| Pressure-Sensitive Paint Data on the Facility Aerodynamics Validation and Research (FAVOR) Model at AEDC |
Dec-2009 |
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| Authors:
Marvin E Sellers; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
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 | Arnold Engineering Development Center (AEDC) recently acquired the Facility Aerodynamics Validation and Operations Research (FAVOR) model for use as a standard check model for Propulsion Wind Tunnel (PWT) 16T. The test article is a 5% scale model of the F-111 with new wings having a NACA 64-210 profile, a fixed sweep angle of 35 deg, and a span of 48 in. The plan is to periodically install the model and ... |
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| Diagnostics of Flow Suppression on Rotor Blades: Final Report |
30-Sep-2009 |
37 pages |
| Authors:
James DiOttavio; Narayanan M Komerath; Vrishank Raghav; GEORGIA INST OF TECH ATLANTA OFFICE OF SPONSORED RESEARCH
|
 | In a 4-year project, the radial flow phenomena in the stalled region of rotor blades typical of retreating-blade stall were investigated. First a partial inflow obstructor was devised in order to create transient flow separation on a rotor blade in a hover facility. Next, a 2-bladed teetering rotor rig was designed, built and operated at high advance ratios appropriate for dynamic stall, in the John Harper Low Speed Wind Tunnel ... |
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| Evaporation Rates of Chemical Warfare Agents Measured Using 5 CM Wind Tunnels. 2. Munitions Grade Sulfur Mustard From Sand |
Jul-2009 |
184 pages |
| Authors:
H D Durst; Erin L Maloney; Christopher V Giannaras; Bruce E King; Joseph P Myers; Robert G Nickol; Seok H Hong; Kenneth B Sumpter; Carol A Brevett; John J Pence; SCIENCE APPLICATIONS INTERNATIONAL CORP GUNPOWDER MD
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| The evaporation of sulfur mustard from sand was studied as a function of temperature, drop size and air flow rate, using the same instrumentation as prior studies on glass. The evaporation rate increased with higher temperature, drop size, and wind speed; and an empirical equation was determined that would allow for the calculation of the evaporation rate given the environmental conditions. |
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| Enabling Technologies for Nano Air Vehicles |
10-Feb-2009 |
85 pages |
| Authors:
Jamey D Jacob; OKLAHOMA STATE UNIV STILLWATER
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| This project investigated several areas with the aim of improving performance and operational use of nano air vehicles (NAVs) by understanding fundamental operating principles and developing key technologies. The project developed plasma actuators for thrust and maneuvering control and examined flapping flight through the development of a high speed videogrammetry system and a gust/shear tunnel to replicate flow fields seen as the NAV scale. In the first portion of the ... |
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| Mathematical Fluid Dynamics of Plasma Flow Control Over High Speed Wings |
Feb-2009 |
42 pages |
| Authors:
David Marshall; Alexander V Fedorov; Victor R Soloviev; V M Krivtsov; V G Soudakov; TELEDYNE SCIENTIFIC AND IMAGING LLC THOUSAND OAKS CA
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| Develop theoretical models and computational tools for SDBD flow control applications. |
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| Hypermixer Pylon Fuel Injection for Scramjet Combustors |
11-Sep-2008 |
188 pages |
| Authors:
Jason C Doster; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT
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| Fueling the core airflow of a circular or elliptical scramjet combustor cross-section often requires intrusive geometries. Intrusive geometries can distribute the fuel evenly across the combustor cross-section and act as a flameholder for the fuel/air mixture. Compared to conventional transverse or angled wall injection, intrusive geometries allow easier penetration into the core combustor airflow and reduced fuel injection pressures. The design and testing of an intrusive pylon geometry for scramjet ... |
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| White Sands Missile Range 2007 Urban Study: Data Processing - Volume DP-1 (Sonic Calibration) |
01-Sep-2008 |
64 pages |
| Authors:
Manuel Bustillos; Sean D'Arcy; Robert Brice; Gail Vaucher; Ron Cionco; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD COMPUTATIONAL AND INFORMATION SCIENCES DIR
|
| Calibrating sensors is an important step in determining the confidence one has in the quality of data acquired. Without access to a National Institute of Standards and Technology (NIST) wind tunnel facility, side-by-side relative calibration (against a NIST calibrated sensor) is an alternate method for calibrating meteorological sensors. For the White Sands Missile Range 2007 Urban Study (W07US), a Pre- and Post-W07US calibration was conducted on the 27 ultrasonic anemometers ... |
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| Mass Remaining During Evaporation of Sessile Drop |
01-Sep-2008 |
35 pages |
| Authors:
James E Danberg; SCIENCE APPLICATIONS INTERNATIONAL CORP (SAIC) ABINGDON MD
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| A theory to predict the evaporation rate of HD (mustard agent) for the special case of a glass substrate has been developed. This is an important reference case for the wind tunnel and field test measurements of the HD evaporation rate. The HD drop is treated as a spherical segment with a constant base diameter characterized by the variation of the droplet shape factor (height to base diameter) or contact ... |
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| Evaporation of HD Droplets From Nonporous, Inert Surfaces in TGA Microbalance Wind Tunnels |
Sep-2008 |
47 pages |
| Authors:
Kenneth B Sumpter; Seok H Hong; Wendel J Shuely; Robert G Nickol; EDGEWOOD CHEMICAL BIOLOGICAL CENTER ABERDEEN PROVING GROUND MD RESEARCH AND TECHNOLOGY DIR
|
| The environmental fate of chemical warfare agents (CWAs) is important because the contact or vapor hazard is critical input for models used to support decisions on the level of individual protection at fixed sites. Two different microbalances, configured in a wind-tunnel geometry, were used to measure the evaporation and desorption rates from surfaces. The overall experimental design covers several neat and thickened agents and several material surfaces. The initial elements ... |
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| Biologically Inspired Artificial Haircell Sensors |
23-Jun-2008 |
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| Authors:
Chang Liu; ILLINOIS UNIV AT URBANA-CHAMAPIGN
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| The use and development of unmanned aircraft has significantly increased recently. As electronics packages and equipment have decreased in size and weight, so have the potential dimensions of these aircraft. The ability of these vehicles to retain acceptable lift is highly sensitive to separation of flow over the lift surface. The team developed the design and fabrication process for high sensitivity artificial haircell sensors and characterized their performances. The sensors ... |
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| Numerical Investigation of Transition in Supersonic Boundary Layers Using DNS and LES |
31 MAR 2008 |
232 pages |
| Authors:
Hermann F. Fasel; Frank Husmeier; Christian S. Mayer; ARIZONA UNIV TUCSON DEPT OF AEROSPACE AND MECHANICAL ENGINEERING
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| This work focuses on instability mechanisms of high-speed boundary layers over flat plates and cones with a circular cross section. Supersonic transition investigations at Mach 2 and hypersonic transition investigations at Mach 8 are performed using Direct Numerical Simulations (DNS). At wind-tunnel conditions, these simulations allow for comparison with experimental measurements to verify fundamental stability characteristics. For the DNS of boundary-layer transition at Mach 2, the experimental studies by Kosinov ... |
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| Combined High Temperature Aerothermal-Structural Physical Property Testing of Ceramic Matrix Composites |
MAR 2008 |
19 pages |
| Authors:
Don E. King; David G. Drewry; JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB
|
| The objective was to integrate a mechanical test apparatus into a wind tunnel flow field capable of generating controlled multi-directional stress/strain states in flat coupons exposed to appropriate chemical, thermal, and aerodynamic shear flow environments. Displacement control enables imposition of stress/strain fields (in the flat coupons) similar to those expected in complex flight component geometries. Control and measurement of these variables and the material response in a controlled environment enables ... |
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| An Assessment of Productive Computational Fluid Dynamics for Aerodynamic Design |
JAN 2008 |
24 pages |
| Authors:
Jr. Vaughn Milton E.; Lamar M. Auman; ARMY AVIATION AND MISSILE RESEARCH DEVELOPMENT ENG CTR REDSTONE ARSENAL AL SYSTEM SIMULATION AND DEVELOPMENT DIRECTORATE
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| The U.S. Army Aviation and Missile Research, Development, and Engineering Center (AMRDEC) has been applying a Government-developed, productivity-oriented, Computational Fluid Dynamics (CFD) methodology to the aerodynamic design of Army missiles. This methodology, dubbed Enter Tunnel Analysis (ETA), uses a robust Euler solver and automated grid generation software to drastically reduce the time required to set up and execute flow field computations. ETA is described and applied to two hypervelocity missile ... |
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| Fixed-Wing Micro Air Vehicles with Hovering Capabilities |
01 NOV 2007 |
17 pages |
| Authors:
Boris Bataille; Damien Poinsot; Chinnapat Thipyopas; Jean-Marc Moschetta; ECOLE NATIONALE SUPERIEURE DE L'AERONAUTIQUE ET DE L'ESPACE TOULOUSE (FRANCE)
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| Fixed-wing micro air vehicles (MAV) are very attractive for outdoor surveillance missions since they generally offer better payload and endurance capabilities than rotorcraft or flapping-wing vehicles of equal size. They are generally less challenging to control than helicopter in outdoor environment. However, high wing loading associated with stringent dimension constraints requires high cruise speeds for fixed-wing MAVs and it has been difficult so far to achieve good performances at low-speed ... |
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| Turbulence Instrumentation for Stratospheric Airships |
01-Sep-2007 |
83 pages |
| Authors:
Mark L Duell; Lawrence M Saupe; Brent E Barbeau; Kris D Robinson; George Y Jumper; AIR FORCE RESEARCH LAB HANSCOM AFB MA SPACE VEHICLES DIRECTORATE
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| Both commercial and high altitude aircraft such as the U-2 may encounter turbulence in flight. The turbulence seems to be associated with buoyancy waves generated by flow over mountains that can break into turbulence. The exact nature of the wave breaking is not fully understood, and forecast models need to be examined to determine their ability to forecast turbulence. The High Altitude Airship is designed to investigate these phenomena. In ... |
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| Comparative Study of Aerodynamic Interference During AFT Dispense of Munitions |
SEP 2007 |
173 pages |
| Authors:
Matthew G. Burkinshaw; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH DEPT OF AERONAUTICS AND ASTRONAUTICS
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| Based on forthcoming USAF needs, an investigation was launched to further the understanding of aft dispense of munitions in a high-speed environment. A computational fluid dynamics (CFD) study was performed followed by a wind tunnel experiment. The study consisted of a strut-mounted cone simulating a parent vehicle and a sting mounted cone-cylinder store situated directly behind the cone. The CFD modeled the test objects inside a supersonic wind tunnel in ... |
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| Determination of Effective Recombination Probability: Detailed Aspects of a Macroscopic Methodology |
01 JUL 2007 |
47 pages |
| Authors:
P. Rini; G. Degrez; UNIVERSITE LIBRE DE BRUXELLES (BELGIUM)
|
| The purpose of the present Lecture Series is to provide an up-to-date review of the experimental techniques, the theoretical models, as well as the numerical simulation strategies involved in the treatment of the chemical character of high temperatures gases. To this end, aspects of both materials and high temperatures uid sciences are discussed together, with the aim of enhancing the improvements in the understanding of the processes of heat release ... |
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| Leveraging Process Knowledge to Improve Modeling of Evaporation Rate Data for Agent Fate Wind Tunnels |
01-Jun-2007 |
46 pages |
| Authors:
Thomas A Donnelly; EDGEWOOD CHEMICAL BIOLOGICAL CENTER ABERDEEN PROVING GROUND MD
|
| PURPOSE OF TALK: (1) Demonstrate how the modeling (regression analysis) of evaporation rate data can be improved by rescaling the variables based on knowledge of the process (2) Describe how running the experimental design trials in specific randomized blocks -- as compared to running the planned trials in a haphazard order -- facilitates (a) A sequential model building process (b) Identifying when running more trials adds little new information. |
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| Wind Tunnel and Water Channel Investigations for Improving MAV Aerodynamic Performance |
14 MAY 2007 |
11 pages |
| Authors:
Geoffrey Spedding; Frederick Browand; John McArthur; CALIFORNIA UNIV LOS ANGELES
|
| Extensive investigations of the role of sweep in generating and/or stabilizing a leading edge vortex (LEV) in low Reynolds number (Re = 10 000) aerodynamics were made by tracing dye over wing shapes in a low-turbulence water channel. Unlike any other experiment to date, the variation in sweep was the only parameter change, all others being fixed. The airfoil shape was a cambered plate, which is close to optimal at ... |
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| A Wafer-Bonded, Floating Element Shear-Stress Sensor Using a Geometric Moire Optical Transduction Technique |
2007 |
7 pages |
| Authors:
Stephen Horowitz; Tai-An Chen; Venkataraman Chandrasekaran; Ken Tedjojuwono; Louis Cattafesta; Toshikazu Nishida; Mark Sheplak; FLORIDA UNIV GAINESVILLE MECHANICAL AND AEROSPACE ENGINEERING
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| This paper presents a geometric Moire optical-based floating-element shear stress sensor for wind tunnel turbulence measurements. The sensor was fabricated using an aligned waferbond/thin-back process producing optical gratings on the backside of a floating element and on the top surface of the support wafer. Measured results indicate a static sensitivity of 0.26 microns/Pa, a resonant frequency of 1.7 kHz, and a noise floor of 6.2/square root Hz. |
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| Real-Time Processing of Pressure-Sensitive Paint Images |
DEC 2006 |
95 pages |
| Authors:
Wirn Ruyten; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
|
| The Arnold Engineering Development Center is one of the leading aerospace test centers to use pressure-sensitive paint (PSP) technology to measure full-field pressure distributions on the surfaces of test articles in a wind tunnel. This report addresses one of the principal challenges identified prior to the start of this reporting period: automated, on-line processing of the large amounts of image data that are acquired during a typical PSP test. This ... |
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| Experimental Investigation of Pitch Control Enhancement to the Flapping Wing Micro Air Vehicle |
DEC 2006 |
135 pages |
| Authors:
Chin C. Kian; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
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| The mechanical pitching characteristic of the NPS flapping-wing Micro Air Vehicle (MAV) developed by Professor Kevin D. Jones are studied experimentally through the use of constant temperature anemometry and force balance techniques. The MAV without the main fixed-wing is placed in a laminar flow field within a low speed wind tunnel with the wake after the flapping wings characterized with a constant temperature anemometer and thrust generation measured by a ... |
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| Shock Control and Power Extraction by MHD Processes in Hypersonic Air Flow |
NOV 2006 |
31 pages |
| Authors:
Richard B. Miles; Sergey O. Macheret; PRINCETON UNIV NJ DEPT OF AEROSPACE AND MECHANICAL SCIENCES
|
| This project was a theoretical and experimental research effort on the use of MHD body forces and plasmas for boundary layer control and power extraction in supersonic flow, and on the development of new diagnostics for plasmas and for high-speed flows. The first part of this final report addresses MHD processes for control and power extraction. This section includes the constricted DC driven "snowplow arc" discharge that can potentially be ... |
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| Adaptive Stiffness Structures for Air Vehicle Drag Reduction |
01 OCT 2006 |
13 pages |
| Authors:
J. E. Cooper; MANCHESTER UNIV (UNITED KINGDOM)
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| The development of several adaptive internal structures concepts is described that are aimed towards enabling adaptive static aeroelastic shape control of an aircraft wing in flight. It is shown how changes in the position, orientation and stiffness of the internal wing structure can be used to change the bending and torsion stiffness properties of a wing, and hence the control of the aerodynamic performance, in particular the lift and drag ... |
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| Cavity-Based Injector Mixing Experiments for Supersonic Combustors With Implications on Igniter Placement (Postprint) |
OCT 2006 |
15 pages |
| Authors:
Lance S. Jacobsen; Campbell D. Carter; Andrew C. Dwenger; GOHYPERSONIC INC (GHI) DAYTON OH
|
| Mixing experiments using simultaneous acetone and NO PLIF were performed in the AFRL/PRA Test-cell 19 supersonic wind tunnel. These experiments investigated the influence of simulated plasma-torch placement in an injector-cavity configuration exposed to a supersonic crossflow. Both the simulated plasma torch and fuel injector holes injected room temperature air, respectively seeded with acetone and nitric oxide (NO). Experiments at the streamwise centerline of the rectangular wind tunnel investigated the differences ... |
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| Three Component Velocity Measurements in the Tip Vortex of a Micro-Air-Vehicle |
SEP 2006 |
88 pages |
| Authors:
Hong J. Park; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
|
| The purpose of this research was to improve the MAV that will be used for battle damage assessment and reconnaissance or local surveillance through the experiments in AFIT wind tunnel. The experiments were performed to investigate the wing displacement and wing tip vortex interaction. To conduct the experiments, telescopic survey tool and tri-axial hot-wire anemometer was utilized. The results indicate that wing tip displacement of the flexible wing was approximately ... |
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| MHD Flow Control |
SEP 2006 |
236 pages |
| Authors:
Valentin A. Bityurin; RUSSIAN ACADEMY OF SCIENCES MOSCOW INST OF HIGH TEMPERATURES
|
| This report results from a contract tasking Institute of High Temperatures RAS as follows: Task I: Renewed scientific interest has arisen throughout the world as to the potential application of Magneto Hydrodynamics (MHD) processes for advancement of flight. Among the areas of interest is the utilization of MHD as a means for enhancing the speed and range of scramjets through a concept known as MHD energy bypass. Currently. scramjet operation ... |
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| Streamwise Vorticity Effects in a Curved Diffuser with Slot Jet Flow Control (Preprint) |
JUN 2006 |
20 pages |
| Authors:
S. T. Bailie; David Car; Jordi Estevadeordal; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH FAN AND COMPRESSOR BRANCH
|
| A slot jet is used to increase the diffusion level of a curved, diffusing wind tunnel passage. The passage entrance coincides with the tunnel throat, which has respective Mach and Reynolds numbers of 0.7 and 187000 (based on throat height) and jet Reynolds numbers ranging from 10000 to 22000. Each of four presented configurations uses linear slot jet flow control at the same relative location. Three configurations include co- or ... |
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| In-Situ Study of Physical Properties and Structure of Atmospheric Ice |
31 MAY 2006 |
76 pages |
| Authors:
Victor F. Petrenko; THAYER SCHOOL OF ENGINEERING HANOVER NH
|
| This project focused on the following in situ measurements of the physical properties and structure of atmospheric ice during its growth to add to the fundamental data of atmospheric icing. (1) A new approach to determine the volumetric liquid fraction in growing atmospheric ice from in-situ measurements of capacitance and conductance was proposed. Assuming a combination model of series and parallel connections between water and ice parts of atmospheric ice, ... |
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| 3D Velocimetry Equipment for Evaluation of Real Roughness Effects in Wall Turbulence |
14 APR 2006 |
7 pages |
| Authors:
Kenneth T. Christensen; ILLINOIS UNIV AT URBANA-CHAMAPIGN
|
| This grant supported the purchase of state-of-the-art particle-image velocimetry (PIV) equipment, necessary modifications to an existing boundary-layer wind tunnel and construction of roughness panels in Support of an AFOSR core grant (FA9550-05-1-0043). The equipment proposed was meant to significantly improve the PIV spatial dynamic range achievable in the Pi's lab as well as broaden the range of Reynolds numbers that could feasibly be studied to meet the goals of the ... |
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| Experimental Analysis of Propeller Interactions With a Flexible Wing Micro-Air-Vehicle |
23 MAR 2006 |
149 pages |
| Authors:
Brian J. Gamble; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
|
| An investigation into the effects of the propeller slipstream on a flexible wing micro-air-vehicle (MAV) was conducted. The Air Force Research Lab, Munitions Directorate designed a man-portable MAV with a 24 in. wingspan and 6 in. root chord to be used for battle damage assessment and reconnaissance. Two wings have been developed for this MAV. One is a rigid carbon-fiber wing and the other consists of flexible parachute material attached ... |
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| Store Separations From a Supersonic Cone |
MAR 2006 |
109 pages |
| Authors:
Richard J. Simko; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
|
| The purpose of this research was to analyze the environment a store would travel through if ejected from a supersonic cone. This was done using the Beggar Computational Fluid Dynamics (CFD) code from the Air Force SEEK Eagle Office at Eglin Air Force Base, FL. CFD simulations were compared to experimental results from a previous AFIT thesis and conclusions were drawn based on whether or not the current wind tunnel ... |
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| Active Control of Transverse Jets for Film Cooling Applications: A Limited Statement of Work |
FEB 2006 |
30 pages |
| Authors:
D. E. Nikitopoulos; LOUISIANA STATE UNIV BATON ROUGE DEPT OF MECHANICAL ENGINEERING
|
| The objective of this project was to initiate investigation of film cooling flow control in order to improve its performance through active excitation of the film-cooling jet. A theoretical analysis was conducted and mechanisms that can play a defining role in film cooling control were identified on the basis of fundamental fluid-dynamics, prior experiments and preliminary numerical simulations. A cold flow wind-tunnel experiment incorporating a scaled-up, single film-cooling jet on ... |
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| Evaporation Rates of Decontamination Solutions From Operationally Relevant Substrates |
JAN 2006 |
30 pages |
| Authors:
Terrence G. D'Onofrio; Robert G. Nickol; Bruce E. King; GEO-CENTERS INC ABERDEEN PROVING GROUND MD
|
| The evaporation rates of two decontamination solutions, DeconGreen(TradeMark) and DF200(TradeMark), were measured from surfaces with multiple and independent methods. Evaporation was measured by mass of residual decontaminant and video image processing. A wind tunnel was used to simulate an arid climate, with a low relative humidity and high temperature. The decontamination solution, DF200(TradeMark), evaporated faster from bare and CARC-coated aluminum by a factor of approximately 2.8 compared to DeconGreen(TradeMark). |
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| Active Control Strategies to Optimize Supersonic Fuel-Air Mixing for Combustion Associated with Fully Modulated Transverse Jet in Cross Flow |
27 DEC 2005 |
63 pages |
| Authors:
C. Ghenai; G. P. Philippidis; C. X. Lin; FLORIDA INTERNATIONAL UNIV MIAMI APPLIED RESEARCH CENTER
|
| A 76 mm x 76 mm supersonic wind tunnel with variable Mach Numbers (M = 1.5 - 4) was designed and set up. The wind tunnel could support both non-reacting fuel-air mixing and combustion. A back pressure flap was added at the downstream end of the diffuser for dual mode (subsonic- supersonic) combustion studies. A high-speed imaging system was used for the visualization of pure liquid jet, aerated liquid jet ... |
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| Disturbances from Shock/Boundary-Layer Interactions Affecting Upstream Hypersonic Flow |
DEC 2005 |
132 pages |
| Authors:
Craig R. Skoch; PURDUE UNIV LAFAYETTE IN SCHOOL OF AERONAUTICS AND ASTRONAUTICS
|
| Large disturbances and decreased Mach number in the core flow were sometimes found in the downstream end of the nozzle of the Boeing/AFOSR Mach-6 Ludwieg Tube at Purdue University. The cause of the disturbances has been identified using Kulite pressure transducer, hot wire, and hot film measurements. These disturbances were found to be separations caused by shock/boundary-layer interactions in the diffuser, often originating from shocks generated at the sting support. ... |
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| Characterization of the Flow Field, Wind Speed Profiles and Turbulence Intensity in Environmental Wind Tunnels for Measurement of Agent Fate |
01 OCT 2005 |
9 pages |
| Authors:
Daniel J. Weber; John W. Molnar; Mary K. Scudder; EDGEWOOD CHEMICAL BIOLOGICAL CENTER ABERDEEN PROVING GROUND MD
|
| Surface evaporation and desorption sub-models in VLSTRACK require measurements of chemical warfare agent evaporation and desorption under environmental conditions. A 5cm square by approximately I meter wind tunnel for chemical agent measurements was developed with optional strakes and roughening elements to add turbulence. Flow was developed in the pull-mode by an electric blower system. Several candidate intake geometries were designed that allowed controlled restriction of air intake to control wind ... |
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| Effects of Boundary Layer Flow Control Using Plasma Actuator Discharges |
SEP 2005 |
125 pages |
| Authors:
Jeffrey M. Newcamp; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
|
| This study addresses the usage and effects of atmospheric plasma discharges on the near wall flow conditions for a Pak-B low-pressure turbine blade. A plasma actuator was built normal to the freestream flow in a low-speed wind tunnel. The test section of the wind tunnel had a contoured upper wall geometry designed to mimic the suction side of a Pak-B turbine blade. A high frequency ac voltage source supplied three ... |
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| Neural Network Based Adaptive Flow Control for Maneuvering Vehicles |
SEP 2005 |
34 pages |
| Authors:
J. E. Corban; An Glezer; Anthony Calise; GUIDED SYSTEMS TECHNOLOGIES MCDONOUGH GA
|
| This report documents a phase I STIR effort with the objective of developing and demonstrating effective nonlinear adaptive control of the aerodynamic flow about a dynamic body using a distributed array of synthetic jets for actuation. Design of a wind-tunnel test apparatus is presented. Motion of the model is constrained to two degrees of freedom. A conventional elevator is used to trim the model and change its dynamic characteristics. Position ... |
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| Characterization of the Global Hawk Low Pressure Turbine First Rotor |
SEP 2005 |
137 pages |
| Authors:
Timothy L. Garmoe; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
|
| The Air Force Research Laboratory, Propulsion Directorate at Wright Patterson Air Force Base has studied the performance of turbine blade geometries utilizing a large scale, low speed, drawdown wind tunnel in an effort to better understand gas turbine blade aerodynamics. Currently, the Air Force's Unmanned Aerial Vehicle (UAV) Global Hawk has been operated primarily at flight conditions other than the design point of its Allison AE3007H turbofan engine. This off ... |
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| An Experimental Investigation of the Performance of Staggered PIN-FIN array Laminar Flow Heat Exchangers |
MAR 2005 |
127 pages |
| Authors:
Matthew T. Harding; NAVAL POSTGRADUATE SCHOOL MONTEREY CA DEPT OF MECHANICAL ENGINEERING
|
| This study concentrates on the empirical characterization of a staggered pin-fin array heat exchanger placed in a modular, rectangular wind tunnel. A full analysis of the heat transfer and pressure drop behavior was conducted on various pin-fin shapes, sizes, and configurations. The study was based on airflow over a wide range of Reynolds numbers in the laminar regime. The empirical data gathered can be used to corroborate and develop better ... |
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| Experimental Study of the Subsonic Aerodynamics of a Blended Wing Body Air Vehicle with a Focus on Rapid Technology Assessment |
MAR 2005 |
157 pages |
| Authors:
David A. Gebbie; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
|
| The subsonic aerodynamic performance of a blended wing body aircraft constructed using selective laser sintering was assessed in the AFIT low-speed wind tunnel. The scaled-down model of a strike tanker aircraft consisted of a shaped fuselage and sweptback wings. The Reynolds number, based on mean wing chord, during testing was on the order of 105 while the Mach number ranged from 0.10 to 0.20. The model evaluation and analysis process ... |
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| Study of Internal and External Plasma Assisted Combustion in Supersonic Gas Flow |
JAN 2005 |
36 pages |
| Authors:
Anatoly I. Klimov; RUSSIAN ACADEMY OF SCIENCES MOSCOW INST OF HIGH TEMPERATURES
|
| The Project is devoted to basic study on the field of external and internal plasma assisted combustion. This effort consists of three Tasks: Task #1 is titled "Internal plasma assisted combustion controlled by improved plasma generators in metal channel at conditions similar to Scramjet"; Task #2 is tilted "External plasma combustion experiment in a supersonic flow (Mtilde2, Pst=1 Bar)". This is a study of flow around model F with plasma ... |
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| Oblique Wing Aerodynamics |
DEC 2004 |
3 pages |
| Authors:
Melissa A. McDaniel; Brett L. Wilks; ARMY AVIATION AND MISSILE COMMAND REDSTONE ARSENAL AL MISSILE RESEARCH DEVELOPMENT AND ENGINEERING CENTER
|
| The aerodynamic performance of a wing at an oblique deployment orientation has been found through wind tunnel testing to affect both the lateral and longitudinal stability of a cruise missile. While conventional analysis tools are insufficient for calculating the aerodynamics of an oblique wing, a suitable method has been determined for use with the USAF Missile DATCOM code. Comparisons made between wind tunnel results and Missile DATCOM calculations show that ... |
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| Laboratory Evaporation and Desorption Instrumentation Systems (Wind Tunnels) for Measuring the Environmental Fate of Toxic Chemicals: Comparison of Velocity Profiles with the Earth Surface Layer Profiles |
15 NOV 2004 |
27 pages |
| Authors:
Dan Weber; Mary Scudder; Wendel Shuely; Robert Nickol; John Molnar; EDGEWOOD CHEMICAL BIOLOGICAL CENTER ABERDEEN PROVING GROUND MD
|
|
| Evaporation of Chemical Warfare Agent HD on Glass Surface Under Various Environmental Conditions |
15 NOV 2004 |
51 pages |
| Authors:
Seok H. Hong; Kenneth B. Sumpter; Robert Nickol; Wendel Shuely; EDGEWOOD CHEMICAL BIOLOGICAL CENTER ABERDEEN PROVING GROUND MD
|
| Environmental fate of the chemical warfare agents (CWA) is receiving increasing attention, since the evaluation of the contact or vapor hazard is the critical input for models employed to support decisions to determine the individual as well as collective protection level of the combatants. Once released, CWA might evaporate and be carried by the wind, sorb into the surface material, or both. This can be a function of not only ... |
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| Further Developments in Vapor Sampling Methodology Development for Laboratory Measurement of the Environmental Fate of HD on Surfaces |
15 NOV 2004 |
20 pages |
| Authors:
Robert G. Nickol; Terrence G. D'Onofrio; Wendel J. Shuely; J. Pence; H. D. Durst; S. H. Hong; K. B. Sumpter; D. J. Weber; GEO-CENTERS INC ABERDEEN PROVING GROUND MD
|
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| Study of a Structural Plasma Influence on Characteristics of Viscous Friction and Separated Near-Surface Zone Position Under High-Speed Airflow |
NOV 2004 |
277 pages |
| Authors:
Sergey B. Leonov; RUSSIAN ACADEMY OF SCIENCES MOSCOW INST OF HIGH TEMPERATURES
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| This report results from a contract tasking Institute of High Temperatures RAS as follows: The contractor will study the application of plasma technology for drag reduction and flow control. In particular, he will investigate the change in aerodynamic friction and the flow separation point using a modulated High Frequency (HF) multi-streamer electric discharge near a model's surface. In order to measure plasma effects on the viscous friction the experiments will ... |
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| Design and Testing of a 30-Degree Sweep Laminar Flow Wing for a High-Altitude Long-Endurance Aircraft |
01 OCT 2004 |
41 pages |
| Authors:
William D. Solomon Jr; Aaron Drake; Helen L. Reed; William S. Saric; NORTHROP GRUMMAN CORP EL SEGUNDO CA INTEGRATED SYSTEMS
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| A laminar flow wing was designed for a high-altitude long-endurance flying-wing aircraft with a sweep angle of 30 degrees. The resulting wing design satisfied the lift and pitching moment requirements of the aircraft and had extensive runs of laminar flow on the upper and lower surface. A portion of the wing was tested in a low-speed wind tunnel at flight Reynolds number with an equivalent pressure distribution designed to reproduce ... |
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| Some Aspects of Submarine Design Part 1. Hydrodynamics |
OCT 2004 |
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| Authors:
P. N. Joubert; DEFENCE SCIENCE AND TECHNOLOGY ORGANISATION VICTORIA (AUSTRALIA) PLATFORM SCIENCES LAB
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| The history of submarines shows there were two significant advances in the performance of submarines, which occurred after full scientific studies were undertaken. The first was by the Germans at the end of World War II when they produced the Type 21, which could have upset the balance in the U-Boat campaign if it had arrived earlier. The second was by the US Navy with Albacore which had a submerged ... |
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WIND TUNNELS
