An Investigation of the Aerodynamics and Cooling of a Horizontally-Opposed Engine Installation

Miley, S. J.; Cross, E. J.; Owens, John

doi:10.4271/770467

Cited by 6 publications

(2 citation statements)

References 2 publications

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“…The C D values shown in Fig. 8 and throughout the paper have been corrected for shaft thrust by adding the measured shaft thrust T to the measured scale data D scalc for the wing propeller combination (2) Therefore the C D values reflect the influence of the propeller slip-stream on the wing nacelle, but do not include the shaft thrust. To interpret these results, a schematic flowfield around the wing nacelle is drawn in Fig.…”

Section: Variation Of Inlet Areamentioning

confidence: 99%

Effect of Propeller on Engine Cooling System Drag and Performance

Katz

Corsiglia

Barlow

1982

Journal of Aircraft

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Section: Variation Of Inlet Areamentioning

confidence: 99%

Effect of Propeller on Engine Cooling System Drag and Performance

Katz

Corsiglia

Barlow

1982

Journal of Aircraft

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“…A high oil temperature may result in an increase in either the oil consumption rate or the amount of oil mist passing through the engine oil breather [2]. The standard cure for inadequate cooling is to operate the engine at much higher fuel flows resulting in reduced fuel efficiency [3]. A workaround is to provide a jet-pump (or ejector) inside the oil cooler duct, operated by compressor bleed air.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Engine Oil-cooling Problem during Idle Conditions on Pusher Type Turbo Prop Aircraft

Premkumar

Chakravarthy

Subramanian

et al. 2016

International Journal of Turbo &Amp; Jet-Engines

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Aircraft engines need a cooling system to keep the engine oil well within the temperature limits for continuous operation. The aircraft selected for this study is a typical pusher type Light Transport Aircraft (LTA) having twin turbo prop engines mounted at the aft end of the fuselage. Due to the pusher propeller configuration, effective oil cooling is a critical issue, especially during lowspeed ground operations like engine idling and also in taxiing and initial climb. However, the possibility of utilizing the inflow induced by the propeller for oil cooling is the subject matter of investigation in this work. The oil cooler duct was designed to accommodate the required mass flow, estimated using the oil cooler performance graph. A series of experiments were carried out with and without oil cooler duct attached to the nacelle, in order to investigate the mass flow induced by the propeller and its adequacy to cool the engine oil. Experimental results show that the oil cooler positioned at roughly 25 % of the propeller radius from the nacelle center line leads to adequate cooling, without incorporating additional means. Furthermore, it is suggested to install a NACA scoop to minimize spillage drag by increasing pressure recovery.

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