Initial performance evaluation of 2DCD ejector exhaust systems

Brooke, D.; Dusa, D.; Kuchar, A. P.; Romine, B.

doi:10.2514/6.1986-1615

Cited by 2 publications

(3 citation statements)

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“…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%

“…One option for a further improvement of thrust behaviour in the critical transonic flight regime is the additional use of secondary ejector air flow, as suggested in (6,(10)(11)(12)(13)(14). Thick boundary layer air developing at the aircraft forebody must be absorbed at the air intakes before entering the engine operated in turbo-mode.…”

Section: Sern Ejector Nozzlementioning

confidence: 99%

“…A constant secondary -to-primary pressure ratio of PTs/PTp = 0.2 is assumed for these flight points. The axial thrust coefficient CFGx in this paper is related to the ideal thrust of the primary flow as in (13,14) and may yield CFGx values greater than 1.0. The corrected mass flow ratios w [Tare included in Fig.…”

Section: Effects Of Secondary Ejector Air Flowmentioning

confidence: 99%

See 2 more Smart Citations

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%