Computational Flight Testing
DOWNLOAD
Download Computational Flight Testing PDF/ePub or read online books in Mobi eBooks. Click Download or Read Online button to get Computational Flight Testing book now. This website allows unlimited access to, at the time of writing, more than 1.5 million titles, including hundreds of thousands of titles in various foreign languages. If the content not found or just blank you must refresh this page
Computational Flight Testing
DOWNLOAD
Author : Norbert Kroll
language : en
Publisher: Springer Science & Business Media
Release Date : 2013-06-18
Computational Flight Testing written by Norbert Kroll and has been published by Springer Science & Business Media this book supported file pdf, txt, epub, kindle and other format this book has been release on 2013-06-18 with Technology & Engineering categories.
This book reports on the German research initiative ComFliTe (Computational Flight Testing), the main goal of which was to enhance the capabilities of and tools for numerical simulation in flight physics to support future aircraft design and development. The initiative was coordinated by the German Aerospace Center (DLR) and promoted collaboration between the aircraft industry and academia. Activities focused on improving physical modeling for separated flows, developing advanced numerical algorithms for series computations and sensitivity predictions, as well as surrogate and reduced order modeling for aero data production and developing robust fluid-, structure- and flight mechanics coupling procedures. Further topics included more efficient handling of aircraft control surfaces and improving simulation methods for maneuvers, such as gust encounter. The important results of this three-year initiative were presented during the ComFliTe closing symposium, which took place at the DLR in Braunschweig, Germany, on 11-12 June 2012. Computational Flight Testing addresses both students and researchers in the areas of mathematics, numerical simulation and optimization methods, as well as professionals in aircraft design working at the forefront of their field.
Advanced Uav Aerodynamics Flight Stability And Control
DOWNLOAD
Author : Pascual Marqués
language : en
Publisher: John Wiley & Sons
Release Date : 2017-07-11
Advanced Uav Aerodynamics Flight Stability And Control written by Pascual Marqués and has been published by John Wiley & Sons this book supported file pdf, txt, epub, kindle and other format this book has been release on 2017-07-11 with Technology & Engineering categories.
Comprehensively covers emerging aerospace technologies Advanced UAV aerodynamics, flight stability and control: Novel concepts, theory and applications presents emerging aerospace technologies in the rapidly growing field of unmanned aircraft engineering. Leading scientists, researchers and inventors describe the findings and innovations accomplished in current research programs and industry applications throughout the world. Topics included cover a wide range of new aerodynamics concepts and their applications for real world fixed-wing (airplanes), rotary wing (helicopter) and quad-rotor aircraft. The book begins with two introductory chapters that address fundamental principles of aerodynamics and flight stability and form a knowledge base for the student of Aerospace Engineering. The book then covers aerodynamics of fixed wing, rotary wing and hybrid unmanned aircraft, before introducing aspects of aircraft flight stability and control. Key features: Sound technical level and inclusion of high-quality experimental and numerical data. Direct application of the aerodynamic technologies and flight stability and control principles described in the book in the development of real-world novel unmanned aircraft concepts. Written by world-class academics, engineers, researchers and inventors from prestigious institutions and industry. The book provides up-to-date information in the field of Aerospace Engineering for university students and lecturers, aerodynamics researchers, aerospace engineers, aircraft designers and manufacturers.
Computational Flight Dynamics
DOWNLOAD
Author : Malcolm J. Abzug
language : en
Publisher: AIAA (American Institute of Aeronautics & Astronautics)
Release Date : 1998
Computational Flight Dynamics written by Malcolm J. Abzug and has been published by AIAA (American Institute of Aeronautics & Astronautics) this book supported file pdf, txt, epub, kindle and other format this book has been release on 1998 with Computers categories.
Diskette contains: FORTRAN source programs.
Applied Computational Aerodynamics
DOWNLOAD
Author : Russell M. Cummings
language : en
Publisher: Cambridge University Press
Release Date : 2015-04-27
Applied Computational Aerodynamics written by Russell M. Cummings and has been published by Cambridge University Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 2015-04-27 with Mathematics categories.
This book covers the application of computational fluid dynamics from low-speed to high-speed flows, especially for use in aerospace applications.
Flight Testing
DOWNLOAD
Author : Steffen Haakon Schrader
language : en
Publisher: Springer Nature
Release Date : 2023-03-06
Flight Testing written by Steffen Haakon Schrader and has been published by Springer Nature this book supported file pdf, txt, epub, kindle and other format this book has been release on 2023-03-06 with Technology & Engineering categories.
As spinning is still involved in around 60% of all aircraft accidents (BFU, 1985 and Belcastro, 2009), this aerodynamic phenomenon is still not fully understood. As U.S. and European Certification Specifications do not require recoveries from fully developed spins of Normal Category aeroplanes, certification test flights will not discover aeroplane mass and centre of gravity combinations which may result in unrecoverable spins. This book aims to contribute to a better understanding of the spin phenomenon through investigating the spin regime for normal, utility and aerobatic aircraft, and to explain what happens to the aircraft in terms of the aerodynamics, flight mechanics and the aircraft stability. The approach used is to vary the main geometric parameters such as the centre of gravity position and the aeroplane’s mass across the flight envelope, and to investigate the subsequent effect on the main spin characteristic parameters such as the angle of attack, pitch angle, sideslip angle, rotational rates, and recovery time. First of all, a literature review sums up the range of technical aspects that affect the problem of spinning. It reviews the experimental measurement techniques used, theoretical methods developed and flight test results obtained by previous researchers. The published results have been studied to extract the effect on spinning of aircraft geometry, control surface effectiveness, flight operational parameters and atmospheric effects. Consideration is also made of the influence on human performance of spinning, the current spin regulations and the available training material for pilots. A conventional-geometry, single-engine low-wing aeroplane, the basic trainer Fuji FA-200-160, has been instrumented with a proven digital flight measurement system and 27 spins have been systematically conducted inside and outside the certified flight envelope. The accuracy of the flight measurements is ensured through effective calibration, and the choice of sensors has varied through the study, with earlier sensors suffering from more drift than the current sensors (Belcastro, 2009 and Schrader, 2013). In-flight parameter data collected includes left and right wing α and β-angles, roll-pitch-yaw angles and corresponding rates, all control surface deflections, vertical speeds, altitude losses and the aeroplane’s accelerations in all three directions. Such data have been statistically analysed. The pitch behaviour has been mathematically modelled on the basis of the gathered flight test data. Nine observations have been proposed. These mainly cover the effects of centre of gravity and aircraft mass variations on spin characteristic behaviour. They have all been proven as true through the results of this thesis. The final observation concerns the generalisation of the Fuji results, to the spin behaviour of other aircraft in the same category. These observations can be used to improve flight test programmes, aircraft design processes, flight training materials and hence contribute strongly to better flight safety.
Flight Test Identification And Simulation Of A Uh 60a Helicopter And Slung Load
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 2001
Flight Test Identification And Simulation Of A Uh 60a Helicopter And Slung Load written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2001 with categories.
Helicopter slung-load operations are common in both military and civil contexts. Helicopters and loads are often qualified for these operations by means of flight tests, which can be expensive and time consuming. There is significant potential to reduce such costs both through revisions in flight-test methods and by using validated simulation models. To these ends, flight tests were conducted at Moffett Field to demonstrate the identification of key dynamic parameters during flight tests (aircraft stability margins and handling-qualities parameters, and load pendulum stability), and to accumulate a data base for simulation development and validation. The test aircraft was a UH-60A Black Hawk, and the primary test load was an instrumented 8- by 6- by 6-ft cargo container. Tests were focused on the lateral and longitudinal axes, which are the axes most affected by the load pendulum modes in the frequency range of interest for handling qualities; tests were conducted at airspeeds from hover to 80 knots. Using telemetered data, the dynamic parameters were evaluated in near real time after each test airspeed and before clearing the aircraft to the next test point. These computations were completed in under 1 min. A simulation model was implemented by integrating an advanced model of the UH-60A aerodynamics, dynamic equations for the two-body slung-load system, and load static aerodynamics obtained from wind-tunnel measurements. Comparisons with flight data for the helicopter alone and with a slung load showed good overall agreement for all parameters and test points; however, unmodeled secondary dynamic losses around 2 Hz were found in the helicopter model and they resulted in conservative stability margin estimates.
Flight Wind Tunnel And Computational Fluid Dynamics Comparison For Cranked Arrow Wing F 16xl 1 At Subsonic And Transonic Speeds
DOWNLOAD
Author : John E. Lamar
language : en
Publisher:
Release Date : 2001
Flight Wind Tunnel And Computational Fluid Dynamics Comparison For Cranked Arrow Wing F 16xl 1 At Subsonic And Transonic Speeds written by John E. Lamar and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2001 with Airplanes categories.
Geometrical, flight, computational fluid dynamics (CFD), and wind-tunnel studies for the F-16XL-1 airplane are summarized over a wide range of test conditions. Details are as follows: (1) For geometry, the upper surface of the airplane and the numerical surface description compare reasonably well. (2) For flight, CFD, and wind-tunnel surface pressures, the comparisons are generally good at low angles of attack at both subsonic and transonic speeds; however, local differences are present. In addition, the shock location at transonic speeds from wind-tunnel presure contours is near the aileron hinge line and generally is in correlative agreement with flight results.
Evolving Computational Capability For Ship Hydrodynamics
DOWNLOAD
Author : Joseph J. Gorski
language : en
Publisher:
Release Date : 2004
Evolving Computational Capability For Ship Hydrodynamics written by Joseph J. Gorski and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2004 with Hydrodynamics categories.
The ability to obtain flow field predictions of surface ships with Reynolds Averaged Navier-Stokes (RANS) codes has improved tremendously in the last few years. This has been a result of improvements in experience, RANS codes in general, and computer capacity. In particular, the move to parallel processing has been a major catalyst for the recent improvements and a threshold of the usefulness of RANS may well have been crossed. This is particularly significant at a time the U.S. Navy is attempting to move to high-speed ships and more operations in the littorals, both of which are driving ship designs well outside of the traditional experience and experimental data bases. A discussion of where RANS computations may be able to significantly influence the current design and analysis process for surface ships is discussed. Specific areas include: hull flow field and resistance, propulsor inflow, waterjet inlets, bilge keel and appendage alignment, roll motions, maneuvering forces, and scale effects. A number of examples are given for various configurations including: Athena fitted with waterjets, AWJ-21, CG-47, DDG-51, an early DD(X) concept, an aircraft carrier, and Sea Shadow.
Applied Computational Aerodynamics
DOWNLOAD
Author : P. A. Henne
language : en
Publisher: AIAA
Release Date : 1990
Applied Computational Aerodynamics written by P. A. Henne and has been published by AIAA this book supported file pdf, txt, epub, kindle and other format this book has been release on 1990 with Aerodynamics categories.
Nasa Reference Publication
DOWNLOAD
Author :
language : en
Publisher:
Release Date : 1977
Nasa Reference Publication written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1977 with Astronautics categories.