Aerodynamic Interference for Aero-Engine Installations

Stańkowski, Tomasz; MacManus, David G.; Sheaf, Christopher; Grech, Nicholas

doi:10.2514/6.2016-0766

Cited by 7 publications

(5 citation statements)

References 13 publications

(22 reference statements)

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“…A lift coecient of 0.5 was selected as this is the nominal design condition of the CRM airframe [32]. Moreover, a range of engine positions under the CRM wing were investigated with the relative position of the fan cowl trailing edge to the wing leading edge the dening parameter [14,29,30].…”

Section: Airframe and Installation Positionsmentioning

confidence: 99%

Installation aerodynamics of civil aero-engine exhaust systems

Otter

Stańkowski

Robinson

et al. 2019

Aerospace Science and Technology

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Without careful consideration of aerodynamic installation eects on exhaust system performance the projected benets of high bypass ratio engines may not be achievable. This work presents a computational study of propulsion system integration in order to quantify the eect that aircraft installation has on the aerodynamic performance of separate-jet aero-engine exhaust systems. Within this study the sensitivity of exhaust nozzle performance metrics to aircraft incidence and under wing position were investigated for two engines of dierent specic thrust. Upon installation, thrust generation was found to be benecial or detrimental relative to an isolated engine depending on the position of the engine relative to the wing leading edge. The dominant installation eect was observed on the exhaust afterbodies and, over the range of engine positions investigated at cruise conditions, the installed modied velocity coecient was shown to vary up to 1 % relative to an isolated engine. Furthermore, due to variations in the core nozzle mass ow rate by

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Section: Airframe and Installation Positionsmentioning

confidence: 99%

Installation aerodynamics of civil aero-engine exhaust systems

Otter

Stańkowski

Robinson

et al. 2019

Aerospace Science and Technology

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“…The engine wrapped in the nacelle is attached to the airframe wing using a pylon. The location of the engine with reference to the airframe is fixed based on an engine installation aerodynamics study to minimize the installation drag [25]. The ground clearance after the engine is installed in the airframe is 0.6 m. The pylon construction is based on symmetric NACA profiles, the chord length and thickness of which are determined from relative engine location and structural integrity requirements.…”

Section: Nacelle and Pylonmentioning

confidence: 99%

Fan Flow Field in an Installed Variable Pitch Fan Operating in Reverse Thrust for a Range of Aircraft Landing Speeds

Rajendran

Pachidis

2019

Journal of Engineering for Gas Turbines and Power

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The installed flow field for a variable pitch fan (VPF) operating in reverse thrust for the complete aircraft landing run is described in this paper. To do this, a VPF design to generate reverse thrust by reversing airflow direction is developed for a representative 40,000 lbf modern high bypass ratio engine. Thereafter, to represent the actual flow conditions that the VPF would face, an engine model that includes the nacelle, core inlet splitter, outlet guide vanes, bypass nozzle, core exhaust duct, aft-body plug, and core nozzle is designed. The engine model with the VPF is attached to a representative airframe in landing configuration to include the effects of installation. A rolling ground plane that mimics the runway during the landing run is also included to complete the model definition. Three-dimensional (3D) Reynolds-averaged Navier–Stokes (RANS) solutions are carried out for two different VPF stagger angle settings and rotational speeds to obtain the fan flow field. The dynamic installed VPF flow field is characterized by the interaction of the freestream and the reverse stream flows. The two streams meet in a shear layer in the fan passages and get deflected radially outward before turning back onto themselves. The flow field changes with stagger setting, fan rotational speed, and the aircraft landing speed because of the consequent changes in the momentum of the two streams. The description of the installed VPF flow field as generated in this study is necessary to (a) qualify VPF designs that are typically designed by considering only the uninstalled static flow field and (b) choose the VPF operating setting for different stages of the aircraft landing run.

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“…Sibilli et al 16 and Oliveira et al 12 performed similar studies and confirmed this finding. Stankowski 17,18 investigated the effect of powered nacelle position on the aerodynamic interference. They indicated that the best position was located closest to the wing horizontally and lowest from the wing vertically.…”

Section: Introductionmentioning

confidence: 99%

Numerical study on interference effects of the nacelle position on aerodynamic characteristics and nacelle intake performances

Cao,

Qin,

Wang

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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Insight into the interference effects of the nacelle position can be used to provide some guidance for achieving better aircraft performance in the preliminary design of modern civil aircraft. This paper investigates the through-flow nacelle position effects on aircraft aerodynamic characteristics and nacelle intake performances through numerical simulation. The Common Research Model with different nacelle-pylon installation positions is analyzed and all the five nacelle installation parameters, including spanwise position, penetration, gully depth, pitch angle, and toe angle, are systematically studied. Qualitative and quantitative comparisons between different configurations are conducted and the sensitivity of drag, lift distribution, total pressure recovery, and airflow distortion to nacelle position is obtained. The mechanism of interference effects is also explored. These derived insights can provide some guidance for determining the nacelle position and reduce the cost of subsequent wind tunnel test.

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Aerodynamic Interference for Aero-Engine Installations

Cited by 7 publications

References 13 publications

Installation aerodynamics of civil aero-engine exhaust systems

Installation aerodynamics of civil aero-engine exhaust systems

Fan Flow Field in an Installed Variable Pitch Fan Operating in Reverse Thrust for a Range of Aircraft Landing Speeds

Numerical study on interference effects of the nacelle position on aerodynamic characteristics and nacelle intake performances

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