HISTORY ALTHOUGH the present Department of Aeronautics and Fluid Mechanics was created only in 1950, the teaching of Aeronautics in the University goes back to the year 1920, and…
Abstract
HISTORY ALTHOUGH the present Department of Aeronautics and Fluid Mechanics was created only in 1950, the teaching of Aeronautics in the University goes back to the year 1920, and interest in aeronautics begins even further back. One of the pioneers of aviation, Percy S. Pilchcr, was an Assistant in the Department of Naval Architecture in 1892–6. During this time he constructed his first man‐carrying glider.
This paper aims to present the new information about propeller thrust force contribution to airplane longitudinal stability analysis.
Abstract
Purpose
This paper aims to present the new information about propeller thrust force contribution to airplane longitudinal stability analysis.
Design/methodology/approach
The method presented in this paper is empirical, shows how propeller thrust force derivative can be obtained and gives some additional information about misinterpretation of the propeller thrust effects that are present in the current literature.
Findings
New information about propeller thrust force contribution to airplane longitudinal stability analysis has been presented. This information should enable more precise insight in aircraft stability analysis and better understanding of the physical process that occurs during maneuver flight.
Practical implications
The information presented in this paper is new and specific to the propeller aircraft configuration. The methods used here are standard procedure to evaluating propeller thrust force derivative.
Originality/value
The information in this paper presents theoretical results. The method for calculating thrust force contribution to the airplane longitudinal stability is given depending on the propeller type and should enable good engineering results.
Details
Keywords
Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Council, Reports and Technical Memoranda of the United States…
Abstract
Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Council, Reports and Technical Memoranda of the United States National Advisory Committee for Aeronautics and publications of other similar Research Bodies as issued
Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Council, Reports and Technical Memoranda of the United States…
Abstract
Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Council, Reports and Technical Memoranda of the United States National Advisory Committee for Aeronautics and publications of other similar Research Bodies as issued.
Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Council, Reports and Technical Memoranda of the United States…
Abstract
Under this heading are published regularly abstracts of all Reports and Memoranda of the Aeronautical Research Council, Reports and Technical Memoranda of the United States National Advisory Committee for Aeronautics and publications of other similar Research Bodies as issued.
The full text of all the papers presented at an International Conference on Dynamic Stability, held at Northwestern University, Illinois, is reproduced in this volume.
ORIGINS THE Department of Aeronautical Engineer‐ing at The Queen's University was founded primarily to stimulate the flow of local talent into the aircraft industry of Northern…
Abstract
ORIGINS THE Department of Aeronautical Engineer‐ing at The Queen's University was founded primarily to stimulate the flow of local talent into the aircraft industry of Northern Ireland. With the transfer of the whole of the resources of Short Brothers and Harland to Belfast in 1947 and their subsequent development, the aircraft industry had come to represent a considerable fraction of the engineering effort of the Province. It was thus to be expected that the only University in Northern Ireland should concern itself with the special needs of this exacting branch of engineering. The University had long had a School of Engineering forming part of a Faculty of Applied Science and Technology. The engineering disciplines were civil, mechanical and electrical, and the mechanical courses in particular had been adapted to some extent to meet aeronautical needs. But it was only natural that there remained a demand for a separate department, providing a degree course devised specifically for aeronautical engineers. In the event the Department of Aeronautical Engineering was established in 1956, after close consultation with Short Brothers and Harland, who have given it both generous support and willing co‐operation ever since.
This book should serve as an admirable introductory text: it is very well written and organized and the approach adopted is sound. Nowadays, when a book on servomechanism theory…
Abstract
This book should serve as an admirable introductory text: it is very well written and organized and the approach adopted is sound. Nowadays, when a book on servomechanism theory appears almost monthly, one has misgivings at the publication of yet another one, particularly as many of the American texts are practically indistinguishable from each other. However, the book under review has a character of its own, which would make it form a suitable basis for a university course.
Jian-Ming Fu, Hai-Min Tang and Hong-Quan Chen
The purpose of this paper is to develop a new approach for rapid computation of subsonic and low-transonic rotary derivatives with the available steady solutions obtained by Euler…
Abstract
Purpose
The purpose of this paper is to develop a new approach for rapid computation of subsonic and low-transonic rotary derivatives with the available steady solutions obtained by Euler computational fluid dynamics (CFD) codes.
Design/methodology/approach
The approach is achieved by the perturbation on the steady-state pressure of Euler CFD codes. The resulting perturbation relation is established at a reference Mach number between rotary derivatives and normal velocity on surface due to angular velocity. The solution of the reference Mach number is generated technically by Prandtl–Glauert compressibility correction based on any Mach number of interest under the assumption of simple strip theory. Rotary derivatives of any Mach number of interest are then inversely predicted by the Prandtl–Glauert rule based on the reference Mach number aforementioned.
Findings
The resulting method has been verified for three typical different cases of the Basic Finner Reference Projectile, the Standard Dynamics Model Aircraft and the Orion Crew Module. In comparison with the original perturbation method, the performance at subsonic and low-transonic Mach numbers has significantly improved with satisfactory accuracy for most design efforts.
Originality/value
The approach presented is verified to be an efficient way for computation of subsonic and low-transonic rotary derivatives, which are performed almost at the same time as an accounting solution of steady Euler equations.
Details
Keywords
Leonidas D. Evangelou, Andrew Self and John Allen
The increasing demand on high performance fighter aircraft has introduced areas of concern associated with the handling qualities, control and safety at high angles of incidence…
Abstract
The increasing demand on high performance fighter aircraft has introduced areas of concern associated with the handling qualities, control and safety at high angles of incidence. Pilots are limiting combat effectiveness by cautiously avoiding hazardous regions of the flight envelope. This paper presents the results of the work undertaken in analysing the F‐16 aircraft’s handling characteristics during the departure condition. In‐flight experience shows that there are two types of F‐16 control problems when flying at high angles of attack: the “pitch departures” and the resulting “deep stall trim”. Avoidance of the departure requires the aeroplane to have sufficient nose‐down pitch and roll control moment. This paper investigates departure condition during high angles of attack and suggests a method of recovery.