Rear Fuselage Stagnation Area for Thrust and Drag Reduction
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Solution Overview
Problem
Current systems for drag reduction in vehicle and aircraft designs do not effectively maximize thrust output and fuel efficiency, as they rely on outdated designs that do not optimize the interaction between pressure thrust and aerodynamic drag.
Innovation Solution
Creating a stagnation area and a convex cusp area on the rear portion of vehicles or aircraft fuselages, with adjustable concavity and suction inlets to enhance thrust output and fuel efficiency by optimizing the ratio of stagnation area to inlet area, and using regenerative braking to manage power requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If traditional drag reduction systems are used in vehicle and aircraft designs, then the basic aerodynamic performance is maintained, but thrust output is not maximized and fuel efficiency is not optimized
Solution Approach 1:
The rear portion of the vehicle or aircraft fuselage is divided into distinct functional zones: a stagnation area with specific concavity, a suction inlet, and a convex cusp area. This segmentation allows each zone to independently contribute to optimizing the pressure distribution, maximizing thrust output while maintaining fuel efficiency.
Solution Approach 2:
The invention applies specific geometric characteristics (concavity of stagnation area, convexity of cusp area) and localized suction at the inlet to create optimal pressure thrust conditions. These localized quality modifications to the rear portion geometry enable enhanced thrust generation without compromising overall fuel efficiency.
2Power
If the rear portion geometry is modified to increase thrust output through enhanced stagnation area concavity, then pressure thrust is maximized, but the complexity of the vehicle design increases
Solution Approach 1:
The invention employs curved geometric features including a concave stagnation area and a convex cusp area at the rear portion. These curvature-based modifications create the necessary pressure distribution for enhanced thrust while maintaining a relatively simple overall structure that integrates smoothly with conventional vehicle designs.
Solution Approach 2:
The invention optimizes specific geometric parameters of the rear portion, including the concavity of the stagnation area and the convexity of the cusp area, to maximize pressure thrust. By carefully controlling these parameters, the system achieves enhanced thrust output without requiring complex mechanical systems or multiple moving parts.
3Area of moving object
If the fuselage width is increased to improve vehicle performance, then cargo capacity and stability are enhanced, but aerodynamic drag increases and fuel efficiency deteriorates
Solution Approach 1:
The invention converts the potentially harmful wake turbulence and low-pressure regions that typically form behind wider fuselages into beneficial high-pressure stagnation zones. By strategically positioning the concave stagnation area and convex cusp at the rear, the system recovers energy from the expanded fuselage cross-section and transforms it into useful pressure thrust, allowing wider designs to maintain or improve fuel 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 significantly reduces aerodynamic drag and increases thrust output, leading to improved fuel efficiency and the ability to design wider aircraft without increased fuel burn, as demonstrated through computational fluid dynamics and experimental testing.
Implementation Method 1
The general concept of pressure thrust is known in the airfoil and aircraft design arts. The phenomenon uses energy of the air rushing past an airplane's wing, tail surfaces or fuselage, to push that wing, tail surface or fuselage forward.
Implementation Method 2
This approach significantly reduces aerodynamic drag and increases thrust output
Implementation Method 3
Creating a stagnation area and a convex cusp area on the rear portion of vehicles or aircraft fuselages, with adjustable concavity and suction inlets to enhance thrust output
Data Source
AI summary
A system and method for drag reduction allows thrust output, fuel efficiency or both to be maximized. Specifically, a rear portion of a body or motor vehicle may be modified to increase thrust output, fuel efficiency or both by creating a stagnation area, a suction inlet and a convex cusp area formed on the rear portion of the motor vehicle. Increasing the concavity or camber or sharpness of the radius of the stagnation area results in greater local pressure coefficient, which results in greater thrust output. The size and shape of the suction inlet and the convex cusp area will also have an effect on thrust output and fuel efficiency. A width and volume of an airplane fuselage may be increased.