Preprint Article Version 1 Preserved in Portico This version is not peer-reviewed

Radical Reduction of Aircraft Fuel Consumption by Optimizing Aerofoil by New Evolutionary Algorithms

Version 1 : Received: 3 June 2021 / Approved: 8 June 2021 / Online: 8 June 2021 (12:17:22 CEST)

How to cite: Muller, J. Radical Reduction of Aircraft Fuel Consumption by Optimizing Aerofoil by New Evolutionary Algorithms. Preprints 2021, 2021060219 (doi: 10.20944/preprints202106.0219.v1). Muller, J. Radical Reduction of Aircraft Fuel Consumption by Optimizing Aerofoil by New Evolutionary Algorithms. Preprints 2021, 2021060219 (doi: 10.20944/preprints202106.0219.v1).

Abstract

This work deals with aerofoil aerodynamic features optimization, not only to improve flight features, but also to improve economy, ecology and safety of parameters of flight technique. In cruise mission, occupying the most flight time, the most important parameter is aerodynamic drag, which directly influences the aeroplane operational economy of transportation. Drag reduction is adequately reflected in the fuel consumption reduction. Consumption reduction is also adequately reflected in the flight ecology. In take-off and landing mission, the safety is priority and directly influences the aerofoil geometry. For cruise mission the new modified evolutionary algorithms (EA) are used to parameters incoming to Bezier-PARSEC 3434 parametrization. Such aerofoil is processed and evaluated by the Xfoil program. The change of model parameters results to optimal aerofoil shape. The DCAG (Direct Control Aerofoil Geometry) is unique developed mechanical device, makes possible the change of curvature of aerofoil, and also aerofoil geometry. DCAG is based on the rotary principle, which makes it possible to define the curvature of aerofoil for every roll as well as defining the geometry in the variable parts of aerofoil. For take-off and landing mission the best combination of slots and flaps is choosed. To improve of laminarity and reduce turbulent flow the DCAG is used. The work results to optimization, which is 50 times faster in comparison to ordinary optimization, with minimum of input parameters (flight speed, chord length, range of angles of attack and fitness function). The optimized aerofoil can achieve savings in fuel consumption up to 44% in comparison with unoptimized aerofoil, the aerodynamic drag reduction up to 44%. The output was checked by ANSYS Fluent simulation.

Subject Areas

Evolutionary algorithms, shape of aerofoil, optimization of shape, Bezier-PARSEC model

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