Airfoil Heated-Zone Control for Supersonic Shock Reduction

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Solution Overview

Problem

Conventional aircraft designs experience a significant drop in lift-to-drag ratio at supersonic and hypersonic speeds due to increased drag caused by shock waves, leading to inefficient energy consumption and noise pollution, with existing mitigation techniques failing to improve the lift-over-drag ratio effectively.

Innovation Solution

Heating an area on the underside of the aircraft to increase the speed of sound locally, reducing or eliminating compression shock waves and enhancing lift while minimizing drag, using methods such as RF-induced plasma or laser-guided electrical discharges to create a heated zone.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Speed

If conventional aircraft designs operate at supersonic and hypersonic speeds, then speed increases, but drag increases dramatically due to shock waves causing lift-to-drag ratio to drop

Engineering Contradiction:

Improveflight speedVSAvoiddrag

Core Design Contradiction:

SpeedVSLoss of energy

Solution Approach 1:

The patent changes the temperature parameter of the air in the heated zone to increase the local speed of sound. By heating the air to high temperatures (sufficient to raise the local speed of sound above the aircraft's flight speed), the patent transforms the supersonic flow conditions into effective subsonic conditions relative to the heated air, thereby reducing shock wave formation and drag while maintaining high flight speed.

Inventive Principle:

Principle #35Parameter changes

Solution Approach 2:

The patent introduces a thermal dimension to the aerodynamic problem by creating a heated zone around the aircraft. This adds a temperature/energy dimension to the traditional speed-density-pressure aerodynamic parameters, allowing the aircraft to interact with air in a fundamentally different state that reduces compressibility effects and shock wave formation.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

2Speed

If conventional aircraft designs operate at supersonic and hypersonic speeds, then speed increases, but noise pollution increases due to sonic boom from compression shock waves

Engineering Contradiction:

Improveflight speedVSAvoidnoise pollution

Core Design Contradiction:

SpeedVSObject-generated harmful factors

Solution Approach 1:

By changing the temperature parameter of the air in the heated zone, the patent raises the local speed of sound above the aircraft's flight speed. This parameter change prevents the formation of compression shock waves that generate sonic booms, thereby eliminating noise pollution while maintaining high flight speed.

Inventive Principle:

Principle #35Parameter changes

3Loss of energy

If energy is deposited to heat air and increase speed of sound locally, then drag reduction and lift enhancement occur, but energy consumption increases

Engineering Contradiction:

ImprovedragVSAvoidenergy consumption

Core Design Contradiction:

Loss of energyVSUse of energy by moving object

Solution Approach 1:

The patent applies partial heating to a specific zone around the aircraft rather than heating the entire aircraft or surrounding air mass. By concentrating energy deposition in a localized heated zone where it most effectively increases the local speed of sound, the patent achieves drag reduction and lift enhancement with reduced overall energy consumption compared to comprehensive heating approaches.

Inventive Principle:

Principle #16Partial or excessive action

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 enhances the lift-to-drag ratio by reducing far-field shock formation and noise, achieving significant drag reduction and improved aerodynamic efficiency, allowing for more fuel-efficient supersonic flight with reduced propulsion power requirements.

Implementation Method 1

heating air or other gas in a heated zone to a temperature sufficient to increase the speed of sound in the heated zone above the speed of the body moving through the gas

Methodology Applied

Scientific EffectSpeed of sound increases with temperature: Speed of Sound

Implementation Method 2

The increased speed of sound in the heated air reduces or eliminates the formation of a compression shock wave in the far field

Methodology Applied

Scientific EffectCompressibility effects reduction through heating: Heating

Implementation Method 3

using methods such as RF-induced plasma or laser-guided electrical discharges to create a heated zone

Methodology Applied

Scientific EffectRF-induced plasma heating: Plasma

Implementation Method 4

using methods such as RF-induced plasma or laser-guided electrical discharges to create a heated zone

Methodology Applied

Scientific EffectLaser-guided electrical discharge heating: Laser

Data Source

PatentUS11014651B1Enhanced high-speed airfoil performance, including increased lift/drag ratio, from localized high-temperature speed of sound increases, and associated systems and methods

Publication Date: 2021.05.25 ELECTRIC SKY HOLDINGS INC

AI summary

Enhanced high-speed aircraft performance, including increased lift/drag ratio, from localized high-temperature speed of sound increases, and associated systems and methods are disclosed. A representative method for operating a vehicle includes, while a lifting body of the vehicle is immersed in a gas, heating the gas in a target volume sufficiently to increase the speed of sound in the gas relative to the speed of sound in the gas outside the target volume. The target volume can be positioned adjacent to, forward of, and/or along a pressure surface of the lifting body.