Experimental Studies on Control of Delta Wing Aerodynamics

Jinjun Wang; Yan Xu

doi:10.2514/1.9101

Experimental Studies on Control of Delta Wing Aerodynamics

Jinjun Wang^*
, Yan Xu

^*Corresponding author for this work

School of Aeronautic Science and Engineering

Research output: Contribution to journal › Article › peer-review

2 Scopus citations

Abstract

The effects of an apex flap on aerodynamic characteristics of delta wings were demonstrated. The experiments were conducted in a wind tunnels with a test section of 1.02×0.76 m. A six-component balance was employed in the wind tunnel to measure forces and moments of the wings. It was observed that when the flap was deflected downwards, the effective angle of attack decreases for the entire delta wing.

Original language	English
Pages (from-to)	403-405
Number of pages	3
Journal	AIAA Journal
Volume	42
Issue number	2
DOIs	https://doi.org/10.2514/1.9101
State	Published - Feb 2004

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title = "Experimental Studies on Control of Delta Wing Aerodynamics",

abstract = "The effects of an apex flap on aerodynamic characteristics of delta wings were demonstrated. The experiments were conducted in a wind tunnels with a test section of 1.02×0.76 m. A six-component balance was employed in the wind tunnel to measure forces and moments of the wings. It was observed that when the flap was deflected downwards, the effective angle of attack decreases for the entire delta wing.",

author = "Jinjun Wang and Yan Xu",

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T1 - Experimental Studies on Control of Delta Wing Aerodynamics

AU - Wang, Jinjun

AU - Xu, Yan

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N2 - The effects of an apex flap on aerodynamic characteristics of delta wings were demonstrated. The experiments were conducted in a wind tunnels with a test section of 1.02×0.76 m. A six-component balance was employed in the wind tunnel to measure forces and moments of the wings. It was observed that when the flap was deflected downwards, the effective angle of attack decreases for the entire delta wing.

AB - The effects of an apex flap on aerodynamic characteristics of delta wings were demonstrated. The experiments were conducted in a wind tunnels with a test section of 1.02×0.76 m. A six-component balance was employed in the wind tunnel to measure forces and moments of the wings. It was observed that when the flap was deflected downwards, the effective angle of attack decreases for the entire delta wing.

UR - https://www.scopus.com/pages/publications/1542501639

U2 - 10.2514/1.9101

DO - 10.2514/1.9101

M3 - 文章

AN - SCOPUS:1542501639

SN - 0001-1452

VL - 42

SP - 403

EP - 405

JO - AIAA Journal

JF - AIAA Journal

IS - 2

ER -

Experimental Studies on Control of Delta Wing Aerodynamics

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