Performance evaluation of a two dimensional convergent-divergent ejector exhaust system

Federspiel, John; Kuchar, A. P.

doi:10.2514/6.1988-2999

Cited by 4 publications

(2 citation statements)

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“…Furthermore, the nozzle throat area must be variable due to the operation mode of the combined cycle engine. These conditions necessitate an adequate adjustment of nozzle throat and exit areas (6)(7)(8)(9)(10).…”

Section: Fig 3 Nozzle Throat Area Requirementsmentioning

confidence: 99%

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Optimization Aspects of an Ejector Type Hypersonic Thrust Nozzle

Trittler

Eckert

Going

1992

Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery

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Hypersonic aircraft projects are highly dependant on efficient propulsion systems. High performance and integration within the airframe play a vital role in the overall concept. Particular attention must be paid to the exhaust system that is submitted to a wide range of operational requirements. An optimization of the nozzle geometry for high flight Mach numbers will lead to a low performance at the transonic flight regime. The additional use of secondary ejector air flow at transonic speeds is one option to improve the thrust behaviour of the nozzle. In the presented paper performance data of single expansion ramp ejector type nozzles are predicted using a calculation model based on a method-of-characteristics algorithm. For optimization purposes the effects of various design parameters on axial thrust coefficient and thrust vector angle are discussed. The geometric parameters investigated are the length of the lower nozzle wall and its deflection angle as well as the ejector slot location and its cross-section.

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Section: Fig 3 Nozzle Throat Area Requirementsmentioning

confidence: 99%

“…The amended use of a secondary ejector airflow proves to be a suitable way to accomplish this target, (9)(10)(11)(12)(13)(14). In the paper the effects of secondary airflow ejection on the SERN nozzle performance are presented with respect to thrust coefficient and thrust vector angle.…”

Section: Fig 3 Nozzle Throat Area Requirementsmentioning

confidence: 99%