Airfoil Wave-Tripping Channels for Supersonic Shockwave Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Shock waves generated during supersonic flight cause increased drag, reduced controllability, and decreased fuel efficiency in aircraft design.
Innovation Solution
Incorporation of supersonic wave-tripping channels on the wings of aircraft, which dissipate pressure build-up and divert airflow to prevent shockwave formation, promoting laminar flow and reducing energy consumption.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If aircraft travels at near or above Mach number, then speed is improved, but shock waves are generated causing increased drag and reduced fuel efficiency
Solution Approach 1:
The patent applies preliminary action by positioning wave-tripping channels at specific locations on the airfoil surface where transonic flow points are expected to occur. These channels pre-condition the airflow before shock waves can fully develop, trip the boundary layer transition from laminar to turbulent flow in advance, and dissipate pressure build-up that would otherwise lead to shock wave formation and associated energy losses.
2Speed
If aircraft travels at near or above Mach number, then speed is improved, but shock waves cause increased drag
Solution Approach 1:
The patent converts the harmful effect of pressure build-up and incipient shock waves into a beneficial outcome by using wave-tripping channels to intentionally induce controlled boundary layer transition. The channels transform the potentially harmful pressure gradients into controlled flow conditions that prevent full shock wave development, thereby reducing drag while maintaining supersonic speeds.
3Speed
If supersonic flow regions are allowed to develop, then aircraft speed is improved, but flow separations and shock waves reduce controllability
Solution Approach 1:
The wave-tripping channels provide a form of passive feedback control by being positioned at locations where transonic flow points are predicted to occur based on aerodynamic analysis. The channels respond to the developing flow conditions by tripping the boundary layer at the optimal moment and location, preventing flow separations and maintaining attached flow over the airfoil surface, thereby preserving controllability and 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
Reduces drag and improves aerodynamic efficiency by preventing shockwave formation, thereby decreasing energy and fuel requirements.
Implementation Method 1
dissipate pressure build-up and divert airflow to prevent shockwave formation
Implementation Method 2
Shock waves are regions of airflow, along a surface of an object (e.g., an airfoil) in which the properties of that airflow (i.e., fluid pressure and density) change dramatically
Implementation Method 3
promoting laminar flow and reducing energy consumption
Data Source
AI summary
A wing structure for a supersonic aircraft including a pair of supersonic wave-tripping channels formed on each of two laterally extending wings of the supersonic aircraft, wherein each of the pair of supersonic wave-tripping channels extend in a span-wise direction of the wings respectively, wherein an upper supersonic wave-tripping channel of the pair of supersonic wave-tripping channels is disposed on an upper surface of each of the wings and a lower supersonic wave-tripping channel of the pair of supersonic wave-tripping channels is disposed on a lower surface of each of the wings, wherein the upper supersonic wave-tripping channel and the lower supersonic wave-tripping channel are set back from a leading edge of the wings respectively.