Implementation of the panel method to the solution of flow around aircraft

Yassir, ABBAS; Mohammed, M Rahman

doi:10.13111/2066-8201.2015.7.2.1

Cited by 1 publication

(1 citation statement)

References 4 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The aerodynamic characteristics can then be calculated using the Bernoulli equations. This approach turns out to be faster than other numerical methods (finite difference, finite volume or finite element) since the solution is at the body surface only (Abbas and Madbouli, 2015). However, due to the limitation of its control equation and grid layout, it is difficult to obtain high-accuracy results in practical case where viscosity is important.…”

Section: Fast Calculational Panel Methodsmentioning

confidence: 99%

An efficient method for helicopter fuselage shape optimization

Zhu

Shi

2023

AEAT

View full text Add to dashboard Cite

Purpose This paper aims to develop a new method of fuselage drag optimization that can obtain results faster than the conventional methods based on full computational fluid dynamics (CFD) calculations and can be used to improve the efficiency of preliminary design. Design/methodology/approach An efficient method for helicopter fuselage shape optimization based on surrogate-based optimization is presented. Two numerical simulation methods are applied in different stages of optimization according to their relative advantages. The fast panel method is used to calculate the sample data to save calculation time for a large number of sample points. The initial solution is obtained by combining the Kriging surrogate model and the multi-island genetic algorithm. Then, the accuracy of the solution is determined by using the infill criteria based on CFD corrections. A parametric model of the fuselage is established by several characteristic sections and guiding curves. Findings It is demonstrated that this method can greatly reduce the calculation time while ensuring a high accuracy in the XH-59A helicopter example. The drag coefficient of the optimized fuselage is reduced by 13.3%. Because of the use of different calculation methods for samples, this novel method reduces the total calculation time by almost fourfold compared with full CFD calculations. Originality/value To the best of the authors’ knowledge, this is the first study to provide a novel method of fuselage drag optimization by combining different numerical simulation methods. Some suggestions on fuselage shape optimization are given for the XH-59A example.

show abstract

Section: Fast Calculational Panel Methodsmentioning

confidence: 99%