯ r x, y « amb c cr e geom ref sp t = = = = = = = = = = = = = = = = = = = area thrust ight altitude impulse length mass ow rate pressure mass ratio oxidizer/ fuel mixture radius coordinates nozzle area ratio ambient combustion chamber critical exit plane geometrical

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