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<p>The study deals with aerodynamic analysis of a general aviation aircraft Piper PA-24, a monoplane with low-wing configuration using FlightStream, a panel-method based vorticity solver. The present-day preliminary design phase requires a full-scale design analysis mainly to understand the design and aerodynamic performance in a fully integrated aircraft with all the external components attached to the aircraft. Unlike the discretised Navier–stokes equation-based solver, FlightStream uses potential flow Laplace equation to solve for the flow physics reducing the dependency on complex three-dimensional meshes for preliminary design stage analysis. The aircraft is predominantly analysed to observe the aerodynamic performance for angle of attacks varying from <InlineEquation ID="IEq1"> <EquationSource Format="TEX">\(-4^\circ \)</EquationSource> </InlineEquation> to <InlineEquation ID="IEq2"> <EquationSource Format="TEX">\(+20^\circ \)</EquationSource> </InlineEquation>, and validated with the available experimental data. The study also includes the grid independence check and thrust coefficient analysis to optimize the aerodynamic performance at cruising conditions. The findings will benefit aerospace engineers and researchers involved in aircraft design, aerodynamic optimization, and rapid preliminary analysis.</p>

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Aerodynamic analysis of piper PA-24 aircraft using flighstream—a vorticity-based panel solver

  • 期刊论文

  • 发表日期：

    2025年12月18日

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  • Humesh Sanaboyina,
  • Santosh Kumar Pradhan,
  • G. Srinivas

摘要

The study deals with aerodynamic analysis of a general aviation aircraft Piper PA-24, a monoplane with low-wing configuration using FlightStream, a panel-method based vorticity solver. The present-day preliminary design phase requires a full-scale design analysis mainly to understand the design and aerodynamic performance in a fully integrated aircraft with all the external components attached to the aircraft. Unlike the discretised Navier–stokes equation-based solver, FlightStream uses potential flow Laplace equation to solve for the flow physics reducing the dependency on complex three-dimensional meshes for preliminary design stage analysis. The aircraft is predominantly analysed to observe the aerodynamic performance for angle of attacks varying from \(-4^\circ \) to \(+20^\circ \) , and validated with the available experimental data. The study also includes the grid independence check and thrust coefficient analysis to optimize the aerodynamic performance at cruising conditions. The findings will benefit aerospace engineers and researchers involved in aircraft design, aerodynamic optimization, and rapid preliminary analysis.