Abstract
Hybrid laminar flow control or HLFC design is a complex and multi-disciplinary process, which demands a thorough understanding of all aspects from a global systems viewpoint. The objective of the paper is to present a preliminary design of important components of an HLFC system that helps in quick assessment of conceptual system architectures. This is important to evaluate feasibility, system performance, and overall aircraft benefits at early stages of system development. This paper also discusses the various important system requirements and issues concerning the design of active HLFC systems, and the interfaces between various disciplines are presented. It can be emphasized from the study that the future compressor design for the HLFC system should consider the thermal management aspects and additional mass flow requirements from the aerodynamics-structure design optimization and also from water drain system solutions. A method to calculate the accumulated water content inside the plenum chambers is presented, and the effect of a drain hole on the power consumption is studied. A low order thermal management study of the HLFC compressor motor shows a high temperature rise in the windings for very high speed motors for long duration operation and calls for effective cooling solutions.
Highlights
The aviation industry contributes a lot to carbon dioxide (CO2 ) emissions and the research trend in the 21st century is towards environmentally sustainable aviation
The objective of the paper is to present a preliminary design of important components of an hybrid laminar flow control (HLFC) system that helps in quick assessment of conceptual system architectures
This paper presented a generalized approach for the preliminary design of an HLFC system intended for conceptual studies
Summary
The aviation industry contributes a lot to carbon dioxide (CO2 ) emissions and the research trend in the 21st century is towards environmentally sustainable aviation. Drag reduction can be achieved by keeping the flow in the boundary layer over the aircraft surfaces (wing, horizontal tail plane (HTP), vertical tail plane (VTP), engine nacelles, and fuselage) laminar, rather than the usual turbulent boundary layer flow [1]. For conventionally swept wings of high-speed aircraft, the transition point can be delayed by removing air through boundary layer suction to damp aerodynamic instability mechanisms such as Tollmien–Schlichting instability and crossflow instability [1]. The LFC technique, in which the Aerospace 2019, 6, 109; doi:10.3390/aerospace6100109 www.mdpi.com/journal/aerospace
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