Computational aerodynamics analysis of a light sport aircraft: Compliance study for stall speed and longitudinal stability certification requirements

Piedra, Saúl; Martinez, Edward; Escalante-Velazquez, C.A.; Jiménez, Salomón M.A.

doi:10.1016/j.ast.2018.09.016

Cited by 16 publications

(7 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The drag coefficient is used to denote the rearward force that disturbs the airflow of an airfoil 1. As per the result mentioned in Table 4, a stall occurs at a 14° AOA, and the maximum lift occurs at a 12° AOA (Piedra et al, 2018;Ramji et al, 2016).…”

Section: Cfd Resultssupporting

confidence: 64%

Energy Industry and Industrial Design (Innovations in Energy Utilization and Equipment Design)

2024

JST

View full text Add to dashboard Cite

This study represents the aerodynamic design of an Unmanned aerial vehicle intended for surveillance or agriculture with a maximum take weight of 125 kg. Weight estimation and constraint analysis were done based on the Mission profile. Design of Computer-Aided Design (CAD) models were generated for three different configurations using CATIA V5R20 as a high wing, mid-wing, and low wing. Flow analysis was done for the above configurations at various angles of attack. ANSYS 15 was used for the flow Analysis. A Tetrahedron element meshed the model with the minimum required orthogonal quality. Five microns were given to the initial layer height of the prism mesh. Spalart Allmaras model is used as the Turbulence model in the solver. The aerodynamic characteristics of the above configuration obtained from Computational Fluid Dynamics (CFD) results were compared with the DATCOM program and validated with the wind tunnel experimental test data. The open-circuited suction-type Subsonic wind tunnel was employed for the test. The aerodynamic properties for the angle of attack in the range of -2° to 14° angle of attack are calculated using a six-component balance.The study aims to find the Unmanned Aerial Vehicle (UAV) configuration based on the aerodynamic characteristics obtained from the CFD and DATCOM results. High-wing UAVs have better aerodynamic efficiency than the other two configurations.

show abstract

Section: Cfd Resultssupporting

confidence: 64%

Energy Industry and Industrial Design (Innovations in Energy Utilization and Equipment Design)

2024

JST

View full text Add to dashboard Cite

show abstract

“…Moreover, numerical methods are also used to estimate, identify or optimize aerodynamic parameters [12][13][14][15][16][17]. Piedra et al verified the flight requirements of light sport aircraft numerically with the Vortex Lattice Method and Computational Fluid Dynamics simulations concluded [18]. Saderla et al carried out an online aerodynamic parameter estimation method of UAV, which provide high-accuracy results compared with other methods [2,19].…”

Section: Introductionmentioning

confidence: 99%

Research of a novel aerodynamic evaluation method for fixed-wing UAV

Wu,

Liu,

Wang

et al. 2023

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

The aerodynamic parameters of unmanned aerial vehicles (UAVs) play an important role in the newly designed drone. For the purpose of the real-time measurement of the aerodynamic performance parameters of the UAV in flight status, based on the self-development connected-wing configuration airplane, a novel airborne aerodynamics test scheme is researched and verified in this work. The findings of this study indicate that the effectiveness of numerical calculations can be verified by comparison with both results of the numerical simulation and airborne flight test in the same conditions. The newly designed UAV equipped with this test system in the future, not only achieves quick and reliable results of aerodynamic performance and powered system efficiency but also can save the expense of wind tunnel experiments, which is of high potential to the UAV application.

show abstract

“…It affects the fuel consumption of the aircraft and its flight properties. The drag force can be described by the equation ( 2) [4,6].…”

Section: Introductionmentioning

confidence: 99%

Determination of the operational parameters values for Airbus A300-600ST Beluga aircraft on the basis of CFD tests

Nowacki,

Olejniczak

2022

MATEC Web Conf.

View full text Add to dashboard Cite

The article presents a method for estimating the values of basic operational and aerodynamic parameters of an aircraft. It contains a multistage analysis of CFD test results for the Beluga Airbus A300-600ST model. The first step of the method is to determine the values of aerodynamic parameters such as lift coefficient, drag coefficient, lift force and drag force in specific flight conditions. A comparative analysis of the coefficients of lift and drag force depending on the angle of attack of the aircraft allowed the estimation of the optimal angle of attack of the Airbus A300-600ST Beluga. In the next step, the operational values and the maximum flight ceiling of the aircraft were determined. For this purpose, the results of CFD simulation tests for the optimal angle of attack of the aircraft were used. This article allowed determining the characteristics of the components of aerodynamic force of an airplane depending on the angle of attack, flight altitude and flight speed, determining the optimal angle of attack of the aircraft and calculation of the optimal and maximum flight ceiling values of the Airbus A300-600ST Beluga.

show abstract

Computational aerodynamics analysis of a light sport aircraft: Compliance study for stall speed and longitudinal stability certification requirements

Cited by 16 publications

References 9 publications

Energy Industry and Industrial Design (Innovations in Energy Utilization and Equipment Design)

Energy Industry and Industrial Design (Innovations in Energy Utilization and Equipment Design)

Research of a novel aerodynamic evaluation method for fixed-wing UAV

Determination of the operational parameters values for Airbus A300-600ST Beluga aircraft on the basis of CFD tests

Contact Info

Product

Resources

About