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Aerodynamic Testing of Helicopter Side Intake Retrofit Modifications

Chair of Aerodynamics and Fluid Mechanics, Department of Mechanical Engineering, Technical University of Munich, 85748 Garching bei München, Germany
Author to whom correspondence should be addressed.
Aerospace 2017, 4(3), 33;
Received: 5 May 2017 / Revised: 12 June 2017 / Accepted: 19 June 2017 / Published: 23 June 2017
(This article belongs to the Special Issue Propulsion/Airframe Integration)
Aerodynamic characteristics of helicopter engine side air intakes are investigated. The experimental data set is obtained by wind tunnel testing of a full-scale helicopter fuselage section model. For the simulation of realistic engine operation, engine mass flow rates are reproduced. Five-hole pressure probe data of the aerodynamic interface plane as well as local surface pressure distributions are compared for different geometries and operation conditions. Previous investigations indicate that unshielded, sideways-facing air intakes yield lowest distortion and highest total pressure levels in low speed conditions. In fast forward flight condition, however, forward-facing intake shapes are more beneficial. On this basis, the current research assesses the optimization potential of retrofit modifications such as a rear spoiler (small scoop) and an intake guide vane. Two optimal configurations of retrofit modifications are identified, combining benefits of the various basic intake and plenum chamber shapes. View Full-Text
Keywords: experimental aerodynamics; helicopters; air intakes experimental aerodynamics; helicopters; air intakes
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MDPI and ACS Style

Knoth, F.; Breitsamter, C. Aerodynamic Testing of Helicopter Side Intake Retrofit Modifications. Aerospace 2017, 4, 33.

AMA Style

Knoth F, Breitsamter C. Aerodynamic Testing of Helicopter Side Intake Retrofit Modifications. Aerospace. 2017; 4(3):33.

Chicago/Turabian Style

Knoth, Florian, and Christian Breitsamter. 2017. "Aerodynamic Testing of Helicopter Side Intake Retrofit Modifications" Aerospace 4, no. 3: 33.

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