SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS
A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 43, ISSUE 13 - JULY 1, 2005
02 AERODYNAMICS
Includes aerodynamics of flight vehicles, test bodies, airframe components and combinations, wings, and control surfaces.
Also includes aerodynamics of rotors, stators, fans, and other elements of turbomachinery.
For related information see also 34 Fluid Mechanics and Thermodynamics.
20050177343 Air Force History Support Office, Bolling AFB, Washington, DC USA
A Career in Test and Evaluation: Reflections and Observations
Hallion, Richard P.; Jan. 1998; 215 pp.; In English Report No.(s): AD-A433209; No Copyright; Avail: CASI; A10, Hardcopy Charles E. ‘Pete’ Adolph retired as Director of Test and Evaluation in the Office of the Under Secretary of Defense (Acquisition and Technology) on 31 January 1994.
This completed more than 30 years of federal service almost all of it within the challenging field of test and evaluation (T&E). Pete-as he was widely known throughout the Department of Defense testing community- enjoyed a remarkable career. It began in the late 1950s, as the heroic era of flight test in the first decade of the jet age was drawing to a close. Pete then played an increasingly prominent role in the transformation of flight testing into a systematic discipline using the latest in information technology to evaluate sophisticated weapon systems. His government career culminated as a senior director at the Office of the Secretary of Defense (OSD). There, in the Pentagon. he brought his many years of engineering and management experience in the field to bear upon the formulation of policies for the acquisition and testing of weapon systems in the post-cold-war era. The text that follows began as a series of five oral history interviews conducted in the Office of the Air Force Historian between 29 July 1993 and 15 April 1994. Ms. Pauline Tubbs of the USA Air Force Historical Research Agency at Maxwell Air Force Base (AFB), Alabama, expertly transcribed these interviews from approximately eight hours of audio tape. Mr. Lawrence R. Benson, the Air Force Historian’s Assistant for Field Programs (and previously the Director of Research Services at the Air Force Operational Test and Evaluation Center), organized, revised, and edited the transcript adding explanatory material in brackets or footnotes as appropriate. Mr. Adolph was accompanied at most of the interviews by Mr. Douglas Nation of the 46th Test Wing at Eglin AFB, Florida, who was on a special assignment to the OSD T&E Directorate. DTIC
Evaluation; Flight Tests; Industries; Military Technology; Occupation; Research and Development; System Effectiveness
20050177367 Moscow State Univ., Russia
| |
| Tools for Aviation/Aerospace |
| IHS sells products and services designed to meet the needs of today's engineers. To learn more, and for a free quote, please complete the form below. |
|
Parameters of Electrode Ignition Discharges in Supersonic Propane-Air Flows
Ershov, A .P.; Surkont, O. S.; Timofeev, I. B.; Chernikov, V. A.; Shibkov, V. M.; Ardelyan, N. V.; Chuvashev, S. N.; Bychkov,V. L.; Gromov, V. G.; Levin, V. A.; Oct. 2003; 11 pp.; In English; Original contains color illustrations Report No.(s): AD-A433246; No Copyright; Avail: Defense Technical Information Center (DTIC)
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.
DTIC
Electrodes; Ignition; Ramjet Engines; Supersonic Flow; Thermochemistry
20050177437 Air Force Research Lab., Hanscom AFB, MA USA
Reactions and Thermochemistry of Alkyl Ions, Cn H2n+1 + (n=1-8), in the Gas Phase
Williams, Skip; Miller, Thomas M.; Knighton,W. B.; Midey, Anthony J.; Arnold, Susan T.; Viggiano, A. A.; Carter, Campbell D.; Oct. 2003; 26 pp.; In English; Original contains color illustrations
Report No.(s): AD-A433360; No Copyright; Avail: Defense Technical Information Center (DTIC)
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 resulting kinetic and thermodynamic data are being used to develop detailed kinetic mechanisms for incorporation into CFD models. In the present contribution, reaction rate measurements and thermochemical computations pertaining to alkyl ions, CnH2n+1 + (n=1-8) are incorporated into a detailed combustion mechanism, and calculations of the ignition delay time are performed. The result of the ignition delay time for an isooctane/02/Ar/NO mixture to be used in shock tube ignition studies is presented. DTIC
Alkyl Compounds; Ions; Thermochemistry; Vapor Phases
20050177505 California State Univ., Los Angeles, CA USA
| |
| Aerospace Engineering Design |
| ESDU packages provide validated design data, methods and software, offering a valuable toolset to aerospace engineers. To learn more, and for a free quote, please complete the form below. |
|
Multidisciplinary Analysis and Control of High Performance Air Vehicles
Mirmirani, Maj Dean;Wu, Chivey; Boussalis, Helen; Ioannou, Petros; May 2005; 265 pp.; In English; Original contains colorillustrations —Contract(s)/Grant(s): F49620-01-1-0489 Report No.(s): AD-A433465; AFRL-SR-AR-TR-05-0161; No Copyright; Avail: Defense Technical Information Center (DTIC)
Funds provided through the DoD Infrastructure Support for HBCU/MI grant awarded to California State University, Los Angeles (Cal State LA) by the Air Force Office of Scientific Research (AFSOR) Dynamic Systems and Control on August 2001 were used for development of significant infrastructure of research, competency and capabilities in multidisciplinary modeling and control design of high-performance air vehicles. The investigators established a state-of-the-art research facility at CSULA-the Multidisciplinary Flight Dynamic and Control Laboratory (MFDCLab, www.calstatela.edu/centers/mfdclab) where novel methodologies and tools for accurate modeling, simulation, and control system design for high-performance air vehicles were developed. The accomplishments of this project include: The Rapid Conceptual Design Testbed. Nonlinear Adaptive Flight Control Laws. Aeroservoelasticity Hypersonic Vehicles. Human Resource Development. Integration of Research into Curriculum. Collaboration and Synergies. Leveraging the Grant. DTIC
Flight Control; Hypersonic Vehicles
20050177516 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
Free-to-Roll Study of Uncommanded Lateral Motions for the Vented Strake F/ A-18E/F
Melendez Bryant, Elaine; May 2005; 65 pp.; In English Report No.(s): AD-A433485; CI04-1074; No Copyright; Avail: CASI; A04, Hardcopy
A free-to-roll study was conducted on the lateral characteristics of a 10% scale model pre-production vented strake F/A-18E/F. This study carried out both static force and moment tests along with free-to-roll tests to determine the correlation to previous studies, assess the lateral motion, and verify free-to-roll as a viable test technique for the determination of uncommanded lateral motion potential. Static force and moment tests established correlation with previous studies. Using a figure of merit, the free-to-roll tests captured the angle of attack range over which the wing drop occurred in flight tests. Based on the equation of motion, the possible contributors to the lateral motion were: the character of the forcing function, the static lateral stability and roll damping. To determine the causal contributions three different angles of attack were analyzed, verifying the importance of free-to-roll as a viable test technique when used in conjunction with static test results. DTIC
Fighter Aircraft; Jet Aircraft; Roll; Strakes
20050177869 NASA Lewis Research Center, Cleveland, OH, USA
A Vision in Aeronautics: The K-12 Wind Tunnel Project Research and Technology
1996; March 1997; 3 pp.; In English; No Copyright; Avail: CASI; A01, Hardcopy
A Vision in Aeronautics, a project within the NASA Lewis Research Center’s Information Infrastructure Technologies and Applications (IITA) K-12 Program, employs small-scale, subsonic wind tunnels to inspire students to explore the world of aeronautics and computers. Recently, two educational K-12 wind tunnels were built in the Cleveland area. During the 1995-1996 school year, preliminary testing occurred in both tunnels. Author
Subsonic Wind Tunnels; Educational Resources; Wind Tunnel Tests; Schools
20050179334 NASA Lewis Research Center, Cleveland, OH, USA, Allison Engine Co., Indianapolis, IN, USA
Flow Analysis of a Gas Turbine Low- Pressure Subsystem
Veres, Joseph P.; Research and Technology 1996; March 1997; 3 pp.; In English; No Copyright; Avail: CASI; A01, Hardcopy
The NASA Lewis Research Center is coordinating a project to numerically simulate aerodynamic flow in the complete low-pressure subsystem (LPS) of a gas turbine engine. The numerical model solves the three-dimensional Navier-Stokes flow equations through all components within the low-pressure subsystem as well as the external flow around the engine nacelle. The Advanced Ducted Propfan Analysis Code (ADPAC), which is being developed jointly by Allison Engine Company and NASA, is the Navier-Stokes flow code being used for LPS simulation. The majority of the LPS project is being done under a NASA Lewis contract with Allison. Other contributors to the project are NYMA and the University of Toledo. For this project, the Energy Efficient Engine designed by GE Aircraft Engines is being modeled. This engine includes a low-pressure system and a high-pressure system. An inlet, a fan, a booster stage, a bypass duct, a lobed mixer, a low-pressure turbine, and a jet nozzle comprise the low-pressure subsystem within this engine. The tightly coupled flow analysis evaluates aerodynamic interactions between all components of the LPS. The high-pressure core engine of this engine is simulated with a one-dimensional thermodynamic cycle code in order to provide boundary conditions to the detailed LPS model. This core engine consists of a high-pressure compressor, a combustor, and a high-pressure turbine. The three-dimensional LPS flow model is coupled to the one-dimensional core engine model to provide a ‘hybrid’ flow model of the complete gas turbine Energy Efficient Engine. The resulting hybrid engine model evaluates the detailed interaction between the LPS components at design and off-design engine operating conditions while considering the lumped-parameter performance of the core engine. Author
Aerodynamic Characteristics; Gas Turbine Engines; High Pressure; Low Pressure; Compressors; Three Dimensional Flow
20050180493 NASA Lewis Research Center, Cleveland, OH, USA
Oscillating Cascade Aerodynamics at Large Mean Incidence Angles
Buffum, Daniel H.; Research and Technology 1996; March 1997; 2 pp.; In English; No Copyright; Avail: CASI; A01, Hardcopy
In a cooperative program with Pratt & Whitney, researchers obtained fundamental separated flow unsteady aerodynamic data in the NASA Lewis Research Center’s Oscillating Cascade. These data fill a void that has hindered the understanding and prediction of subsonic and transonic stall flutter. For small-amplitude torsional oscillations, unsteady pressure distributions were measured on airfoils with cross sections representative of an advanced, low-aspect-ratio fan blade. Data were obtained for two mean incidence angles with a subsonic inflow. At high mean incidence angles (alpha = 10 deg), the mean flow separated at the leading edge and reattached at about 40 percent of the chord. For comparison purposes, data were also obtained for a low incidence angle (a = 0 deg) attached flow. Author
Separated Flow; Unsteady Aerodynamics; Aerodynamic Stalling; Subsonic Flutter; Transonic Flutter; Incidence
Source: NASA.
|
IHS sells products and services designed to meet the needs of today's aviation & aerospace engineers, including:
- Quick access to FAA, JAA, ICAO and UK-CAA information and regulations.
- Validated engineering methods, data, principles, worked examples, programs and related equations on over 1340 specific aerospace, process, structural and mechanical engineering topics.
- The IHS Fasteners eCatalog, providing decision support for the identification, specification and sourcing of aerospace & defense standard fasteners/hardware such as bolts, screws, nuts, washers, rivets, studs, etc.
- Standards documents and collections from the top aerospace & aviation standards development organizations, including SAE International, AIAA, AIA, FAA and NASA.
|