Spin Aerodynamic Modeling for a Fixed-Wing Aircraft Using Flight Data

To understand the characteristics of aircraft stall for better aerodynamic model, the physical essence of the stall phenomena of aircraft is first introduced, and then a Wavelet Neural Network (WNN) is proposed to set up the stall aerodynamic model. Numerical examples indicates that through the deep cognition of the stall phenomena of aircraft the proposed stall aerodynamic method has a better accuracy than the traditional neural network and is also effective and feasible.

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Longitudinal Aerodynamic Modeling of the Adaptive Compliant Trailing Edge Flaps on a GIII Aircraft and Comparisons to Flight Data

AIAA Atmospheric Flight Mechanics Conference ◽

10.2514/6.2016-3703 ◽

2016 ◽

Cited By ~ 6

Author(s):

Mark S. Smith ◽

Trong T. Bui ◽

Christian A. Garcia ◽

Stephen B. Cumming

Keyword(s):

Trailing Edge ◽

Flight Data ◽

Aerodynamic Modeling ◽

Trailing Edge Flaps

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Research on Longitudinal Aerodynamics Modeling Method for Aircraft Stall Based on Wavelet Neural Network from Flight Data

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.602-605.3144 ◽

2014 ◽

Vol 602-605 ◽

pp. 3144-3147

Author(s):

Xu Sheng Gan ◽

Hai Long Gao

Keyword(s):

Neural Network ◽

Wavelet Neural Network ◽

Modeling Method ◽

Flight Data ◽

Aerodynamic Modeling ◽

Aerodynamic Model ◽

Modeling Problem ◽

Modeling Flow

For the aerodynamic modeling problem from measured flight data for aircraft stall, a WNN aerodynamic modeling method is proposed. According to the aerodynamic modeling flow from flight data for aircraft stall, WNN is introduced to establish the aerodynamic model of aircraft for stall phenomenon. Experiment shows that the method can improve the modeling ability of WNN, and is suitable for actual aerodynamic modeling for aircraft stall.

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High-fidelity aerodynamic modeling of an aircraft using OpenFoam – application on the CRJ700

The Aeronautical Journal ◽

10.1017/aer.2021.86 ◽

2021 ◽

pp. 1-22

Author(s):

M. Segui ◽

F.R. Abel ◽

R.M. Botez ◽

A. Ceruti

Keyword(s):

Open Source Software ◽

Absolute Error ◽

Flight Simulator ◽

High Fidelity ◽

Maximum Absolute Error ◽

Flight Data ◽

Aerodynamic Modeling ◽

Aerodynamic Model ◽

Data Source ◽

Source Level

Abstract This study is focused on the development of longitudinal aerodynamic models for steady flight conditions. While several commercial solvers are available for this type of work, we seek to evaluate the accuracy of an open source software. This study aims to verify and demonstrate the accuracy of the OpenFoam solver when it is used on basic computers (32–64GB of RAM and eight cores). A new methodology was developed to show how an aerodynamic model of an aircraft could be designed using OpenFoam software. The mesh and the simulations were designed only using OpenFoam utilities, such as blockMesh, snappyHexMesh, simpleFoam and rhoSimpleFoam. For the methodology illustration, the process was applied to the Bombardier CRJ700 aircraft and simulations were performed for its flight envelope, up to M0.79. Forces and moments obtained with the OpenFoam model were compared with an accurate flight data source (level D flight simulator). Excellent results in data agreement were obtained with a maximum absolute error of 0.0026 for the drag coefficient, thus validating a high-fidelity aerodynamic model for the Bombardier CRJ-700 aircraft.

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