Profiled Lifting Members on Engine Pylons for Drag Reduction

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Aircrafts face challenges in reducing aerodynamic drag during cruising flight, which affects fuel efficiency, and existing designs do not effectively harness oblique air flows to generate propulsive forces while minimizing drag.

Innovation Solution

The integration of profiled lifting members on engine support pylons, oriented obliquely to capture and redirect high-intensity local air flows, generating a propulsive force that counteracts drag, with specific dimensions and placements to optimize lift and minimize inherent drag.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Loss of energy

If a profiled lifting member is added to the engine support pylon to generate propulsive force, then aerodynamic drag is reduced, but device complexity increases

Engineering Contradiction:

Improveaerodynamic dragVSAvoiddevice complexity

Core Design Contradiction:

Loss of energyVSDevice complexity

Solution Approach 1:

The lifting member is integrated onto the existing engine support pylon structure, allowing it to serve dual purposes: maintaining structural support functions while simultaneously generating propulsive force through aerodynamic lift. This multi-functionality approach reduces the need for separate drag reduction devices, thereby limiting the increase in device complexity while achieving drag reduction

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The lifting member utilizes the existing oblique air flows created by the fuselage and wing interaction without requiring additional active control systems or energy input. The structure passively captures and converts the natural oblique flow field into propulsive force, making the system self-sufficient and avoiding complex control mechanisms

Inventive Principle:

Principle #25Self-service

2Force

If the lifting member is positioned closer to the wing unit to maximize lift, then propulsive force increases, but detrimental flow interaction occurs

Engineering Contradiction:

Improvepropulsive forceVSAvoiddetrimental flow interaction

Core Design Contradiction:

ForceVSObject-affected harmful factors

Solution Approach 1:

The lifting member is positioned at a specific location on the pylon (10-70% of the wing chord length from the wing-fuselage junction) where the local flow conditions are optimal. This positioning captures the beneficial oblique flows while avoiding the detrimental interaction zone near the wing leading edge, demonstrating local optimization of the flow-field interaction

Inventive Principle:

Principle #3Local quality

3Force

If the member's wetted area is increased to generate more lifting force, then propulsive force increases, but inherent drag increases

Engineering Contradiction:

Improvelifting forceVSAvoidinherent drag

Core Design Contradiction:

ForceVSLoss of energy

Solution Approach 1:

The design optimizes the wetted area and height dimensions of the lifting member to achieve an area-to-height ratio between 1 and 4. This parameter optimization balances the competing requirements of generating sufficient lifting force while minimizing the inherent drag that increases with larger wetted areas, finding the optimal dimensional compromise

Inventive Principle:

Principle #35Parameter changes

4Force

If the member is disposed vertically (90°) to maximize lift generation, then lifting force is maximized, but the member cannot effectively use oblique flows

Engineering Contradiction:

Improvelifting forceVSAvoidflow utilization

Core Design Contradiction:

ForceVSAdaptability or versatility

Solution Approach 1:

The lifting member is designed with an inclination angle of at least 30° relative to the wing top surface, deviating from the vertical orientation. This angular adjustment makes the member dynamically adapted to the oblique flow conditions in the pylon region, allowing it to effectively capture and utilize the angled air flows while still generating sufficient propulsive lift force

Inventive Principle:

Principle #15Dynamics

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 significantly reduces the overall aerodynamic drag of the aircraft by generating a propulsive force that compensates for local drag forces, while adjusting dimensions and orientations to balance lift and drag, enhancing fuel efficiency and aerodynamic performance.

Implementation Method 1

at least one profiled lifting member is disposed on each of the engine support pylons, in such a way as to generate a propulsive resultant force under the action of an oblique air flow

Methodology Applied

Scientific EffectAerodynamic lift: Aerofoil

Implementation Method 2

local drag forces are generated by the member

Methodology Applied

Scientific EffectAerodynamic drag: Drag

Data Source

PatentUS8167248B2Aircraft comprising a device for reducing the induced drag

Publication Date: 2012.05.01 AIRBUS OPERATIONS (SAS)

AI summary

An aircraft including a longitudinal fuselage, at least two lateral wings connected symmetrically one on each side of the fuselage and at least one engine pod fixed to each lateral wing via an engine support pylon. At least one profiled bearing rod is positioned on each of the engine support pylons so as to generate a propulsive resultant force under action of an oblique air flow.