Aerodynamic Surface Assembly with Fluidic Orifice for Flow Control
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Solution Overview
Problem
Existing aerodynamic surface technologies face inefficiencies in active flow control, particularly in high-lift systems, where traditional methods like fluidic oscillators have varying effectiveness and complexity, and there is a need for improved control of flow separation and increased coefficient of lift without increasing complexity.
Innovation Solution
The aerodynamic surface assembly features a smooth contour with strategically placed orifices and overhangs, combined with a fluidic actuator having curved passageways and a plenum, which directs fluid flow to control flow separation and enhance lift by decoupling actuation frequencies from global flow instabilities, facilitating self-oscillation and improved fluid interaction with the flow field.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional fluidic oscillators are used for active flow control, then flow separation can be mitigated, but the device footprint becomes relatively large and complexity increases
Solution Approach 1:
The aerodynamic surface is segmented into multiple zones with discrete orifices distributed across the surface. Each orifice acts as an independent flow control element, allowing localized flow separation mitigation without requiring a large centralized actuator device.
Solution Approach 2:
The invention transitions from using large planar fluidic oscillator structures to utilizing the third dimension by embedding compact orifices within the aerodynamic surface thickness. This dimensional transition reduces the device footprint while maintaining flow control functionality.
2Reliability
If high-lift systems use complex multi-element designs with intricate positioning mechanisms, then performance characteristics improve, but weight and number of parts increase
Solution Approach 1:
The invention extracts the essential flow control function from complex multi-element high-lift systems with positioning mechanisms. By implementing active flow control through orifices directly on the aerodynamic surface, the system eliminates heavy mechanical positioning mechanisms while retaining performance enhancement capabilities.
Solution Approach 2:
The invention replaces mechanical positioning mechanisms with fluidic actuation. Instead of mechanically adjusting high-lift system elements, the system uses fluid injection through orifices to control flow separation and enhance lift, thereby reducing weight and part count.
3Reliability
If actuation frequency matches wake instability frequency, then Coanda-like deflection of vortices is achieved, but control is limited to separated flow conditions
Solution Approach 1:
The invention implements dynamic flow control by varying actuation frequency across different operating conditions. The system adapts actuation parameters in real-time to maintain effectiveness whether the flow is separated or attached, providing versatility across different flight regimes.
Solution Approach 2:
The invention changes the actuation frequency parameter to decouple from wake instability frequency. By operating at frequencies that do not resonate with wake instabilities, the system achieves effective flow control in both separated and attached flow conditions, expanding adaptability.
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 effectively mitigates flow separation and enhances aerodynamic performance by increasing the coefficient of lift while reducing complexity and weight, improving cruise efficiency and high-lift system performance.
Implementation Method 1
This actuation induces a Coanda-like deflection of the shed vortices toward the surface of the stalled airfoil
Implementation Method 2
fluidic oscillators that generate self-oscillating jets so as to provide spatial and temporal oscillation
Implementation Method 3
an aerodynamic surface may employ active flow control in order to inject fluid or momentum into the flow field passing proximate the aerodynamic surface
Implementation Method 4
the injection of fluid or momentum into a flow field may mitigate the partial or complete flow separation of the flow field from the aerodynamic surface
Data Source
AI summary
An aerodynamic surface assembly is provided to facilitate control of the flow over the aerodynamic surface. The aerodynamic surface assembly includes an aerodynamic surface defining an outer mold line over which a fluid is to flow in a downstream direction. The outer mold line defines a smooth contour that is interrupted by step down region that is inset relative to the smooth contour defined by the outer mold line upstream thereof. The aerodynamic surface defines an orifice opening in to the step down region. The aerodynamic surface assembly may also include an overhang extending from the outer mold line of the aerodynamic surface upstream at the orifice. The overhang extends in the downstream direction and at least partially over the orifice. The aerodynamic surface assembly may also include a fluidic actuator defining a pair of curved passageways extending from an input region and are in fluid communication with the orifice.