Forward Swept Wing Boundary Layer Ingestion Propulsion
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Solution Overview
Problem
Conventional aircraft designs have not significantly evolved to improve aerodynamic performance and reduce fuel consumption, particularly in terms of high and low-speed performance and range.
Innovation Solution
The design incorporates forward-swept wings, a distributed electrical propulsion system with air intakes located rearward of the wing-fuselage intersection to ingest boundary layer air, and a combination of combustion engines and generators for electrical power, optimizing air flow and reducing drag.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional aircraft design is maintained, then structural simplicity is preserved, but aerodynamic performance and fuel consumption remain suboptimal
Solution Approach 1:
The propulsion system is divided into multiple distributed electric fans along the wingspan rather than using a single conventional engine, allowing independent optimization of each fan's position and size to improve overall aerodynamic efficiency while managing complexity through modular design
Solution Approach 2:
The wing structure serves multiple functions: it provides structural support, generates lift, and houses the distributed electric propulsion system within the wing body, eliminating the need for separate engine nacelles and reducing overall system complexity
2Speed
If rearward-swept wings are used, then structural stability is improved, but low-speed performance and boundary layer control deteriorate
Solution Approach 1:
The patent uses forward-swept wings instead of the conventional rearward-swept configuration, inverting the traditional design approach to achieve superior low-speed performance and enhanced boundary layer control while the distributed propulsion system compensates for any structural stability concerns
3Loss of energy
If boundary layer ingestion is implemented, then drag reduction is achieved, but air intake positioning becomes more complex
Solution Approach 1:
The air intake system is merged with the wing structure itself, using the wing body to guide and channel the boundary layer flow directly to the electric fans, eliminating the need for separate complex intake ducting and simplifying the overall system while maximizing drag reduction
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This configuration enhances aerodynamic performance, reduces fuel consumption, and improves both high-speed and low-speed characteristics by increasing air mass flow and reducing drag, resulting in more efficient propulsion and improved wing loading.
Implementation Method 1
an air intake located rearward of an intersection between the forward swept wings and the fuselage and open to a boundary layer region on a surface of the fuselage
Data Source
AI summary
An aircraft including a fuselage extending along a longitudinal axis; forward swept wings extending from the fuselage; at least one horizontal stabilizer secured to the fuselage; and a distributed electrical propulsion system operatively connected to an electrical power source. The distributed electrical propulsion system have an air intake located rearward of an intersection between the forward swept wings and the fuselage open to a boundary layer region on a surface of the fuselage.