Aircraft Wing Trip Device for Laminar Flow Transition and Load Control
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Solution Overview
Problem
Existing aircraft wing designs face challenges in maintaining laminar boundary layer flow to reduce drag while ensuring the wing can withstand extreme load conditions without increasing weight, and there is a need for accurate load and handling-quality data during wind tunnel testing.
Innovation Solution
A fixed-location trip device is placed along the span of the wing to control the transition from laminar to turbulent boundary layer flow, setting a downstream limit on laminar flow extent and reducing load increases, with systematic wind tunnel testing to predict control effectiveness and handling qualities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If the extent of laminar flow is increased to reduce drag, then aerodynamic efficiency is improved, but the wing weight increases to withstand extreme load conditions
Solution Approach 1:
A trip device is installed at a predetermined location on the wing surface to proactively trigger transition from laminar to turbulent flow at a specific chordwise position. This preliminary action ensures that the transition occurs at the optimal location that balances drag reduction benefits with structural load limits, avoiding the need to increase wing weight for uncertainty margins.
Solution Approach 2:
The trip device actively changes the flow regime parameter from laminar to turbulent at a controlled location. By manipulating the boundary layer transition point through the trip device, the patent optimizes the extent of laminar flow to maximize drag reduction while keeping the wing structure within acceptable load limits, thus avoiding weight increases.
2Loss of energy
If the extent of laminar flow is increased to reduce drag, then aerodynamic efficiency is improved, but the wing structural strength must be increased to handle extreme load conditions
Solution Approach 1:
The trip device is positioned at a location that corresponds to the maximum acceptable shock load position. By triggering transition at this predetermined location, the patent ensures that the wing structure only needs to be designed for the known maximum loads, rather than for uncertain extended laminar flow conditions, thus avoiding the need to increase structural strength.
3Measurement precision
If wind tunnel testing is conducted to gather load and handling-quality data, then flight performance prediction is improved, but testing complexity and uncertainty increase
Solution Approach 1:
The trip device is installed during wind tunnel testing to establish a known and controlled transition location. This preliminary configuration allows testers to gather accurate load and handling-quality data under well-defined flow conditions, reducing uncertainty in flight performance predictions without requiring overly complex testing procedures.
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 trip device enhances aerodynamic efficiency by maintaining laminar flow benefits while limiting loads, providing a reliable predictor for structural response and reducing uncertainty in flight performance.
Implementation Method 1
maintaining laminar boundary layer flow over the wing which reduces drag... delaying the transition to turbulent flow in the boundary layer on the surface
Implementation Method 2
Laminar flow control on an aerodynamic surface reduces drag and improves fuel efficiency by delaying the transition to turbulent flow
Data Source
Figure 1A~1B
Figure 2
Figure 3
AI summary
An aircraft wing (104) is disclosed herein having a fixed-location trip device (108) placed along the span of the wing to transition airflow from laminar flow (302) to turbulent flow (306) so that potential load increases are limited and flight performance uncertainties associated with laminar flow wings are reduced. Wings designed for extended laminar flow offer the potential to significantly reduce airplane drag and fuel consumption. A collateral impact of a laminar flow wing is the generation of elevated wing loads at critical load conditions. This impact is mitigated by controlling the downstream limit of transition at these critical load conditions.