| NLR 7301 Supercritical Airfoil Oscillatory Pitching and Oscillating Flap |
01 OCT 2000 |
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| Authors:
R. J. Zwaan; NATIONAL AEROSPACE LAB AMSTERDAM (NETHERLANDS)
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 | The supercritical airfoil NLR 7301 has a maximum thickness of 16.5 per cent of the chord. In the Set of two-dimensional aeroelastic configurations this airfoil represents the category of thick and blunt-nosed airfoils. The airfoil was investigated in two windAtunnel tests with different models. In the first test the model could be driven harmonically in a pitching motion about an axis at 40 per cent of the chord. Information about ... |
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| ZKP Wing, Oscillating Aileron |
01 OCT 2000 |
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| Authors:
K. Dau; S. Vogel; H. Zimmermann; MBB TRANSPORT AND VERKEHRSFLUGZEUGE BREMEN (GERMANY)
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| This Data Set contains pressure distributions measured on the ZKP wing for an oscillating aileron in the ONERA fransonic 5 1 wind tunnel at Modane, France, in late 1982. The tests were part of a cooperative project between MBB, ONERA, and the Aerospatiale Corporation. The purpose of the tests was to obtain steady and unsteady pressures due to fast-moving control surfaces in transonic flow, likely to be encountered in the ... |
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| F-5 CFD Results |
01 OCT 2000 |
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| Authors:
BRITISH AEROSPACE OPERATIONS LTD BROUGH(UNITED KINGDOM) MILITARY AIRCRAFT AND AEROSTRUCTURES
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| The F-5 test series (see chapter 5) provides a succession of geometries of increasing complexity Ref. 1 Ref. 2, which will he useful for validating CFD codes during their development. In this chapter a range of CFD results are provided for the clean wing configuration at selected flow conditions, and a more limited set for one complex configuration. Results from essentially slate of the art UTSP (Unsteady Transonic Small Perturbation), ... |
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| F-5 Wing & F-5 Wing + TIP Store |
01 OCT 2000 |
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| Authors:
Evert G. Geurts; NATIONAL AEROSPACE LAB AMSTERDAM (NETHERLANDS)
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| This data set relates to a transonic wind tunnel investigation carried out in l977 on an oscillating, slightly modified model of the outer part of a Northrop F-5 wing with and without an external store. The store represented an AlM-9J missile including its launcher. These tests were reported in references 1,2 and 3. The model proceeded from an F-5 wing model for subsonic tests by a slight reduction of the ... |
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| Test Cases for a Rectangular Supercritical Wing Undergoing Pitching Oscillations |
01 OCT 2000 |
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| Authors:
Robert M. Bennett; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA AEROELASTICITY BR STRUCTURES/MATERIALS
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| Steady and unsteady measured pressures for a Rectangular Supercritical Wing (RSW) undergoing pitching oscillations have been presented in Ref I to 3. From the several hundred compiled data points, 27 static and 36 pitching oscillation cases have been proposed for computational Test Cases to illustrate the trends with Mach number, reduced frequency, and angle of attack. The wing was designed to be a simple configuration for Computational Fluid Dynamics (CFD) ... |
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| Test Cases for Flutter of the Benchmark Models Rectangular Wings on the Pitch and Plunge Apparatus |
01 OCT 2000 |
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| Authors:
Robert M. Bennett; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA AEROELASTICITY BR STRUCTURES/MATERIALS
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| As a portion of the Benchmark Models Program at NASA Langley (Ref I), three models with the same rectangular plankton, but with different airfoils were flutter tested on the Pitch and Plunge Apparatus (PAPA. Ref 2-3). These models were designed and tested to provide flutter data for evaluating Computational Aeroelasticity (CA) programs with emphasis on transonic flows The geometry of the wings was kept simple to reduce the complexity of ... |
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| Test Cases for the Benchmark Active Controls Model: Spoiler and Control Surface Oscillations and Flutter |
01 OCT 2000 |
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| Authors:
Robert M. Bennett; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA AEROELASTICITY BR STRUCTURES/MATERIALS
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| As a portion of the Benchmark Models Program at NASA Langley (Ref 1-2). a simple generic model was developed for active controls research and was called BACT for Benchmark Active Controls Technology model. This model was based on the previously-tested Benchmark Models rectangular wing with the NACA 0012 airfoil section that was mounted on the Pitch and Plunge Apparatus (PAPA) for flutter testing (Ref 1, 3-5) The BACT model had ... |
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| Benchmark Active Controls Technology (BACT) Wing CFD Results |
01 OCT 2000 |
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| Authors:
David M. Schuster; Robert E. Bartels; DNW(DEUTCH-NIEDERLANDISCHER WINDKANAL)-NWB(NIEDERGESCHWINDIGKEITS-WINDCANAL)BRAUNSCHWEIG (GERMANY)
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| The Benchmark Active Controls Technology (BACT) wing test (see chapter 8E) provides data for the validation of aerodynamic, aeroelastic, and active aeroelastic control simulation codes. These data provide a rich database for development and validation of computational aeroelastic and aeroservoelastic methods. In this vein, high-level viscous CFD analyses of the BACT wing have been performed for a subset of the test conditions available in the dataset. The computations presented in ... |
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| Test Cases for a Clipped Delta Wing with Pitching and Trailing-Edge Control Surface Oscillations |
01 OCT 2000 |
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| Authors:
Robet M. Bennett; DNW(DEUTCH-NIEDERLANDISCHER WINDKANAL)-NWB(NIEDERGESCHWINDIGKEITS-WINDCANAL)BRAUNSCHWEIG (GERMANY)
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| Steady and unsteady measured pressures for a Clipped Delta Wing (CDW) undergoing pitching oscillations and trailing-edge control surface oscillations have been presented in Ref I and 2. From the several hundred compiled data points, 22 static cases, 12 pitching-oscillation cases, and 12 control-surface-oscillation cases have been proposed for Computational Test Cases to illustrate the trends with Mach number, reduced frequency, and angle of attack. The planform for this wing was ... |
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| Supersonic 2D Wing with Control Surfaces |
01 OCT 2000 |
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| Authors:
P. Naudin; OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES CHATILLON-SOUS-BAGNEUX (FRANCE)
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| For some years ONERA, in collaboration with AEROSPATIALE, has undertaken research into improvement of CFD codcs, in the framework of studies on a new supersonic plane. The main goal has been to take unsteady effects, induced by movements of control surfaces such as spoilers or trailing edge flaps, into account with improved accuracy. For this purpose a wind tunnel test was carried out to provide an extensive database of unsteady ... |
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| RAE Rests on AGARD Tailplane |
01 OCT 2000 |
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| Authors:
I. W. Kaynes; DEFENCE EVALUATION AND RESEARCH AGENCY FARNBOROUGH (UNITED KINGDOM)
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| This data set relates to tests at RAE which were carried out and reported by D (3 Mabey, B L Welsh and B E Cripps, ref. 1. The tests were undertaken to provide data for the validation of codes for the prediction of both steady and unsteady pressures on low aspect ratio configurations, suitable for the wings or controls of military aircraft. Comprehensive measurements have not been available to verify ... |
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| NAL SST Arrow Wing with Oscillating Flap |
01 OCT 2000 |
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| Authors:
M. Tamayama; K. Saitoh; H. Matsushita; J. Nakamichi; NATIONAL AEROSPACE LAB TOKYO (JAPAN)
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| A wind tunnel model of a SST(Supersonic Transport) arrow wing was tested in transonic regime. The purpose of this experiment is to accumulate verification data for the establishment of aeroelasticity related CFD codes and ACT (Active Control Technology ) in the Japanese SST program. The model is a semi-span arrow wing with a fuselage. The leading edge is double-swept-backed as shown in Fig. 1 and 2. The inboard sections of ... |
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| Transonic Buffet of a Supercritical Airfoil |
01 OCT 2000 |
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| Authors:
X. Z. Huang; NATIONAL RESEARCH COUNCIL OF CANADA OTTAWA (ONTARIO) INST FOR AEROSPACE RESEARCH
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| This investigation was carried out in the Institute for Aerospace Research (IAR) 2D High Reynolds Test Facility (Ref. 1 to Ref. 3 and Fig. 1) to study the buffet characteristics of a supercritical airfoil DGK No. I (Fig. 2). Steady unsteady surface pressure and normal force were measured at various angles of attack and Mach numbers. The statistical properties of the normal force and pressure were carried out by spectral ... |
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| Buffet Data from M2391 Diamond Wing |
01 OCT 2000 |
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| Authors:
I. W. Kaynes; DEFENCE EVALUATION AND RESEARCH AGENCY FARNBOROUGH (UNITED KINGDOM)
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| Unsteady aerodynamic loads may be described in terms of the aerodynamic excitation arising from unsteady separated flows (buffet) or the associated uncoupled structural response (buffeting). Buffeting response measurements arc usually made on nominally rigid or aero-elastically tuned models, with buffeting levels determined from the narrow band response of wing root strain gauges or wing tip mounted accelerometers. In such cases the model structural dynamics are tuned to provide sufficient buffeting ... |
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| Wing and FIN Buffet on the Standard Dynamics Model |
01 OCT 2000 |
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| Authors:
X. Z. Huang; FIELD TECHNOLOGY INC LONG BEACH CA
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| For modern aircraft with higher sweep angles flying at higher incidence, unsteady and burst vortex flow in the vicinity of the wing and downstream lifting surface lead to strong unsteady airloads and buffeting'. Thus, investigations were conducted in the Institute for Aerospace Research (lAR) Low Speed Wind Tunnel (LSWT)2 to study the buffet characteristics of the Standard Dynamics Model (SDM)3, a generic fighter aircraft configuration. Since the spectrum of the ... |
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| Selected Data Set from Static and Rolling Experiments on a 65 Deg. Delta Wing at High Incidence |
01 OCT 2000 |
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| Authors:
X. Z. Huang; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCHCENTER
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| This data set is selected from an extensive set of experimental results obtained for configurations with a 650 delta wing under static as well as large-amplitude high-rate rolling or pitching conditions at high incidence. The experiments were performed under a joint research program on "Non-Linear Aerodynamics under Dynamic Maneuvers" by the National Research Council of Canada (NRC (IAR)), the U.S. Air Force (USAF (AFOSR, AFRL)) and the Canadian Dept. for ... |
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| Large-Amplitude, High-Rate Roll Oscillations of a 65 deg. Delta Wing at High Incidence |
01 OCT 2000 |
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| Authors:
Neal M. Chaderjian; Lewis B. Schiff; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCHCENTER
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| The IAR/WL 65 deg. delta wing experimental results provide both detail pressure measurements and a wide range of flow conditions covering from simple attached flow, through fully developed vortex and vortex burst flow, up to fully-stalled flow at very high incidence. Thus, the Computational Unsteady Aerodynamics researchers can use it at different level of validating the corresponding code. In this section a range of CFD results are provided for the ... |
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| Oscillating 65 Deg. Delta Wing, Experimental |
01 OCT 2000 |
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| Authors:
Thomas Loeser; DNW(DEUTCH-NIEDERLANDISCHER WINDKANAL)-NWB(NIEDERGESCHWINDIGKEITS-WINDCANAL)BRAUNSCHWEIG (GERMANY)
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| This data set contains force and pressure data resulting from static and dynamic measurements on a sharp-edged cropped delta wing with a leading edge sweep of 65 oscillating in different modes. Motivation for the experiment were the provision of experimental data for validation of unsteady computational codes and understanding of the flow past an oscillating delta wing. The model geometry is identical to a geometry used in the Vortex Flow ... |
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| Oscillating 65 Deg. Delta Wing, Numerical |
01 OCT 2000 |
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| Authors:
Willy Fritz; DAIMLER CHRYSLER AEOROSPACE MANCHING (GERMANY)
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| This data set consists of steady and unsteady numerical solutions of a sharp-edged cropped delta wing with a leading edge sweep of 65 undergoing a pitching oscillation. The geometry of the wing corresponds with the geometry of the wind tunnel model described in the previous data set (chapter 17B), the difference being the absence of the fuselage in the numerical model. The presence of the fuselage on the upper surface ... |
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| Low Speed Straked Delta Wing |
01 OCT 2000 |
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| Authors:
Evert G. Geurts; NATIONAL AEROSPACE LAB AMSTERDAM (NETHERLANDS)
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| Straked wings have become common features of advanced fighter-type aircraft. The strakes are designed to generate vortices from their highly swept leading edges, which stabilize the flow over the wing and provide additional lift up to high angles of amuck In this way the strakes contribute much to a high maneuverability. The vortex lift capability of straked wings has been extensively explored and experimental data concerning aerodynamic loading are available ... |
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| Transonic Simple Straked Delta Wing |
01 OCT 2000 |
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| Authors:
Evert G. Geurts; NATIONAL AEROSPACE LAB AMSTERDAM (NETHERLANDS)
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| The unsteady transonic flow during manoeuvres of fighters is not very well understood. For instance, large time delays and severe dynamic overshoots in normal force may occur, which cannot be predicted accurately by numerical methods. As a consequence to be conservative structures must be over-designed or flight envelopes must be unnecessarily restricted There fore, a better understanding of the unsteady transonic flows, which occur during maneuvers, is of interest for ... |
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| M219 Cavity Case |
01 OCT 2000 |
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| Authors:
M. J. Henshaw; BRITISH AEROSPACE OPERATIONS LTD BROUGH(UNITED KINGDOM) MILITARY AIRCRAFT AND AEROSTRUCTURES
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| The data contained in this set consists of pressure tire histories measured on the ceiling of an empty rectangular cavity, and were measured as p&t of a joint BAe./DERA programme at the ARA wind tunnel at Bedford during November 1991 The overall programme consisted of several configurations, with bodies positioned at various proximities to the cavity, but the data presented here only considers the empty cavity, configured for both shallow ... |
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| DLR Cavity Pressure Oscillations, Experimental |
01 OCT 2000 |
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| Authors:
Jan Delfs; GERMAN AEROSPACE CENTER BRAUNSCHWEIG (GERMANY) INST OF DESIGN AERODYNAMICS
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| Wind tunnel tests were carried out with the aim of establishing a measured unsteady surface pressure data set in and around a box- shaped shallow cavity, subject to tangential flow in the transonic Mach number range. Apart from the baseline case, for which systematic Mach number and Reynolds number variations were completed, the main purpose of the tests was to investigate the effect of certain upstream mounted passive flow control ... |
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| Dynamic Stall Data for 2-D and 3-D Test Cases |
01 OCT 2000 |
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| Authors:
R. A. McD Galbraith; F. N. Coton; R. B. Green; M. Vezza; GLASGOW UNIV (UNITED KINGDOM)
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| Although substantial work has been carried out and much understanding gained of the phenomena associated with dynamic stall, out description and understanding of it is incomplete. Even if we consider the nominally two-dimensional flow associated with most experiments, some significant anomalies have yet to be explained. Fully three-dimensional experiments are few and, as might have been expected, raise more questions than have been answered. The purpose of the selected cases ... |
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| Sikorsky SSC-A09 Data (Nominally Two Dimensional) |
01 OCT 2000 |
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| Authors:
GLASGOW UNIV (UNITED KINGDOM) DEPT OF AEROSPACE ENGINEERING
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| The tests described were carried out in the University of Glasgow's 'Handley Page' wind tunnel, which is a closed-return, low- speed type with a 2.13m x 1 .61m octagonal working section (Fig 3). The model span and chord were l.61m and O.55m respectively, and its construction was of a fiberglass skin filled with an epoxy foam bonded to an aluminium spar. The model was pitched about the quarter chord by ... |
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| NACA 0015 Data (Nominally Two-Dimensional) |
01 OCT 2000 |
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| Authors:
GLASGOW UNIV (UNITED KINGDOM) DEPT OF AEROSPACE ENGINEERING
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| The tests described were carried out in the University of Glasgow's Handley Page wind tunnel, which is a closed-return, low- speed type with a 2.13m x 1.61m octagonal working section. The model span was l.61m, and its construction was of a fibre glass skin filled with an epoxy foam bonded to an aluminium spar. The model was pitched about the quaffer chord by a linear hydraulic actuator and crank mechanism. ... |
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| NACA 0015 Data (Three-Dimensional) |
01 OCT 2000 |
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| Authors:
GLASGOW UNIV (UNITED KINGDOM) DEPT OF AEROSPACE ENGINEERING
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| The tests described herein were carried out in the University of Glasgow's 2.1 3m X 1.61 m 'Handley Page' wind tunnel which is a low-speed closed return type. The test model was a straight wing with a NACA 0015 cross-section and had simple solids of revolution at its tips. Because the lift behaviour at low aspect-ratios (AR) is quite different from that at high aspect ratios, particularly when AR is ... |
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| Generic Wing, Pylon, and Moving Finned Store |
01 OCT 2000 |
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| Authors:
John H. Fox; SVERDRUP TECHNOLOGY INC ARNOLD AFS TN
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| A Computational Fluid Dynamics (CFD) Program of the U. S. Air Force Research Laboratory (AFRL), formerly (AFATL), funded and supported this wind tunnel test. The data support the ongoing validation efforts for CFD codes. A review at AEDC, completed June 12. 1996, determined the data were unrestricted. The test met the objectives of providing pressure data from geometrically simple wing and store shapes under mutual interference conditions with the store ... |
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| Proceedings of JSASS 14th International Sessions in 38th Aircraft Symposium October 11-13, 2000 Sendal Civic Auditorium Sendal, Japan |
OCT 2000 |
185 pages |
| Authors:
TOHOKU UNIV SENDAI (JAPAN)
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 | Conference Proceedings Included 7 Sessions With Topics Which Included: An Improved Co-Evolutionary Method for Pursuit-Evasion Game"; Analytic Solution of the Calculation of Turn Maneuver of Agricultural Aircraft"; Control Law Design for Aircraft With Reduced Tail Size in Preliminary Design Phase"; Aeroelastic Analysis of Active Twist Helicopter Rotor Blades"; Acoustic Behaviour of Cavities Due to Fluid-Structure Interactions Problems"; Numerical Simulation of a Dual-Combustor Scramjet Flow-Field"; "Deployment ... |
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| Donnees de Verification et de Validation pour L'Aerodynamique Instationnaire Numerique. (Verification and Validation Data for Computational Unsteady Aerodynamics) (CD-ROM) |
OCT 2000 |
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| Authors:
NATO RESEARCH AND TECHNOLOGY ORGANIZATION NEUILLY-SUR-SEINE (FRANCE)
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| ELECTRONIC FILE CHARACTERISTICS: 1,481 files; text, database and video; MS Word and Adobe PDF, FORTRAN, QuickTime movies. PHYSICAL DESCRIPTION: 1 computer laser optical disc (CD-ROM); 4 3/4 in.; 342 MB. SYSTEMS DETAIL NOTE: IBM-clone PC-compatible; requires CD-ROM drive, video driver and Adobe Acrobat. ABSTRACT: This CD-ROM contains two main file folders; one holding the electronic version in PDF of the publication, the other holding the database and also the original ... |
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| Trailing Edge Noise Prediction: Large-Eddy Simulation of Wall Bounded Shear Flow Using the Nonlinear Disturbance Equations |
26 SEP 2000 |
18 pages |
| Authors:
Thomas S. Chyczewski; Philip J. Morris; Lyle N. Long; PENNSYLVANIA STATE UNIV UNIVERSITY PARK APPLIED RESEARCH LAB
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| The potential benefits of using the Nonlinear Disturbance (NLD) equations, which govern flow variable fluctuations about an estimated mean, for the large-eddy simulation (LES) of wall bounded shear flows are investigated in this paper. In addition to verifying the suitability of the NLD equations for wall bounded flows, we build upon its advantages by introducing a new wall model that is easily and efficiently implemented within ... |
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| Data Base Tomography Applied to an Aircraft Science and Technology Investment Strategy |
21 SEP 2000 |
114 pages |
| Authors:
Ronald N. Kostoff; Kenneth A. Green; Darrell R. Toothman; James A. Humenik; SEMCOR INC WARMINSTER PA
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| Data Base Tomography (DT) is a textual data base analysis system consisting of two major components: (1) algorithms for extracting multiword phrase frequencies and phrase proximities (physical closeness of the multiword technical phrases) from any type of large textual data base, and (2) applying interpretative capabilities of the expert human analyst. DT was used to obtain technical intelligence from aircraft data bases derived from the ... |
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| An Assessment of Smart Air and Space Structures: Demonstrations and Technology |
SEP 2000 |
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| Authors:
Alok Das; Janet M. Sater; C. R. Crowe; Richard Antcliff; INSTITUTE FOR DEFENSE ANALYSES ALEXANDRIA VA
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| During the past decade, the multidisciplinary field of smart materials and structures has experienced rapid growth in terms of individual technologies and applications. The integration of sensors, actuators, and controllers with structures that enable adaptation to environmental and operational conditions has progressed to such a point that numerous systems applications are being demonstrated. This paper reviews the current status, results to date, and issues ... |
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| Plasma Influence on Characteristics of Aerodynamic Friction and Separation Lines Location |
SEP 2000 |
105 pages |
| Authors:
Serguei Leonov; RUSSIAN ACADEMY OF SCIENCES MOSCOW INST OF HIGH TEMPERATURES
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| This report results from a contract tasking Moscow Technical Company Institute of High Temperature RAS as follows: The contractor will analyze experimental plasma data already obtained on different aerodynamic shapes and produce an experiment at plate model. Three types of surface discharges will be tested in this work: HF multi-streamer discharge, micro hollow cathode discharge and glide surface discharge. The project objectives are 1) analysis of ... |
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| AGARD Flight Test Techniques. Volume 19. Simulation in Support of Flight Testing. (la Simulation pour le soutien des essais en vol) |
SEP 2000 |
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| Authors:
NATO RESEARCH AND TECHNOLOGY ORGANIZATION NEUILLY-SUR-SEINE (FRANCE)
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| Flight testing continues to remain an essential step in the development or modification of an aircraft. Modem fixed wing aircraft are highly complex systems that push the edges of aerodynamic, propulsion, and control system technologies. Many of these technologies are integrated together and dependent upon each other. Certainly, modem military aircraft ranging from the F-22 to the EF2OOO push the boundaries of capabilities that can be built into an aircraft. ... |
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| Parallell Multigrid DNS/LES Methods for Time-Dependent Compressible Turbulent Flow Around 3-D Airfoils |
SEP 2000 |
52 pages |
| Authors:
Chaoguin Liu; Hua Shan; Li Jiang; LOUISIANA TECH UNIV RUSTON COLLEGE OF ENGINEERING AND SCIENCE
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| Direct numerical simulation has been carried out to simulate the flow around a slender flat-plate delta wing at 12.5 deg angle of attack. Two Reynolds numbers have been selected. At a lower Reynolds number of 5 x 104, the flow is stable and dominated by a pair of leading-edge primary vortices. At a higher Reynolds number of 1.96 x 105, small-scale vortical structures are shedding from the leading-edge. It has ... |
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| Technologies for Future Precision Strike Missile Systems - Missile Aeromechanics Technology |
SEP 2000 |
11 pages |
| Authors:
Eugene L. Fleeman; GEORGIA INST OF TECH ATLANTA SCHOOL OF AEROSPACE ENGINEERING
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| This paper provides an assessment of the state-of-the-art of new aeromechanics technologies for future precision strike missile systems. The aeromechanics technologies are grouped into specific discussion areas of aerodynamics, propulsion, and airframe materials technologies. Technologies that are addressed in this paper are: *Missile aerodynamics technologies. Assessments include aerodynamic configuration shaping, lattice tail control, split canard control, forward swept surfaces, bank-to-turn maneuvering, and flight trajectory shaping. * Missile propulsion technologies. Assessments ... |
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| Nonlinear Reduced Order Modeling of Limit Cycle Oscillations of AircraftWings |
28 AUG 2000 |
107 pages |
| Authors:
P. C. Chen; D. D. Liu; K. C. Hall; E. H. Dowell; ZONA TECHNOLOGY INC SCOTTSDALE AZ
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| This report documents the result of an STTR Phase I on the investigation in the use of a frequency-domain proper orthogonal decomposition (POD) / Reduced Order Modeling (ROM) procedure in conjunction with a harmonic balance nonlinear scheme for the prediction and analysis of limit cycle oscillations (LCO) of aircraft wings/airfoils in transonic flow regimes. A significant milestone has been reached in the phase I ... |
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| Characterization and Control of Vortex Breakdown over a Delta Wing at High Angles of Attack |
08 AUG 2000 |
380 pages |
| Authors:
Anthony M. Mitchell; AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH
|
| Demands for more maneuverable and stealthy air vehicles have encouraged the development of new control concepts for separated flows. The goal of this research is the control of leading-edge vortex breakdown by open-loop, along-the-core blowing near the apex of a delta wing to improve lift and maneuverability at high angles of attack. Control is dependent on the knowledge of and the ability to detect principle characteristics of the phenomena. Therefore, ... |
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| Experimental And Theoretical Investigation Of The Weakly Ionized Non- Equilibrium Plasma Influence On A Flow Over Bodies Of Simple Forms |
AUG 2000 |
77 pages |
| Authors:
Nicolai Makachev; TSAGI ZHUKOVSKY (RUSSIA)
|
| This report results from a contract tasking TsAGI as follows: The contractor will investigate the effects of plasma discharge on aerodynamic bodies. He will perform experiments in the supersonic and subsonic wind tunnels at TsAGI. His proposed investigation will answer fundamental questions such as: 1) Nature of the observed behavior of shock waves in (or after) clouds of gas- discharge plasma; 2) The possible influence of gas-discharge plasma on aerodynamic ... |
|
| Structural Dynamics; Recent Advances. Proceedings of the International Conference (7th), Held in Southampton, England on July 24-27 2000). Volume 1 |
27 JUL 2000 |
753 pages |
| Authors:
N. S. Ferguson; H. F. Wolfe; M. A. Ferman; S. A. Rizzi; SOUTHAMPTON UNIV (UNITED KINGDOM)
|
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| Structural Dynamics: Recent Advances. Proceedings of the International Conference (7th), Held in Southampton England on July 24-27, 2000. Volume 2 |
27 JUL 2000 |
333 pages |
| Authors:
N. S. Ferguson; H. F. Wolfe; M. A. Freeman; S. A. Rizzi; SOUTHAMPTON UNIV (UNITED KINGDOM)
|
| The Final Proceedings for Seventh International Conference on Recent Advances in Structural Dynamics, 24 July 2000 - 27 July 2000 Aeronautics and Flutter; Analytical Developments; Numerical Methods; Finite Element Methods; Nonlinear Vibration; Experimental techniques; Rotating Machines; Control; System Identification; Acoustic Fatigue and Thermal Effects; Power Flow Approaches and Impact Dynamics |
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| Aerodynamic Shape Optimization Techniques Based on Control Theory |
25 JUL 2000 |
33 pages |
| Authors:
Antony Jameson; Luigi Martinelli; PRINCETON UNIV NJ DEPT OF MECHANICAL AND AEROSPACE ENGINEERING
|
| This document serves as a final technical report for the AFOSR award F49620-95-1-0259. It reviews the formulation and application of optimization techniques based on control theory for aerodynamic shape design in viscous compressible flow. The theory is applied to a system defined by the partial differential equations of the flow, with the boundary shape acting as the control. The Frechet derivative of the cost function is determined via the solution ... |
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| Reduced Order Modeling in Control of Open Cavity Acoustics |
19 JUL 2000 |
26 pages |
| Authors:
D. M. Bortz; A. D. Rubio; H. T. Banks; A. B. Cain; R. C. Smith; NORTH CAROLINA STATE UNIV AT RALEIGH CENTER FOR RESEARCH IN SCIENTIFIC COMPUTATION
|
| Aircraft with internal carriage of weapons or surveillance systems require active control strategies to limit high amplitude open bay acoustic resonances and to facilitate optimization of structure requirements and weapon/surveillance reliability. This paper focuses on communicating an investigation of the use of numerical simulation combined with Proper Orthogonal Decomposition (POD) model reduction methods to optimize an active control system for aircraft open cavity applications. Issues ad- dressed include characterizing shear ... |
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| Semi-Automatic Domain Decomposition Based on Potential Theory |
10 JUL 2000 |
19 pages |
| Authors:
S. P. Spekreijse; J. C. Kok; NATIONAL AEROSPACE LAB AMSTERDAM (NETHERLANDS)
|
| Decomposition of a flow domain into blocks, so-called domain decomposition, is the most challenging task in the process of multi-block grid generation. In this paper, a method is described to facilitate the construction of the blocks in exterior flow domains. Layers of blocks are automatically generated by solving the Laplace equation in a region between the configuration surface and a bounding box surface. A boundary element method based on simple- ... |
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| Militarily Critical Technologies. Part III: Developing Critical Technologies. Section 1: Aeronautics Technology |
JUL 2000 |
|
| Authors:
DEFENSE THREAT REDUCTION AGENCY DULLES VA
|
| Developing Critical Technologies identifies those technologies that will produce increasingly superior performance of military systems or maintain a superior capability more affordably. The object of the document is to look beyond the Department of Defense (DoD) planning period (5+ years) and as far into the future as is reasonable. Although it may not be possible to identify all technologies that' will be used in future military ... |
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| Simulation and Analysis of Wing Rock Physics for a Generic Fighter Model with Three Degrees-of-Freedom |
JUL 2000 |
115 pages |
| Authors:
Ahmed A. Saad; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
|
| Modern fighter designs have been associated with lateral self-excited oscillations own as "Wing Rock". Simulations of wing rock by flow visualization utilities have been encouraged to develop a complete understanding of the fluid mechanism that drives fl%e motion as well as for prediction purposes. Previous windiwater tunnel simulations have been limited to a single degree-ofifreedom (DoF) in roll. In this study, for the first time, wing rock is computationally simulated ... |
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| Aeroelastic Problems Associated With External Stories and Innovative Scaling Laws for Such Problems |
30 JUN 2000 |
3 pages |
| Authors:
Peretz P. Friedmann; CALIFORNIA UNIV LOS ANGELES DEPT OF MECHANICAL AND AEROSPACE ENGINEERING
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| This AASERT grant was initially funded 7/1/95 and a Ph.D. student (Anne Le) was hired and started her studies towards a Ph. D. degree working on the problem of active control of flutter induced by stores on the wing of a typical fighter aircraft and its aeroelastic scaling. The main thrust of her research has been the development of an aeroelastic computer code capable of simulating the subsonic flutter of ... |
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| Adaptive Reconfigurable Control Based on a Reduced Order System Identification for Flutter and Aeroservoelastic Instability Suppression |
19 JUN 2000 |
74 pages |
| Authors:
C. Nam; P. C. Chen; D. D. Liu; R. M. Yurkovich; J. Urnes; ZONA TECHNOLOGY INC SCOTTSDALE AZ
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| This report documents the design of a reconfigurable adaptive control (RAC) system for flutter/aeroservoelasticity (ASE) instability suppression of battle-damaged aircraft and limit cycle oscillation (LCO) suppression of aircraft/store configurations. With the F/A-18 as a baseline aircraft, rapid suppression of its critical damage/flutter and LCO (at 5.6 and 8.8 Hz) has been successfully demonstrated through eight cases of numerical simulations studied. The developed RAC system is ... |
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| Low-Speed Wind Tunnel Tests on a Diamond Wing High Lift Configuration |
JUN 2000 |
5 pages |
| Authors:
Terence A. Ghee; Nigel J. Taylor; NAVAL AIR WARFARE CENTER AIRCRAFT DIV PATUXENT RIVER MD
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| On modem military air vehicles, high lift systems are used to improve takeoff and landing performance. For naval air vehicles, an improvement in the lift coefficient of a landing or approach configuration allows for arrested landings at reduced speeds or the ability to carry more weight back to the ship. For conventional takeoff or landing (CTOL), improved lift to drag ratios allow for shorter takeoff runs or ... |
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Aerodynamics
