An experimental study of the relationship between forces and moments and vortex breakdown on a pitching delta wing

Wind-tunnel experiments were performed to study the complex flow mechanisms on a 70-deg. sharp leading-edge delta wing model at both static and dynamic conditions at a Reynolds number of 1.43 $\times$ 10$\sp6$. Large amplitude oscillatory motions were produced by sinusoidally pitching the model over a range of reduced frequencies. Ramp motions were obtained using an initial sinusoidal increase in angle of attack and hold. Aerodynamic forces and moments were obtained from a six-component internal strain-gauge balance. In addition, smoke flow visualization was conducted to study the development, and breakdown of the leading-edge vortices under static, dynamic, and ramp conditions. The visualization experiment was performed at a Reynolds number of 0.16 $\times$ 10$\sp6$.

Name thesis:degree_name

Ph.D.

Level thesis:degree_level

Dissertation

Discipline thesis:degree_discipline

Aerospace Engineering

Grantor

University of Illinois at Urbana-Champaign

Year dc:date

2011

Author dc:creator

• Soltani, Mohammad Reza

Contributors dc:contributor

• Bragg, Michael B.

• Engineering, Aerospace

Statement dc:rights

• Copyright 1992 Soltani, Mohammad Reza

Language dc:language

eng

Identifier

AAI9215885
(UMI)AAI9215885

OAI identifier oai:identifier

oai:www.ideals.illinois.edu:2142/22695