Aircraft Vortex Generators for Fuselage Stability
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Solution Overview
Problem
Aircraft with upswept aft fuselages and sponsons experience deteriorated directional stability and increased aerodynamic drag due to complex vortex systems created by main and sponson vortices, which are not effectively addressed by existing solutions.
Innovation Solution
The arrangement of laterally offset aerodynamic auxiliary surfaces on the underside of the aircraft generates vortices that positively influence main vortices and sponson vortices, improving directional stability and reducing aerodynamic drag by deflecting air flow and compensating for vortex interference.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If the aircraft comprises an upswept aft fuselage with sponsons for cargo access, then the cargo compartment accessibility is improved, but the directional stability deteriorates due to complex vortex systems
Solution Approach 1:
The patent applies vortex generators that generate controlled vortices to counteract the harmful sponson vortices. By intentionally creating smaller, controlled vortices on the fuselage underside, the patent converts the harmful vortex effect into a beneficial stabilizing mechanism that cancels out the destabilizing sponson vortex influence.
Solution Approach 2:
The patent modifies the vortex characteristics by changing parameters such as vortex strength, position, and orientation. The vortex generators are positioned and angled to create vortices with specific parameters that counterbalance the sponson vortex effects, transforming the overall vortex system from unstable to stable.
2Ease of operation
If the aircraft comprises an upswept aft fuselage with sponsons, then the cargo compartment accessibility is improved, but the aerodynamic drag increases due to complex vortex systems
Solution Approach 1:
The patent converts the harmful energy loss from sponson vortices into beneficial effects by using vortex generators to create counter-vortices. These controlled vortices cancel out the turbulent, energy-wasting sponson vortices, reducing overall aerodynamic drag while preserving the cargo access functionality.
Solution Approach 2:
The patent optimizes aerodynamic performance by adjusting vortex generation parameters including the angle, position, and strength of the vortex generators. These parameter changes result in a more efficient vortex system that reduces energy loss from turbulent flow and decreases aerodynamic drag.
3Loss of energy
If vortex generators are arranged on the underside of the upswept aft fuselage, then the aerodynamic drag is reduced, but the directional stability improvement is limited
Solution Approach 1:
The patent employs asymmetric positioning and angling of the vortex generators relative to the fuselage. The vortex generators are oriented at specific angles and positions that create asymmetric vortex patterns, which effectively counteract the sponson vortex influences and provide both drag reduction and enhanced directional stability.
Solution Approach 2:
The patent addresses the limited effectiveness of conventional vortex generators by introducing a third dimension - vertical positioning and angular orientation. By arranging the vortex generators at specific angles and heights on the fuselage underside, the patent creates vortices that extend into the vertical dimension, enhancing their ability to counteract sponson vortices and improve directional stability.
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 solution enhances directional stability by up to +15% and reduces aerodynamic drag by 2.5×10−5 (cw-value) during cruising, without requiring significant constructive modifications to the aircraft.
Implementation Method 1
The aerodynamic auxiliary surface is designed for generating vortices when it is subjected to an oncoming air flow
Data Source
AI summary
An arrangement of aerodynamic auxiliary surfaces is configured for being arranged on the underside of an aircraft and furthermore includes a longitudinal axis and at least one aerodynamic auxiliary surface, wherein the aerodynamic auxiliary surface is laterally offset referred to the longitudinal axis, and wherein the aerodynamic auxiliary surface is configured for generating vortices when it is subjected to an oncoming air flow. This makes it possible to compensate vortices caused by the shape of the aircraft such that the directional stability of the aircraft can be improved and the aerodynamic drag may be reduced.