Aerodynamic performance of a bypass engine with fan nozzle exit area change by warped chevrons

Sloan, B.; Wang, J.; Spence, Stephen; Raghunathan, Srinivasan; Riordan, David

doi:10.1243/09544100jaero529

Cited by 7 publications

(8 citation statements)

References 16 publications

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“…Subsequently, there have been numerous investigations within the literature on the use of RANS CFD for the calculation of aerodynamic performance metrics for civil separate-jet nozzles [13,14,15,16]. Moreover, due to the high temperatures present in the core jet [13], research has been undertaken in order to assess the limitations of RANS CFD for predicting heated nozzle flows [17,18].…”

Section: Computational Methods For the Calculation Of Exhaust System Flowsmentioning

confidence: 99%

“…The gauge stream forces for the fan and core streams were evaluated from CFD computations through the integration of the momentum and pressure terms at the inlets of the respective duct, Eq. (14). Where is the fluid density, is the axial velocity and is the elemental surface area of the inlet boundary.…”

Section: The Experimental Nozzle Coefficients Reported By Mikkelsen Et Al Were Calculated Based On An Assumed Constantmentioning

confidence: 99%

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Aerodynamic Analysis of Civil Aeroengine Exhaust Systems Using Computational Fluid Dynamics

Otter

Goulos

MacManus

et al. 2018

Journal of Propulsion and Power

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As the specific thrust of civil aero-engines reduces, the aerodynamic performance of the exhaust system will become of paramount importance in the drive to reduce engine fuel burn. This paper presents an aerodynamic analysis of civil aero-engine exhaust systems through the use of Reynolds Averaged Navier-Stokes Computational Fluid Dynamics . Two different numerical approaches were implemented and the numerical predictions were compared to measured data from an experimental high-bypass ratio separate-jet exhaust system. Over a fan nozzle pressure ratio range from 1.4 to 2.6, a comparison was drawn between values of thrust coefficient calculated numerically and values obtained from experimental measurements. In addition to the validation of numerical approaches, the effects of freestream Mach number and extraction ratio on the aerodynamic behavior of the exhaust system have been quantified and correlated to fundamental aerodynamic parameters.

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Section: Computational Methods For the Calculation Of Exhaust System Flowsmentioning

confidence: 99%

Section: The Experimental Nozzle Coefficients Reported By Mikkelsen Et Al Were Calculated Based On An Assumed Constantmentioning

confidence: 99%

Aerodynamic Analysis of Civil Aeroengine Exhaust Systems Using Computational Fluid Dynamics

Otter

Goulos

MacManus

et al. 2018

Journal of Propulsion and Power

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“…The advent of Computational Fluid Dynamics (CFD) during the past two decades has rendered it a reliable and useful performance prediction tool for the aerodynamic analysis of exhaust nozzles [11,[15][16][17][18][19][20]. The associated flow phenomena observed in the vicinity of a gas-turbine engine exhaust system can be quite complex.…”

Section: Accepted Manuscript N O T C O P Y E D I T E Dmentioning

confidence: 99%

Aerodynamic Design of Separate-Jet Exhausts for Future Civil Aero-engines—Part I: Parametric Geometry Definition and Computational Fluid Dynamics Approach

Goulos

Stańkowski

Otter

et al. 2016

Journal of Engineering for Gas Turbines and Power

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This paper presents the development of an integrated approach which targets the aerodynamic design of separate-jet exhaust systems for future gas-turbine aero-engines. The proposed framework comprises a series of fundamental modeling theories which are applicable to engine performance simulation, parametric geometry definition, viscous/compressible flow solution, and design space exploration (DSE). A mathematical method has been developed based on class-shape transformation (CST) functions for the geometric design of axisymmetric engines with separate-jet exhausts. Design is carried out based on a set of standard nozzle design parameters along with the flow capacities established from zero-dimensional (0D) cycle analysis. The developed approach has been coupled with an automatic mesh generation and a Reynolds averaged Navier–Stokes (RANS) flow-field solution method, thus forming a complete aerodynamic design tool for separate-jet exhaust systems. The employed aerodynamic method has initially been validated against experimental measurements conducted on a small-scale turbine powered simulator (TPS) nacelle. The developed tool has been subsequently coupled with a comprehensive DSE method based on Latin-hypercube sampling. The overall framework has been deployed to investigate the design space of two civil aero-engines with separate-jet exhausts, representative of current and future architectures, respectively. The inter-relationship between the exhaust systems' thrust and discharge coefficients has been thoroughly quantified. The dominant design variables that affect the aerodynamic performance of both investigated exhaust systems have been determined. A comparative evaluation has been carried out between the optimum exhaust design subdomains established for each engine. The proposed method enables the aerodynamic design of separate-jet exhaust systems for a designated engine cycle, using only a limited set of intuitive design variables. Furthermore, it enables the quantification and correlation of the aerodynamic behavior of separate-jet exhaust systems for designated civil aero-engine architectures. Therefore, it constitutes an enabling technology toward the identification of the fundamental aerodynamic mechanisms that govern the exhaust system performance for a user-specified engine cycle.

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“…Many aircraft studies took place in 1973 when Boeing introduced computational fluid dynamic (CFD) as one of the aircraft research tools. Nowadays, many researchers have used CFD in aircraft studies to reduce the experimental cost as reported by Ismail and Wang [1], Sloan et al, [2] and Ives et al, [3] and Loutun et al, [4]. Ismail and Wang [1] employed CFD to study swirl flow of hot air for nacelle lip-skin application.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study of Rigid and Flexible Tandem Wing for Micro Aerial Vehicle

Mohamed

Ismail

Ramli

et al. 2021

ARFMTS

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Unmanned aerial vehicle is becoming increasingly popular each year. Now, aeronautical researchers are focusing on size minimization of unmanned aerial vehicle, especially drone and micro aerial vehicle. The lift coefficient of micro aerial vehicle has wing dimension of 12 cm and mass of less than 7 g. In the present study, with the aid of 3D printer, polylactic acid material was used to develop the micro aerial vehicle structure for tandem wing arrangement. The materials for rigid wing skin and flexible wing skin were laminating film and latex membrane, respectively. The present work elaborates the lift coefficient profiles on rigid wing skin and flexible wing skin at wing flapping frequency of 11 Hz, three different Reynolds numbers of 14000, 19000 and 24000, and five different angles of attacks between 0° and 50°. According to the results obtained, the lift coefficient decreased as the Reynolds number increased. The lift coefficient increased up to 9 as the angle of attack increased from 0° to 50° at the Reynolds number of 14000 for flexible wing skin. The results also showed that the lift coefficient of flexible wing skin was higher than that of rigid wing skin at the attack angle of10° and below, except for the Reynolds number of 14000.

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Aerodynamic performance of a bypass engine with fan nozzle exit area change by warped chevrons

Cited by 7 publications

References 16 publications

Aerodynamic Analysis of Civil Aeroengine Exhaust Systems Using Computational Fluid Dynamics

Aerodynamic Analysis of Civil Aeroengine Exhaust Systems Using Computational Fluid Dynamics

Aerodynamic Design of Separate-Jet Exhausts for Future Civil Aero-engines—Part I: Parametric Geometry Definition and Computational Fluid Dynamics Approach

Experimental Study of Rigid and Flexible Tandem Wing for Micro Aerial Vehicle

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