Wingtip De Laval Nozzle for Induced Drag Reduction
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Solution Overview
Problem
Existing winglets, while reducing induced drag, increase wing area and weight, and are not universally applicable to all aircraft types.
Innovation Solution
Creating an additional airflow at the wing tip using a de Laval nozzle positioned at the wing end to generate flows with velocities greater than the wing sweep rate, forming vortices with opposite rotations to reduce induced drag without altering the wing geometry.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If winglets are used to reduce induced drag, then induced drag is reduced, but wing area and weight increase
Solution Approach 1:
The patent uses a de Laval nozzle to generate a high-velocity gas jet (pneumatic flow) at the wingtip. This jet creates a vortex that reduces induced drag without requiring physical winglet structures, thereby avoiding the weight penalty associated with traditional winglets while maintaining the aerodynamic benefit of vortex control
Solution Approach 2:
The invention changes the flow velocity parameter by injecting a high-velocity jet (Mach number > 0.3) at the wingtip. This parameter change creates the desired vortex effect to reduce induced drag without the need for increased wing area or additional structural weight
2Loss of energy
If winglets are designed for each specific aircraft, then induced drag is reduced for that aircraft, but device complexity and design time increase
Solution Approach 1:
The de Laval nozzle system is a universal solution that can be applied to various aircraft types without requiring custom-designed winglet structures for each aircraft. The pneumatic flow generation mechanism provides a standardized approach that reduces induced drag across different aircraft configurations while simplifying the design process
3Loss of energy
If wing area is increased to reduce induced drag, then induced drag is reduced, but aerodynamic drag and weight increase
Solution Approach 1:
The patent employs pneumatic flow injection through a de Laval nozzle to create the vortex effect without increasing wing area. This approach avoids the harmful side effect of increased parasitic drag that would result from larger wing surfaces, while still achieving the goal of reducing induced drag through vortex control
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
Reduces induced drag and enhances lift without increasing wing area or weight, applicable to various aircraft designs.
Implementation Method 1
A high velocity flow can be created by a de Laval nozzle placed in a suitable location at the end of the wing. The nozzle is a convergent-divergent tube in which the gas at the inlet contracts, increasing its velocity, then expands and increases its velocity again due to the increase in kinetic energy of the flow on account of the pressure drop in the expanding section
Implementation Method 2
the gas at the inlet contracts, increasing its velocity, then expands and increases its velocity again due to the increase in kinetic energy of the flow on account of the pressure drop in the expanding section
Implementation Method 3
The flow on the upper surface of the wing will be in an inward-outward direction, thereby creating conditions for a smooth circulation of the entire wing and forming a vortex together with the new flow. The flow from the lower surface of the wing will also be directed outwards and will form a second vortex. As a result, a vortex will form at the end of the wing, outboard of the end of the wing, which will be less intense as the two vortices have opposite directions of rotation
Data Source
AI summary
Reduction of the induced drag by placing a convergent-divergent nozzle at the wingtip which creates an additional airflow with a velocity greater than the airflow velocity around the wing, which changes the nature and direction of the airflow along the upper and lower surfaces at the wingtip, thus forming a new vortex of lesser intensity, which is shifted to the sides of the wingtip, creating conditions for better airflow, less induced drag, and greater aerodynamic force.