Hypersonic Inlet Shockwave Integration for Aerodynamic Efficiency
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Solution Overview
Problem
Hypersonic aircraft designs face inefficiencies in engine inlet design, particularly at high speeds, where two-dimensional inlets are not as effective as three-dimensional inlets, and existing designs do not optimize aerodynamic efficiency without detracting from wing performance.
Innovation Solution
The design of three-dimensional engine inlets for hypersonic aircraft that align their leading edges with the wing shockwave, using streamline tracing to define both inner and outer shapes, allowing the inlets to ride on the wing shockwave and enhance engine performance without altering the shockwave, thereby improving aerodynamic efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If two-dimensional inlets are used for hypersonic aircraft, then the design is simpler, but the engine performance is not as efficient as three-dimensional inlets at hypersonic speeds
Solution Approach 1:
The patent transitions from two-dimensional inlet designs to three-dimensional inlet configurations by positioning inlet leading edges at the intersection of the wing shockwave and inlet shockwaves. This dimensional change allows the inlet to effectively capture and compress hypersonic airflow, improving engine performance while maintaining aerodynamic efficiency through the integrated 3D geometry.
2Productivity
If three-dimensional inlets are designed for hypersonic aircraft, then engine performance is improved, but the aerodynamic efficiency of the waverider wing may be detracted
Solution Approach 1:
The patent merges the wing shockwave and inlet shockwave into a unified aerodynamic system. By positioning the inlet leading edge at the intersection of these shockwaves, the design combines the wing's aerodynamic function with the inlet's compression function, allowing both to ride on the same shockwave structure. This integration ensures that the three-dimensional inlet improves engine performance without compromising the waverider wing's aerodynamic efficiency.
3Productivity
If the inlet leading edge is positioned at the intersection of wing shockwave and inlet shockwave, then both waverider wing and engine inlet ride on the shockwave improving efficiency, but the design complexity increases
Solution Approach 1:
The patent applies local quality by defining the inlet leading edge geometry through the specific intersection point of the wing shockwave and inlet shockwave. This localized geometric definition ensures that the inlet structure is optimized precisely where the shockwaves intersect, creating the efficient three-dimensional configuration needed for both the wing and inlet to ride on the shockwave simultaneously, thereby improving overall aircraft efficiency.
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 approach improves engine performance by ensuring the engine inlets operate efficiently while maintaining the aerodynamic efficiency of the waverider wing, enhancing the overall performance of the hypersonic aircraft.
Implementation Method 1
In traveling at such high speeds, pressure from impacted air molecules may build up in front of aircraft forward-facing surfaces, resulting in a shockwave.
Data Source
AI summary
Methods, aircraft, and engine nacelles are disclosed. A wing leading edge of a planform is superimposed on a wing shockwave that extends in a first direction from a shockwave apex toward the wing leading edge. A waverider shape is streamline traced between the wing leading edge and a trailing edge of the planform to form a waverider wing. A position of an engine inlet vertex relative to the waverider wing is identified. An inlet shockwave is projected from the inlet vertex in a second direction generally opposed to the first direction. The inlet shockwave intersects the wing shockwave. An inlet leading edge of an engine inlet includes a lower leading edge including a plurality of points where the inlet shockwave intersects the wing shockwave.