Potential-flow Inflow Model Including Wake Distortion and Contraction

<p>Dynamic wake models have been used in real-time flight simulations for over thirty years. The models have evolved from the earliest, three-degree-of-freedom models (derived from momentum theory) to full finite-state models derived from potential flow theory by a formal Galerkin method. These models are widely used in industry, but still have some drawbacks that need to be remedied. These drawbacks include: 1.) lack of good convergence both on the disk and off the disk (one can use one or the other but not both), 2.) poor results downstream in the limit of shallow skew angles, 3.) poor convergence inside of the rotor wake, 4.) lack of the effects of wake curvature and wake contraction, and 5.) lack of other important nonlinearities. This thesis uses applications of adjoint theorem, a special change of variable and effective introduction of solution blending to overcome these obstacles. The resultant model is well-behaved in all regimes and is applicable to use in realistic problems of flight simulation, even when only a few states are allowed.</p>

Name thesis:degree_name

Doctor of Philosophy (PhD)

Level thesis:degree_level

Dissertation

Discipline thesis:degree_discipline

Mechanical Engineering & Materials Science

Year dc:date.available

2015

Author dc:creator

• Huang, Jianzhe

Contributors dc:contributor

• David Peters
• Kenneth Jerina, Swami Karunamoorthy, Mark Meacham, Shankar Sastry, Heinz Schaettler

• finite state inflow model
• helicopter
• nonlinear
• wake skew
• Engineering

Statement dc:rights

• I have not registered my thesis with the U.S. Copyright Office, and do not intend to.

Language dc:language

English (en)

Identifier

https://openscholarship.wustl.edu/eng_etds/101

OAI identifier oai:identifier

oai:openscholarship.wustl.edu:eng_etds-1102