Computation of the Aerodynamic Characteristics of a Subsonic Transport

Troeger, Lillianne P.; Selby, G. V.

doi:10.2514/2.2306

Cited by 2 publications

(1 citation statement)

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“…The advantage of the panel methods is that they only require a surface panel representation of the geometry, instead of a complete flowfield used by finite difference, finite element and volume element methods. 10 The present work has as objective to do a complete aerodynamic analysis of the ANCE. Panel method PAN AIR is used to compute the inviscid flowfield.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Analysis of the Unmanned Aerial Vehicle for Ecological Conservation

Boschetti¹,

Cárdenas²,

Amerio³

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The present work has as objective to do a complete aerodynamic analysis of the Unmanned Aerial Vehicle for Ecological Conservation. The panel method code PAN AIR is used to compute the inviscid flowfield. The viscous effects in drag are estimated by the classic Hoerner method, and the maximum lift coefficient via the classic Valarezo and Chin method. The numerical aerodynamic forces of the complete airplane are compared to experimental data for validation. The spanload and wing pressure distribution are estimated for four configurations: wing, wing-body, wing-body-tail, and wing-body-tail with wing twist. The sources of induced drag for all configurations are achieved graphically via Trefftz plane. All the data were estimated at cruise flight, Reynolds number equal to 1.413×10 6 and Mach 0.15.

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Section: Introductionmentioning

confidence: 99%