Aerodynamic Flow Control Panel for Aircraft Body Vortex Mitigation
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Solution Overview
Problem
Aerodynamic phenomena such as vortex shedding on aircraft bodies with aerodynamically squat shapes lead to increased aerodynamic resistance, noise, and erroneous data acquisition due to pressure drops, which existing solutions fail to effectively address across various flight conditions.
Innovation Solution
A panel with at least one inlet and one outlet aperture is positioned on the aircraft surface to control fluid flow, generating an output flow that interferes with and reduces aerodynamic phenomena, while maintaining a lightweight design and minimizing acoustic disturbances.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a body with aerodynamically squat shape (cylindrical or conical) is used for functional requirements, then the body can perform its intended function, but vortex shedding occurs causing increased aerodynamic resistance and structural stress
Solution Approach 1:
A panel is introduced as an intermediary element between the flight path and the IMFP body. This panel generates a controlled output flow that acts as a mediator to interfere with and reduce the vortex shedding phenomenon, thereby decreasing aerodynamic resistance and structural stress without modifying the functional IMFP body itself
Solution Approach 2:
The solution segments the aerodynamic control function from the IMFP body by introducing a separate panel structure. The panel is divided into multiple apertures (inlet and outlet) that work together to generate the beneficial output flow, allowing the IMFP to maintain its functional shape while the panel handles aerodynamic optimization
2Ease of manufacture
If the IMFP has a circular section shape for structural simplicity, then manufacturing is easier, but this shape generates vortex shedding causing noise and pressure drop
Solution Approach 1:
Rather than modifying the IMFP structure itself, a panel is introduced as an external intermediary that generates a controlled output flow to counteract the harmful effects of the circular IMFP shape. This approach maintains manufacturing simplicity while eliminating noise and pressure drop through flow interference
Solution Approach 2:
The panel converts the harmful vortex shedding phenomenon into a beneficial effect by generating an output flow that interferes with and reduces the vortex magnitude. The same geometric features that cause vortex shedding are leveraged, but the panel's output flow transforms the harmful effect into a reduced aerodynamic disturbance
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 panel significantly reduces the magnitude and frequency of vortices by up to 50%, improving signal accuracy and reducing structural fatigue and noise, and is effective across a broad range of aircraft speeds and altitudes.
Implementation Method 1
generating an output flow that interferes with the aerodynamic phenomena generated by the body and thus eliminating the above-mentioned problems
Implementation Method 2
A body comprising at least one circular or semicircular or elliptical or aerodynamically squat portion creates a trail of vortices detaching from the body itself in an alternated, non-stationary manner
Implementation Method 3
said panel comprises at least one inlet aperture and at least one outlet aperture, through which a portion of the fluid flow in which said body or object is immersed can pass
Data Source
AI summary
A panel (3) for controlling the aerodynamic phenomena generated by a body (0) to be positioned on a surface of an aircraft (V). The panel (3) can be associated with the base of the body (0) and includes at least one inlet aperture (322) and at least one outlet aperture (322′) placed in communication with each other, through which a portion of a fluid flow (W) in which the body (0) is immersed can selectively pass. The inlet aperture (322) is located upstream of the body (0) and the outlet aperture (322′) is located downstream of the body (0), with respect to the direction of the fluid flow (W).