| Parallel Unstructured Mesh Adaptation for Transient Moving Body and Aeropropulsive Applications |
2004 |
12 pages |
| Authors:
P. A. Cavallo; N. Sinha; G. M. Feldman; COMBUSTION RESEARCH AND FLOW TECHNOLOGY INC PIPERSVILLE PA
|
 | Adaptive, unstructured grid methods, in which the mesh is allowed to deform, and grid quality subsequently restored through localized coarsening and refinement, offer the potential of a more rapid, straightforward approach to generalized moving body problems. Automation of this mesh movement and quality correction strategy requires a close coupling with the flow solution process. With parallel simulations now common, parallel coarsening and refinement methods for moving meshes are needed. In ... |
|
| The DTIC Review: Advanced Space Transportation (CD-ROM) |
2004 |
|
| Authors:
Phyllis Levine; Candy Parker; DEFENSE TECHNICAL INFORMATION CENTER FORT BELVOIR VA
|
 | ELECTRONIC FILE CHARACTERISTICS: 120 files; HyperText Markup Language (.HTML), Adobe Acrobat (.PDF), MS Word (.DOC), and QuickTime Movie (.MOV). PHYSICAL DESCRIPTION: 1 CD-ROM; 4 3/4 in.; 230 MB. SYSTEMS DETAIL NOTE: ABSTRACT: The concept of hypersonic flight is not a new one. NASA has been building a hypersonic research program dating back to the 1950's. The new effort takes advantage of resources and manufacturing capabilities unavailable 30 years ago. Within ... |
|
| Limit Cycle Oscillations and Nonlinear Aeroelastic Wing Response: Reduced Order Aerodynamic Models |
31 DEC 2003 |
24 pages |
| Authors:
Earl H. Dowell; Kenneth C. Hall; DUKE UNIV DURHAM NC DEPT OF MECHANICALENGINEERING AND MATERIALS SCIENCE
|
| To develop an eigenmode or proper orthogonal decomposition (POD) modal representation of unsteady aerodynamic forces on oscillating flexible airfoils and wings and thereby reduce the size and cost of mathematical models for such forces by several orders of magnitude. Building on earlier work for two-dimensional inviscid flows, we seek to extend our models to. three- dimensional flows with viscous effects included. Also a novel form of the harmonic balance (HB) ... |
|
| Computational Algorithms for High-Fidelity Multidisciplinary Design of Complex Aerospace Systems |
31 DEC 2003 |
21 pages |
| Authors:
Anthony Jameson; Juan J. Alonso; STANFORD UNIV CA DEPT OF AERONAUTICS AND ASTRONAUTICS
|
| During the first year, with the help of S. Nadarajah, a number of different studies on the suitability of the continuous and discrete adjoint formulations for design using the viscous Reynolds-Averaged Navier-Stokes equations were carried out. Our conclusion is that the implementation of the continuous formulation is more straightforward and leaves more freedom on the choices of discretization of the adjoint equations. We found, however, that the discrete adjoint approach ... |
|
| Investigation of the Orthogonal Blade-Vortex Interaction |
01 DEC 2003 |
44 pages |
| Authors:
J. M. Early; R. B. Green; F. N. Coton; GLASGOW UNIV (UNITED KINGDOM) DEPT OF AEROSPACE ENGINEERING
|
| A Stereoscopic Particle Image Velocimetry (SPIV) system was developed and applied to measurements of the Orthogonal Blade-Vortex Interaction (BVI) in a wind tunnel. Measurements of the isolated vortex showed that the SPIV system could resolve the jet velocity profile within the vortex core to a reasonable accuracy, and views of the vortex from different sides of the wind tunnel showed similar velocity profiles. For the BVI measurements the SPIV system ... |
|
| Angular Rate Estimation by Multiplicative Kalman Filtering Techniques |
DEC 2003 |
68 pages |
| Authors:
Vincent C. Watson; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| Spacecraft attitude estimation and pointing accuracy have always been limited by imperfect sensors. The rate gyroscope is one of the most critical instruments used in spacecraft attitude estimation and unfortunately historical trends show this instrument degrades significantly with time. Degraded rate gyroscopes have impacted the missions for several NASA and ESA spacecraft, including the Hubble Telescope. A possible solution to this problem is using a mathematically modeled dynamic gyroscope in ... |
|
| An Investigation Relating Longitudinal Pilot-Induced Oscillation Tendency Ratings to Describing Function Predictions for Rate-Limited Actuators (Project MAX GAP) |
DEC 2003 |
135 pages |
| Authors:
Joel Witte; Svend Monson; Thomas Washington; Kris Cowart; Rich Salasovich; AIR FORCE FLIGHT TEST CENTER EDWARDS AFB CA
|
| This report presents the results of Project MAX QAP, a method of predicting pilot induced oscillations (PIO) caused by actuator rate limiting. The overall test objective was to correlate, if possible, Pilot-induced Oscillation Tendency Ratings with a new preflight calculation called the Gap Criterion. The Air Force Institute of Technology, Engineering Department (AFIT/ ENY) requested this testing. The USAF Test Pilot School (TPS), Class 03A, conducted 8 flight test totaling ... |
|
| Optical Air Flow Measurements in Flight (Mesures optiques de l'ecoulement aerodynamique en vol) |
DEC 2003 |
|
| Authors:
R. K. Bogue; H. W. Jentink; NATO RESEARCH AND TECHNOLOGY ORGANIZATION NEUILLY-SUR-SEINE (FRANCE)
|
| Providing an introductory practical overview of in-flight optical flow measurement techniques is the goal of this AGARDograph. This document is written for instrumentation engineer or research scientist having a need for making non-intrusive flow measurements on an aircraft. It is hoped that this document will be particularly useful for the technologist with a limited background in optical theory and limited experience in applying optical technology. The experience of the authors ... |
|
| Localized Flow Control in High Speed Flows Using Laser Energy Deposition |
30 NOV 2003 |
25 pages |
| Authors:
Doyle D. Knight; Hong Yan; Greg Elliott; Graham Candler; Alexander Zheltovodov; RUTGERS - THE STATE UNIV PISCATAWAY NJDEPT OF MECHANICAL AND AEROSPACE ENGINEERING
|
| The capability for localized flow control in high speed flows using laser energy deposition has been investigated in a collaborative computational and experimental program. Three proposed applications have been comprehensively studied. First, two models of laser energy deposition in air have been developed and validated by comparison with experiment. The first model is an engineering approach wherein the laser energy deposition is treated as an energy release in a perfect ... |
|
| High Repetition Rate Pulse-Burst Laser and Camera for Energy Deposition Research |
30 NOV 2003 |
13 pages |
| Authors:
Greg Elliott; Doyle Knight; RUTGERS - THE STATE UNIV NEW BRUNSWICKNJ DEPT OF MECHANICAL AND AEROSPACE ENGINEERING
|
| Final Progress (1 Jun 02 30 Nov 03): A high speed camera and pulse- burst Nd:YAG laser system has been purchased as part of the DURIP equipment grant to be used for the development of novel diagnostic techniques and research associated with energy deposition. This system will allow a burst of laser pulses (for diagnostics and flow excitation utilizing laser energy deposition) and subsequent imaging at MHz rates. Preliminary images ... |
|
| Enhancement of Efficiency of Operation of High-Speed Aircraft Engine Elements by Means of Separation Flow Controlling |
20 OCT 2003 |
3 pages |
| Authors:
N. V. Guryleva; M. A. Ivankin; O. M. Kolesnikov; G. N. Lavrukhin; D. V. Merekin; TSAGI (CENTRAL AEROHYDRODYNAMIC INST) ZHUKOVSKY (RUSSIA)
|
| Results of investigations of the mechanism of appearance and destruction of separation zones in supersonic gas flows are presented. Methods for controlling separation phenomena were developed to increase the operation efficiency of ducts combustors inlets and outlets of high-speed aircrafts. The main trends of investigations were: 1) Study of deceleration flows in ducts of various shapes with pseudoshock; 2) Development of non-traditional manners of spatial implementation of combustion in supersonic ... |
|
| Burning of the Supersonic Propane-Air Mixture in the Aerodynamic Channel With the Stagnant Zone |
20 OCT 2003 |
11 pages |
| Authors:
V. M. Shibkov; V. A. Chernikov; A. P. Ershov; A. A. Karachev; R. S. Konstantinovskij; A. V. Voskanyan; V. V. Zlobin; MOSCOW STATE UNIV (RUSSIA) DEPT OF PHYSICS
|
| In the report the pulsed-periodical discharges created on an external surface of a flat plate being flown around of supersonic airflow and under condition of a stagnant zone located on a wide wall of the aerodynamic channel of rectangular section were investigated. It was show that the surface pulsed- periodical discharge results to ignition beforehand mixed supersonic propane-air fuel in the aerodynamic channel. In experimental conditions the combustion front speed ... |
|
| Numerical Research of Capabilities of Flat Thermochemical Reactor as Element of a Hypersonic Flight Vehicle Heat Protection |
20 OCT 2003 |
12 pages |
| Authors:
V. K. Vasilyev; A. V. Korabelnikov; A. V. Fedotov; AKADEMIYA NAUK SSSR MOSCOW
|
| Thermal protection of heat-stressed surfaces of a hypersonic flight vehicle (HFV) flying in dense layers of atmosphere with hypersonic velocities (M greater than or equal 7) is now one of the most actual problems 1,2. In HFV developed under the "Ajax" concept it is supposed that in the most heat- stressed parts of a skin and engine the chemical catalytic reactors will be placed in which the high endothermic processes ... |
|
| Parameters of Electrode Ignition Discharges in Supersonic Propane-Air Flows |
20 OCT 2003 |
11 pages |
| Authors:
A . P. Ershov; O. S. Surkont; I. B. Timofeev; V. A. Chernikov; V. M. Shibkov; N. V. Ardelyan; S. N. Chuvashev; V. L. Bychkov; V. G. Gromov; V. A. Levin; MOSCOW STATE UNIV (RUSSIA) DEPT OF PHYSICS
|
| Effective solution of such aerodynamic problem as fuel ignition in ramjets at supersonic velocities is evidently impossible without an application of plasma technologies. In presented work we expose results of experimental and theoretical investigations of ignition process of supersonic propane-air flows with a help of transversal and longitudinal discharges. |
|
| Reactions and Thermochemistry of Alkyl Ions, Cn H2n+1 + (n=1-8), in the Gas Phase |
20 OCT 2003 |
26 pages |
| Authors:
Skip Williams; Thomas M. Miller; W. B. Knighton; Anthony J. Midey; Susan T. Arnold; A. A. Viggiano; Campbell D. Carter; AIR FORCE RESEARCH LAB HANSCOM AFB MA SPACE VEHICLES DIRECTORATE
|
| Our research program focuses on identifying reaction processes important for plasma enhancement of combustion systems. Recommendations for temperature and energy dependencies of key ion-molecule reactions are made based on the laboratory measurements described above. Thermodynamic data such as heat capacity entropy, and enthalpy are not available as a function of temperature for many of the ionic species formed in these reactions and are thus calculated using quantum mechanical methods. The ... |
|
| Thermochemical Processes in Plasma Aerodynamics (CD-ROM) |
20 OCT 2003 |
|
| Authors:
A. A. Turchak; A. V. Korabelnikov; A. L. Kuranov; Silvano Casini; V. K. Vasilyev; LENINETZ HOLDING CO NIPGS SAINT PETERSBURG (RUSSIA) HYPERSONIC SYSTEM RESEARCH INST
|
| ELECTRONIC FILE CHARACTERISTICS: 10 files; Adobe Acrobat (.PDF) and MS Word (.DOC). PHYSICAL DESCRIPTION: 1 CD-ROM; 4 3/4 in.; 19.9 MB. SYSTEMS DETAIL NOTE: ABSTRACT: The Final Proceedings for Thermochemical Processes in Plasma Aerodynamics, 28-31 July 2003. This is an interdisciplinary conference. Topics to be covered include 1) Active thermal protection on the basis of endothermic reactions; 2) The problem of catalysis at the conversion of hydrocarbon fuel; 3) Burning ... |
|
| Winged Crusade: The Quest for American Aerospace Power |
OCT 2003 |
78 pages |
| Authors:
AIR FORCE ACADEMY COLORADO SPRINGS CO
|
| This bibliography lists a selected portion of the McDermott (Cadet) Library's holdings on the American experience of manned powered flight during the twentieth century. Excluded are newspaper articles, most pictorial works, works dealing with lighter-than-air flight and studies of rotorcraft. |
|
| Measurement and Modeling of Human Performance Under Differing G conditions |
OCT 2003 |
163 pages |
| Authors:
Robert D. O'Donnell; Samuel L. Moise; Regina Schmidt; Richard Smith; NTI INC DAYTON OH
|
| A synthesis of past literature on cognitive skills identified by pilots as being critical in the acceleration environment was performed. These skills include various kinds of decision making, tracking, spatial orientation, time/velocity estimation, perceptual speed, visual function, and instrument reading. Since the literature base on these skills is far from complete, a new test battery designed specifically to address these cognitive skills was developed. The "G-Performance Assessment Simulation System" (G-PASS) ... |
|
| A Variable Stiffness Concept For Efficient Aircraft Vertical Tail Design |
29 SEP 2003 |
30 pages |
| Authors:
Jonathan E. Cooper; O. Sensburg; M. Amprikidis; MANCHESTER UNIV (UNITED KINGDOM) SCHOOL OF ENGINEERING
|
| This report results from a contract tasking University of Manchester as follows: The contractor will investigate using a variable stiffness vertical tail attachment to control aeroelastic performance over a range of dynamic pressures. The contractor will (1) Develop an adaptive stiffness attachment for vertical tail aircraft; (2) Develop an analytical model of the attachment and predict aeroelastic performance; (3) Design build and test a vertical tail model with and without ... |
|
| Electrokinetic Flow Control and Propulsion for MAVs |
24 SEP 2003 |
30 pages |
| Authors:
B. Goeksel; I. Rechenberg; R. Bannasch; TECHNISCHE UNIV BERLIN (GERMANY F R)
|
| Briefing charts from presentation on electrokinetic flow control and propulsion systems for Micro Air Vehicles (MAV). |
|
| Projectile Aerodynamic Jump Due to Lateral Impulsives |
SEP 2003 |
36 pages |
| Authors:
Gene R. Cooper; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| The linear theory for spinning projectiles is extended to account for the application of a simple lateral square impulse activated during free flight. Analytical results are shown to produce simple contributions to the familiar aerodynamic jump formulation. Inquiries regarding jump smearing caused by nonzero impulse length are addressed and answered. The formulation shows for sufficiently long-range target interception; lateral impulse trajectory response for a guided projectile is independent of when ... |
|
| Air National Guard Flight Safety Assessment Protocol (Computer Diskette) |
SEP 2003 |
|
| Authors:
David A. Krooks; ENGINEER RESEARCH AND DEVELOPMENT CENTER CHAMPAIGN IL CONSTRUCTION ENGINEERING RESEARCH LAB
|
| ELECTRONIC FILE CHARACTERISTICS: 3 files; WinZip and MS Word (.DOC). PHYSICAL DESCRIPTION: 1 HD computer diskette; 3 1/2 in.; 298 KB (extracted). SYSTEMS DETAIL NOTE: IBM-clone PC-compatible. ABSTRACT: This flight safety compliance assessment manual is based on Air Force Instructions. The manual is intended for use by the Air National Guard. |
|
| Validation of Plasma Injection for Hypersonic Blunt-Body Drag Reduction |
27 AUG 2003 |
13 pages |
| Authors:
J. S. Shang; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH CENTER OF EXCELLENCE FOR COMPUTING SIMULATION
|
| The optimum blend of numerical and physical fluid experiment for risk and cost reduction is an actual reflection of the stage of maturation for individual technology development. As an illustration, the detailed validation of drag reduction technique using plasma injection was investigated using a side-by-side experimental and computational approach. The major portion of the reduced drag is found from the favorable counter-flow jet shock interaction and thermal deposition. |
|
| Experimental Aspects of Code Verification/Validation Application to Internal and Afterbody Aerodynamics |
27 AUG 2003 |
27 pages |
| Authors:
Richard Benay; Bruno Chanetz; Jean Delery; ONERA-MEUDON CENTRE MEUDON (FRANCE) FUNDAMENTAL/EXPERIMENTAL AERODYNAMICS DEPT
|
| The past 40 years have known a spectacular development of CFD capabilities. It is now possible to compute complex three-dimensional unsteady flows even at the design stage by solving the Unsteady Averaged Navier-Stokes Equations (URANS approach) and progress is made every day in still more advanced approaches such as LES and DNS. However, the confidence in CFD methods is still limited because of uncertainties in the numerical accuracy of the ... |
|
| Towards Faster and Safer Flight Flutter Testing |
27 AUG 2003 |
13 pages |
| Authors:
J. E. Cooper; MANCHESTER UNIV (UNITED KINGDOM) SCHOOL OF ENGINEERING
|
| The current state of the art of flight flutter testing is reviewed, and areas where this part of the certification procedure could be improved are discussed. It is argued that the key towards speeding up the flight flutter test procedure, and also to reduce costs, is to reduce the number of flight test points that are required as part of the test clearance programme. To achieve this aim, the entire ... |
|
| Nonlinear Computational Aeroelasticity: Formulations and Solution Algorithms |
27 AUG 2003 |
13 pages |
| Authors:
A. Soulaimani; A. BenElhajAli; Z. Feng; ECOLE DE TECHNOLOGIE SUPERIEURE MONTREAL (QUEBEC) DEPT DE GENIE MECANIQUE
|
| This paper highlights some technical features of an analysis methodology being developed for nonlinear computational aeroelasticity. A conservative finite element formulation for the coupled fluid/mesh interaction problem is proposed. Fluid-structure coupling algorithms are then discussed with some emphasis on distributed computing strategies. Numerical results are finally shown for the Agard 445.6 wing. |
|
| Military Aviation |
JUL 2003 |
111 pages |
| Authors:
Clement Ader; AIR UNIV PRESS MAXWELL AFB AL
|
| War is humanity's greatest calamity; on this everyone agrees. But will we ever be able to put an end to it? Only from Europe might we hope for an answer to this question, and up until now we have had no hint of a positive response. Let us then at least try to reduce the evils of war. what we should strive to do is reduce the number of war's ... |
|
| Study of the Boundary Layer in the Inboard Sections of a Tilt-Rotor Blade by Embedded LDV Measurements |
JUL 2003 |
19 pages |
| Authors:
Christian Maresca; Marcellin Nsi Mba; Eric Berton; Daniel Favier; Charlie Barla; MEDITERRANEE UNIV MARSEILLE (FRANCE) LAB D'AERODYNAMIQUE ET DE BIOMECANIQUE DU MOUVEMENT
|
| This report focuses on the boundary layer (BL) velocity distribution in the inboard region of a tiltrotor blade. The instrumentation consists of a Laser Doppler Velocimeter embedded in the inboard region of the blade. This set up allows measuring the chordwise and spanwise component of the boundary layer velocity from a distance of 0.3 mm to 20 mm along a direction normal to the blade surface. The experiments were carried ... |
|
| Computational Mechanics Approach for Multidisciplinary Nonlinear Sensitivity Analysis |
30 JUN 2003 |
8 pages |
| Authors:
Ramana V. Grandhi; WRIGHT STATE UNIV DAYTON OH DEPT OF MECHANICAL AND MATERIALS ENGINEERING
|
| The primary objective of this research work was to develop preliminary designs of aircraft wing/store configurations to achieve improved flutter performance in the transonic regime. In this research work, a methodology was developed to incorporate the nonlinearities associated with the wing and store in transonic regime into the multidisciplinary environment. Investigated the aeroelastic effects of the wing with and without the inclusion of store aerodynamics. The tip store configurations and ... |
|
| Energy Based Design and Control for Innovative Air Vehicle Concepts |
30 JUN 2003 |
15 pages |
| Authors:
Gregory Washington; OHIO STATE UNIV COLUMBUS
|
| In nature, birds change shape of their wings to achieve proper flight performance. In fact a falcon can glide or loiter at tremendous heights and then dive at three times its gliding speed to strike its prey. Falcons are able change the geometry of their wings by bending them at the shoulder, elbow and wrist. They can also affect the camber of the wing, and even articulate feathers at the ... |
|
| An Advanced Free Flight Research Facility |
20 JUN 2003 |
31 pages |
| Authors:
P. M. Sforza; Chris Anderson; FLORIDA UNIV SHALIMAR GRADUATE ENGINEERING AND RESEARCH CENTER
|
| This report documents activities to install a tomographic density station into the Aeroballistic Research Facility (ARF). The objective of this research grant was to provide new insights into fluid dynamic research and design since this technology has the ability to characterize the spatial and temporal density profiles around the projectile/model. In this section, an overview of the current measurement capabilities ARF are discussed as stand alone techniques and we reintroduce ... |
|
| AeroLab User's Guide (CD-ROM) |
04 JUN 2003 |
|
| Authors:
Lamar M. Auman; Aaron Tauchen; ARMY AVIATION AND MISSILE COMMAND REDSTONE ARSENAL AL MISSILE RESEARCH DEVELOPMENT AND ENGINEERING CENTER
|
| ELECTRONIC FILE CHARACTERISTICS: 108 files; Adobe Acrobat (.PDF), MS Word (.DOC), and AeroLab Application. PHYSICAL DESCRIPTION: 1 computer laser optical disc (CD-ROM); 4 3/4 in.; 7.75 MB. SYSTEMS DETAIL NOTE: IBM-clone PC-compatible. ABSTRACT: An aerodynamic analysis tool for archiving, manipulating, plotting, and tabulating wind tunnel test data has been developed. This tool, dubbed AeroLab, is part of the U. S. Army Aviation and Missile Command's (AMCOM's) Aerodynamic Analyzer System (AAS). ... |
|
| Intelligent Systems for Aerospace Engineering - An Overview |
01-Jun-2003 |
|
| Authors:
K Krishnakumar; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER
|
|
| Upgrade of a LabVIEW Based Data Acquisition System for Wind Tunnel Test of a 1/10 Scale OH-6A Helicopter Fuselage |
JUN 2003 |
99 pages |
| Authors:
Philipp A. Lines; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| For over half a century the NPS Aerolab Low Speed Wind Tunnel located in Halligan Hall of the Naval Postgraduate school has served to provide students and facility with meaningful aerodynamic data for research and problem analysis. New data acquisition hardware was installed three years ago but never fully verified, and contained no integrated software program to collect data from the strain-gauge balance pedestal. Existing National Instruments based hardware for ... |
|
| An Experimental Investigation of Flapping Wing Aerodynamics in Micro Air Vehicles |
JUN 2003 |
111 pages |
| Authors:
Christopher J. Bradshaw; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| Flapping-wing propulsion was studied experimentally through Laser Doppler Velocimetry. Measurements were both time-averaged and unsteady, and were conducted on a Micro- Air Vehicle (MAV) model developed at NPS by Professors Max Platzer and Kevin Jones. The objective of this work was to further understanding of the aerodynamics of flapping-wing propulsion. In specific, this study examined separation control on the leading fixed wing due to entrainment by the trailing flapping wings. ... |
|
| Preliminary Experiments for Evaluating 3-D Effects on Cracks in Frozen Stress Models |
28 MAY 2003 |
11 pages |
| Authors:
C. W. Smith; J. D. Hansen; C. T. Liu; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| Information gleaned from applying the frozen stress photoelastic method to cracks emanating from critical locations around the fin tips in models of solid rocket motors is reviewed and assessed together with new experimental results. The studies are the initial part of a program developed to contribute background data for consideration in modifying current motor grain design rationale. |
|
| The Aeroelastic Effects of Transverse Shear Deformation on Composite Wings in Various Speed Flow Regimes |
02 MAY 2003 |
70 pages |
| Authors:
Michael Oliver; NAVAL ACADEMY ANNAPOLIS MD DEPT OF AEROSPACE ENGINEERING
|
| This project analyzes the effect of transverse shear deformation upon the aeroelastic response of composite wings in high speed flow regimes. Previously, models were developed to predict the aeroelastic characteristics of classical materials in high speed flow. However, these studies ignored transverse shear by assuming an infinite modulus of rigidity. This assumption underestimates transverse flexibility by ignoring the transfer of loads through the wing thickness. By assuming a finite modulus ... |
|
| Unsteady Numerical Simulations of Subsonic Flow Over a Projectile with Jet Interaction |
MAY 2003 |
27 pages |
| Authors:
Jubaraj Sahu; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
|
| This report describes a computational study undertaken to consider the aerodynamic effect of synthetic jets as a means to provide the control authority needed to maneuver a projectile at low subsonic speeds. The time- accurate Navier-Stokes computational technique has been used to obtain numerical solutions for the unsteady jet interaction flow field for a projectile at a subsonic speed, Mach = 0.11, and several angles of attack from O deg ... |
|
| Dynamic Aeroelastic Instabilities of an Aircraft Wing with Underwing Store in Transonic Regime |
MAY 2003 |
31 pages |
| Authors:
Chakradhar Byreddy; Ramana V. Grandhi; Philip Beran; ADVANCED STRATEGIC AND TACTICAL INFRARED EXPENDABLES OFFICE WRIGHT-PATTERSONAFB OH
|
| The research used the Transonic Small Disturbance (TSD) theory to better understand the dynamic aeroelastic phenomena and factors that affect the onset of flutter and store induced Limit-Cycle Oscillations (LCO) in the transonic regime. Several parametric studies of the flutter and LCO of an aircraft wing with underwing store in the transonic regime were conducted, as well as an investigation of the effect of inclusion of store aerodynamics on the ... |
|
| Distributed Modeling and Control of Adaptive Wings |
10 MAR 2003 |
7 pages |
| Authors:
Daniel J. Inman; VIRGINIA POLYTECHNIC INST AND STATE UNIV BLACKSBURG CENTER FOR INTELLIGENT MATERIAL SYSTEMS AND STRUCTURES
|
| New generations of highly-maneuverable aircraft, such as Uninhabited Combat Air Vehicles (UCAV) or Micro Air Vehicles (MAV), are likely to feature very flexible lifting surfaces. In order to enhance their stealth properties and maneuverability, the possibility of using smart wings and morphing airfoils instead of conventional, hinged control surfaces is investigated. This task requires a fundamental understanding of the interaction between fluid, structure and control system, in a coded form ... |
|
| DNS Studies of Transitional Hypersonic Reacting Flows Over 3-D hypersonic Vehicles |
05 MAR 2003 |
54 pages |
| Authors:
Xiaolin Zhong; CALIFORNIA UNIV LOS ANGELES DEPT OF MECHANICAL AND AEROSPACE ENGINEERING
|
| The objectives of this research project are to develop CFD techniques and to conduct DNS studies of fundamental flow physics leading to boundary-layer instability and transition in hypersonic flows During the three-year period, we have conducted extensive DNS studies on the receptivity of a supersonic boundary layer over a blunt cone, and over both sharp and blunt leading edge; and on the receptivity of the Goertler vortices. DNS studies were ... |
|
| UAV Aeroelastic Control Using Redundant Micro-Actuators |
03 MAR 2003 |
15 pages |
| Authors:
Ilan Kroo; Fritz Prinz; John Eaton; STANFORD UNIV CA
|
| The investigation of trailing edge micro-actuators for aeroelastic control of uninhabited air vehicles (UAVs) has ranged from examining the fundamental aerodynamic effects to demonstrating flutter suppression of a flexible wing. The applicability of aerodynamic prediction methods including CFD and panel methods has been studied. Several generations of actuator concepts have been developed and characterized. Wind tunnel experiments have been completed on a rigid wing to determine the aerodynamic performance of ... |
|
| Statistical Process Control: An Application in Aircraft Maintenance Management |
MAR 2003 |
93 pages |
| Authors:
Bradley A. Beabout; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
|
| Maintenance management at the 135th Airlift Wing, Maryland Air National Guard desires a visualization tool for their maintenance performance metrics. Currently they monitor their metrics via an electronic spreadsheet. They desire a tool that presents the performance information in a graphical manner. This thesis effort focuses on the development of a visualization tool utilizing two of the seven tools offered by Statistical Process Control (SPC). This research demonstrates the application ... |
|
| Performance Measurements, Flow Visualization, and Numerical Simulation of a Crossflow Fan |
MAR 2003 |
127 pages |
| Authors:
M. S. Seaton; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| Recently, NASA has placed emphasis on the need for a more robust civil transport system intended to alleviate congestion in ground and air traffic near major cities. This has resulted in funding for research into various aspects of this broad goal. One such research program encourages the development of civil alternatives to private ground transport, the intent being to reduce ground traffic by replacing the private automobile with a similarly ... |
|
| Reduction of Military Vehicle Acquisition Time and Cost through Advanced Modelling and Virtual Simulation (La reduction des couts et des delais d'acquisition des vehicules militaires par la modelisation avancee et la simulation de produit virtuel) |
MAR 2003 |
|
| Authors:
NATO RESEARCH AND TECHNOLOGY ORGANIZATION NEUILLY-SUR-SEINE (FRANCE)
|
| Integrated weapon systems modeling and simulation from concept to operation were treated as essential tool for achieving cost and time reductions which are needed to field new systems. Such tools are being applied to lower the cost and design cycle times from both a design/development and recurring manufacturing perspective. Early identification of problems dramatically reduces costs and improves procurement as well as operations, increasing performance as well as cost effectiveness. ... |
|
| Unsteady Aerodynamic Model for Thin Wings With Evolutive Vortex Sheets |
MAR 2003 |
|
| Authors:
Annie Leroy; Franck Buron; Philippe Devinant; NATO RESEARCH AND TECHNOLOGY AGENCY CEDEX (FRANCE)
|
| This paper presents recent advances in a computing method for unsteady inviscid incompressible flows around thin lifting surfaces with arbitrary motion. This involves the velocity field, deriving from a potential, the pressure field and the free vortex sheet characteristics (geometry and vortex strength). When considering high angles of attack, the separation lines along which the vortex sheets are shed are the trailing edge, as well as wing tips or parts ... |
|
| Vortex Flow Dilemmas and Control on Wing Planforms on High Speed |
MAR 2003 |
|
| Authors:
R. K. Nangia; A.S. MILLER; NATO RESEARCH AND TECHNOLOGY AGENCY CEDEX (FRANCE)
|
| Aircraft for sustained supersonic flight usually feature low aspect ratio wings with varying (reducing) leading edge sweep over the outer portion to achieve an adequate low-speed performance. A high-speed "cruise" wing then becomes subject to mixed flows at low-speeds including strong Vortical flows. |
|
| Unsteady Flows and Airfoil-Vortex Interaction |
MAR 2003 |
14 pages |
| Authors:
M. Mamou; M. Khalid; H. Xu; NATIONAL RESEARCH COUNCIL OF CANADA OTTAWA (ONTARIO) INST FOR AEROSPACE RESEARCH
|
| Unsteady flows past two airfoils in tandem placed in a shock tube flow field have been studied using Navier-Stokes equations. An implicit Global Newton iterative procedure is applied for time-accurate solution of the transient flow field. This study is primarily motivated by a need to understand the aerodynamic implications of the blade-vortex interaction in the rotor flow field of a helicopter. To simulate the vortex effects in 2D, a streamwise ... |
|
| Time Accurate Euler Calculations of Vortical Flow over a Delta Wing in Rolling Motion |
MAR 2003 |
14 pages |
| Authors:
W. Fritz; M. T. Arthur; F. J. Brandsma; K. A. Buetefisch; N. Ceresola; EUROPEAN AERONAUTIC DEFENCE AND SPACE DEUTSCHLAND GMBH MUNCHEN (GERMANY)
|
| This paper presents the results of research conducted by Alenia (Italy), Dasa (Germany), DERA (United Kingdom), NLR (The Netherlands), and DLR (Goettingen, Germany) as part of the Western European Armaments Group (WEAG) ta15 program, Common Exercise V. The WEAG TA15 program was a collaborative program concerned with the investigation of steady and unsteady vortical flows over military aircraft configurations. An important component of the program were the Common Exercises (CE), ... |
|
| An Experimental Study of the Flow Around an Axisymmetric Body at High Angles of Attack |
MAR 2003 |
12 pages |
| Authors:
D. K. Pantelatos; D. S. Mathioulakis; NATIONAL TECHNICAL UNIV ATHENS (GREECE) DEPT OF MECHANICAL ENGINEERING
|
| The investigation of the flow field around an axisymmetric body inclined at an angle with respect to the oncoming free stream constitutes a challenging task due to the complex nature of the flow. However, understanding the as yet unanswered question as to what causes flow asymmetries over a symmetric body at high angles of attack would improve the maneuverability of such bodies. In the present work, the flow field about ... |
|
Aerodynamics
