Submerged Vortex Generator for Aircraft Drag Reduction

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Solution Overview

Problem

Existing vortex generators for improving aerodynamic performance protrude above the aircraft's surface, violating line-of-sight requirements and adding complexity and weight, while passive designs fail to enhance performance effectively.

Innovation Solution

A submerged vortex generator is integrated into the aircraft's aerodynamic surface with a depression and a vortex generator leading edge positioned at or below the tangent line, generating vortices without protruding above the surface, thus meeting line-of-sight requirements and improving aerodynamic performance.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Loss of energy

If traditional vortex generators are used to improve aerodynamic performance, then drag reduction and lift increase are achieved, but the devices protrude above the aircraft surface violating line-of-sight requirements

Engineering Contradiction:

Improveaerodynamic dragVSAvoidsurface profile

Core Design Contradiction:

Loss of energyVSShape

Solution Approach 1:

The vortex generator is nested within a depression formed in the aircraft surface, with the leading edge positioned below the tangent line of the surface. This nesting approach allows the vortex generator to function while remaining concealed within the surface geometry, eliminating the protrusion problem of traditional vortex generators.

Inventive Principle:

Principle #7Nested doll (Nesting)

Solution Approach 2:

The invention transitions from a protruding three-dimensional structure to a submerged configuration by defining the leading edge position relative to the tangent line of the surface. This dimensional repositioning allows the vortex generator to operate effectively while maintaining a sleek surface profile that meets line-of-sight requirements.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

2Shape

If active flow control systems are used to meet line-of-sight requirements, then the aircraft surface profile is maintained, but system complexity and weight increase significantly

Engineering Contradiction:

Improvesurface profileVSAvoidsystem complexity

Core Design Contradiction:

ShapeVSDevice complexity

Solution Approach 1:

The vortex generator operates passively, utilizing the natural airflow over the aircraft surface to generate vortices. No external power source, control systems, or active mechanisms are required. The device self-regulates based on flow conditions, eliminating the complexity and weight associated with active flow control systems while maintaining the required surface profile.

Inventive Principle:

Principle #25Self-service

Solution Approach 2:

The invention replaces complex active mechanical systems (suction devices, actuators, control systems) with a simple passive geometric structure. The vortex generator achieves flow control through its fixed geometric configuration and interaction with natural airflow, eliminating the need for powered mechanical systems.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

3Shape

If active flow control systems are used to maintain surface profile, then line-of-sight requirements are met, but continuous power is required to operate

Engineering Contradiction:

Improvesurface profileVSAvoidpower consumption

Core Design Contradiction:

ShapeVSUse of energy by moving object

Solution Approach 1:

The passive vortex generator requires no external power input. It harnesses the kinetic energy of the passing airflow to generate vortices that energize the boundary layer. This self-powered operation eliminates continuous power consumption while maintaining the required surface profile and providing effective flow control.

Inventive Principle:

Principle #25Self-service

Solution Approach 2:

The invention converts the kinetic energy of the airflow (which would otherwise be lost to drag) into useful vortex structures that energize the boundary layer. By utilizing the natural flow field rather than adding energy through active systems, the device turns the flowing air itself into the actuating mechanism, eliminating power requirements.

Inventive Principle:

Principle #22Blessing in disguise (Convert harm into benefit)

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

The submerged vortex generator reduces aerodynamic drag, increases lift, and delays stall, while maintaining a sleek design that conceals the vortex generator from view, enhancing aircraft performance without adding weight or complexity.

Implementation Method 1

vortex generators are flow control devices that may improve the performance of a vehicle by generating vortices that passively energize low-energy areas of a fluid medium flowing over the vehicle

Methodology Applied

Scientific EffectVortex generation: Vortex Generator

Implementation Method 2

vortex generators may be mounted on an aircraft to energize the boundary layer of local airflow over an aerodynamic surface and thereby reduce or eliminate the tendency of the downstream airflow to separate from the aerodynamic surface

Methodology Applied

Scientific EffectBoundary layer energization: Boundary Layer

Data Source

PatentEP2979974B1Submerged vortex generator

Publication Date: 2018.03.14 THE BOEING CO

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AI summary

A vortex generator (200) includes a depression (202) in an aerodynamic surface (126), and a vortex generator leading edge (300) located in the depression (202). The vortex generator leading edge includes a leading edge upper surface (312). The leading edge upper surface (312) is positioned at or below a tangent line defined at a location along the aerodynamic surface (126) upstream of the depression (202) relative to an oncoming local flow.