Trend in Engineering at the University of Washington Newsletter
Author :
Publisher :
Page : 616 pages
File Size : 35,47 MB
Release : 1965
Category : Engineering
ISBN :
Lateral Stability of an F-100A Airplane
Author : Norman E. Gowin
Publisher :
Page : 82 pages
File Size : 33,83 MB
Release : 1957
Category : Airplanes
ISBN :
Book Description
A Study of the Use of Experimental Stability Derivatives in the Calculation of the Lateral Disturbed Motions of a Swept-wing Airplane and Comparison with Flight Results
Author : John D. Bird
Publisher :
Page : 88 pages
File Size : 12,98 MB
Release : 1950
Category : Aerodynamics
ISBN :
Book Description
Experimentally determined lateral-stability derivatives of a swept-wing airplane are presented to show effects of slots, flaps, propeller, and ventral fins and are sued in calculations of a number of lateral disturbed motions. The calculated motions are compared with those obtained in flight tests to determine the applicability of the experimental stability derivatives . The effects of nonlinearity of some of the aerodynamic forces with sideslip are shown by a few supplemental calculations.
Stability and Control
Author : Courtland D. Perkins
Publisher : Elsevier
Page : 520 pages
File Size : 37,53 MB
Release : 2014-05-12
Category : Technology & Engineering
ISBN : 1483222330
Book Description
Flight Testing, Volume II: Stability and Control focuses on the development of adequate flight test techniques for the appraisal of stability and control characteristics and flying qualities of airplanes. This book discusses the flying quality requirements, longitudinal motions, and flight determination of stick-fixed neutral points. The determination of aerodynamic parameters from steady maneuvering, desirable control characteristics in steady flight, and various forms of lateral control surfaces are also elaborated. This publication likewise covers the measurement of maximum lift coefficient, emergency anti-spin devices, and concept of the altitude-Mach number flight envelope. This volume is recommended for design, development or research engineers, test pilots, and instrumentation personnel interested in airplane stability and control.
Determination of the Stability and Control Derivatives of the NASA F/A-18 Harv Using Flight Data
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 124 pages
File Size : 20,14 MB
Release : 2018-07-17
Category :
ISBN : 9781723022715
Book Description
This report documents the research conducted for the NASA-Ames Cooperative Agreement No. NCC 2-759 with West Virginia University. A complete set of the stability and control derivatives for varying angles of attack from 10 deg to 60 deg were estimated from flight data of the NASA F/A-18 HARV. The data were analyzed with the use of the pEst software which implements the output-error method of parameter estimation. Discussions of the aircraft equations of motion, parameter estimation process, design of flight test maneuvers, and formulation of the mathematical model are presented. The added effects of the thrust vectoring and single surface excitation systems are also addressed. The results of the longitudinal and lateral directional derivative estimates at varying angles of attack are presented and compared to results from previous analyses. The results indicate a significant improvement due to the independent control surface deflections induced by the single surface excitation system, and at the same time, a need for additional flight data especially at higher angles of attack. Napolitano, Marcello R. and Spagnuolo, Joelle M. Unspecified Center AIRCRAFT CONTROL; AIRCRAFT STABILITY; ANGLE OF ATTACK; F-18 AIRCRAFT; FLIGHT TESTS; LATERAL STABILITY; LONGITUDINAL STABILITY; MAXIMUM LIKELIHOOD ESTIMATES; PARAMETER IDENTIFICATION; AIRCRAFT MANEUVERS; CONTROL SURFACES; EQUATIONS OF MOTION; MATHEMATICAL MODELS; THRUST VECTOR CONTROL...
Determination of the Longitudinal and Lateral Stability Derivatives of the Stinson L-5 Airplane From Steady State Flight Tests
Author : Carl N Kurtz William E Saldin
Publisher : Hassell Street Press
Page : 140 pages
File Size : 48,31 MB
Release : 2021-09-09
Category :
ISBN : 9781014858665
Book Description
This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. To ensure a quality reading experience, this work has been proofread and republished using a format that seamlessly blends the original graphical elements with text in an easy-to-read typeface. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.
Experimental Determination of the Effect of Negative Dihedral on Lateral Stability and Control Characteristics at High Lift Coefficients
Author : Marion O. McKinney
Publisher :
Page : 34 pages
File Size : 25,65 MB
Release : 1946
Category : Aerodynamics
ISBN :
Book Description
Summary: The effects of negative dihedral on lateral stability and control characteristics at high lift coefficients have been determined by flight tests of a model in the Langley free-flight tunnel. The geometric dihedral angle of the model wing was varied from 0° to -20° and the vertical-tail area, from 0 to 35 percent of the wing area. The model was flown with various combinations of dihedral angle and vertical-tail area at lift coefficients of 1.0, 1.4, and 1.8. As the effective dihedral was decreased from 0° to -15°, the model became increasingly difficult to fly. With an effective dihedral of -15° the flying characteristics were considered to be dangerous because, when there was only a slight lag in the application of corrective control following a disturbance, the unstable moments resulting from spiral instability became sufficiently large to overpower the moments of the controls so that return to straight flight was impossible. Inasmuch as full-scale airplanes because of their greater size will diverge at a slower rate than free-flight models, the amount of negative effective dihedral that would constitute a dangerous condition is expected to be greater for full-scale airplanes.
The Effects on Dynamic Lateral Stability and Control of Large Artificial Variations in the Rotary Stability Derivatives
Author : Robert O. Schade
Publisher :
Page : 66 pages
File Size : 34,44 MB
Release : 1952
Category : Aeronautics
ISBN :
Book Description
The results of an experimental and theoretical investigation of the effects of large artificial variations of four rotary stability derivatives on the dynamic lateral stability and control of a 45 degree sweptback-wing airplane model are presented. The experimental results are presented mainly in the form of flight ratings for stability, control, and general flight behavior. Calculations of period and damping and of the response of rolling and yawing disturbances are also presented.
Stability and Control Estimation Flight Test Results for the SR-71 Aircraft With Externally Mounted Experiments
Author : Timothy R. Moes
Publisher :
Page : 98 pages
File Size : 37,80 MB
Release : 2002
Category : Airplanes
ISBN :
Book Description
A maximum-likelihood output-error parameter estimation technique is used to obtain stability and control derivatives for the NASA Dryden Flight Research Center SR-71A airplane and for configurations that include experiments externally mounted to the top of the fuselage. This research is being done as part of the envelope clearance for the new experiment configurations. Flight data are obtained at speeds ranging from Mach 0.4 to Mach 3.0, with an extensive amount of test points at approximately Mach 1.0. Pilot-input pitch and yaw-roll doublets are used to obtain the data. This report defines the parameter estimation technique used, presents stability and control derivative results, and compares the derivatives for the three configurations tested. The experimental configurations studied generally show acceptable stability, control, trim, and handling qualities throughout the Mach regimes tested.
The Effect of Lateral Area on the Lateral Stability and Control Characteristics of an Airplane as Determined by Tests of a Model in the Langley Free-flight Tunnel
Author : Hubert M. Drake
Publisher :
Page : 32 pages
File Size : 32,57 MB
Release : 1946
Category : Aerodynamics
ISBN :
Book Description
The effects of large variations of lateral area on the lateral stability and control characteristics of a free-flying model when ailerons are used as the principal control have been determined by flight tests in the Langley free-flight tunnel. The effects of the lateral-force parameter (rate of change of lateral-force coefficient with angle of sideslip) were investigated for a wide range of values of the directional-stability parameter (rate of change of yawing-moment coefficient with angle of sideslip) and the rotary-damping-in-yaw parameter (rate of change of yawing-moment coefficient with yawing angular velocity).
