Wing Slot Air Acceleration for Lift and Drag Reduction
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Solution Overview
Problem
Aircraft wing configurations with drooped leading edges and slotted wings provide aerodynamic improvements but face challenges at low-speed operations and integrating anti-ice features, leading to reduced lift-to-drag ratios and disrupted laminar flow.
Innovation Solution
The implementation of air nozzles at the slot between the wing and flap, which accelerate air from an air supply source or compressor assembly, enhancing lift and reducing drag by ejecting pressurized air into the slot, thereby maintaining laminar flow and improving low-speed aerodynamics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a slotted-wing configuration is used, then aerodynamic performance is improved, but lift-to-drag ratio decreases at low-speed operations
Solution Approach 1:
The patent applies pneumatic principles by using pressurized air from the engine compressor system to blow through slots in the wing and flap surfaces. This pneumatic flow control actively manages the boundary layer, preventing flow separation and maintaining attached flow at low speeds, thereby improving the lift-to-drag ratio while preserving the aerodynamic benefits of the slotted-wing configuration.
Solution Approach 2:
The patent changes the physical state and flow parameters of air by pressurizing it through the engine compressor and directing it through controlled slots at specific pressures and velocities. This parameter change transforms the ambient air into a controlled flow that actively manages boundary layer behavior, resolving the contradiction between maintaining aerodynamic performance and improving lift-to-drag ratio at low speeds.
2Productivity
If a drooped leading edge is used, then flight aerodynamics are improved, but low-speed operations are degraded
Solution Approach 1:
The patent uses pneumatic flow from pressurized air to counteract the adverse effects of the drooped leading edge at low speeds. The controlled air flow through slots near the leading edge prevents boundary layer separation, allowing the drooped configuration to maintain its high-speed aerodynamic advantages while improving low-speed performance through active flow control.
Solution Approach 2:
The patent introduces dynamic control to the static drooped leading edge configuration by using variable air pressure and flow rate through the slots. This dynamic adjustment allows the system to adapt to different flight regimes, maintaining optimal aerodynamic performance across both high-speed and low-speed operations.
3Reliability
If anti-ice features are integrated, then wing protection is improved, but aerodynamic performance is reduced
Solution Approach 1:
The patent merges the anti-ice system with the aerodynamic flow control system by using the same pressurized air source from the engine compressor for both purposes. The air that would otherwise be used solely for anti-icing is redirected through slots to provide both wing protection and active flow control, thereby maintaining aerodynamic performance while ensuring reliable anti-ice protection.
Solution Approach 2:
The patent makes the pressurized air system multi-functional by using it for both anti-ice protection and aerodynamic flow control. This universal application of the same system eliminates the need for separate systems, preventing the aerodynamic performance reduction that would result from adding dedicated anti-ice features while still providing reliable wing protection.
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 increases the lift-to-drag ratio, enabling higher load carrying capacity, shorter runway lengths, and longer range, while maintaining laminar flow benefits and reducing drag, thus enhancing overall flight performance.
Implementation Method 1
a compressor assembly configured to accelerate air from the inlet port
Implementation Method 2
the nozzle accelerates air such as from an air supply source of the aircraft (e.g., anti-ice system) or an inlet port and compressor assembly, and ejects the air into the slot
Data Source
AI summary
Air acceleration at slot of aircraft wing. In one embodiment, a wing includes an air duct configured to transport air in a spanwise direction along a leading edge of the wing from an air supply source of the aircraft. The wing further includes a discharge duct configured to transport the air in an aft direction from the air duct to an aft end of the wing, and one or more nozzles disposed on the aft end of the wing and configured to accelerate air into a slot between the wing and a flap of the aircraft to increase lift and reduce drag for the wing.