| CFD Transient Simulation of an Isolator Shock Train in a Scramjet Engine |
Sep 2012 |
221 pages |
| Authors:
Troy C Hoeger; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
|
 | For hypersonic flight, the scramjet engine uses an isolator to contain the pre-combustion shock train formed by the pressure difference between the inlet and the combustion chamber. If this shock train were to reach the inlet, it would cause an engine unstart, disrupting the flow through the engine and leading to a loss of thrust and potential loss of the vehicle. Prior to this work, a Computational Fluid Dynamics (CFD) ... |
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| HIFiRE-1 Preliminary Aerothermodynamic Measurements (Postprint) |
May 2012 |
37 pages |
| Authors:
Roger L Kimmel; David W Adamczak; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIRECTORATE/AERONAUTICAL SCIENCES DIV
|
| The Hypersonic International Flight Research Experimentation (HIFiRE) program is a hypersonic flight test program executed by the Air Force Research Laboratory (AFRL) and Australian Defence Science and Technology Organisation (DSTO). HIFiRE flight one flew in March 2010. Principle goals of this flight were to measure hypersonic boundary-layer transition and shock boundary layer interactions in flight. The flight successfully gathered pressure, temperature and heat transfer measurements during ascent and reentry. HIFiRE-1 ... |
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| Validation of the Chemistry Module for the Euler Solver in Unified Flow Solver |
Mar 2012 |
109 pages |
| Authors:
Jr Humphrey William C; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT
|
| In the world of computational fluid dynamics (CFD), three main types of flow regimes exist: continuum, rarified, and free molecular. Of these regimes, the rarified regime is the most difficult to model because the continuum equations don't apply and using the Boltzmann equation is too computationally expensive to use. The Unified Flow Solver (UFS) is currently being developed to solve this problem by using the kinetic continuum Euler equations where ... |
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| Testing and Modeling Ultra-High Temperature Ceramic (UHTC) Materials for Hypersonic Flight |
Nov 2011 |
134 pages |
| Authors:
Jochen Marschall; SRI INTERNATIONAL MENLO PARK CA
|
| This project focused on zirconium diboride and hafnium diboride ultra-high temperature ceramics in two main research areas: i) their thermal and electrical transport properties; and ii) their oxidation and volatilization behavior in simulated re-entry environments. The first area involved experimental studies of the thermal and electrical properties as a function of temperature, and the analysis of these results in terms of effective conductivity and Wiedemann-Franz models. Thermal diffusivity was measured ... |
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| Revolutionary Materials for Hypersonic Flight |
Oct 2011 |
18 pages |
| Authors:
A G Evans; F W Zok; C G Levi; R M McMeeking; R M Miles; Tresa M Pollock; H N Wadley; CALIFORNIA UNIV REGENTS SANTA BARBARA
|
| A team had been assembled to address challenges presented by future generations of hydrocarbon-fueled, long-range expendable missiles that operate up to Mach 7. The core issues involve robust materials and designs capable of sustaining pressure loads and extreme heat flux as well as shape-morphing components that allow efficient flight scenarios. The concepts invoke active cooling of the combustion system as well as passive cooling, through the use of heat pipes, ... |
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| Ground Test and Computation of Boundary Layer Transition on the Hypersonic International Flight Research and Experimentation (HIFiRE)-5 Vehicle |
Feb 2011 |
93 pages |
| Authors:
Roger Kimmel; David Adamczak; Ryan Gosse; Karen Berger; Shann Rufer; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIRECTORATE
|
| The HIFiRE Flight 5 payload was assessed in the NASA LaRC 20-Inch Mach 6 Air Tunnel. The primary objectives were to determine the boundary layer transition characteristics and the effectiveness trips. Boundary layer profiles were extracted from Navier-Stokes calculations of the flow field, and were used to assess trip heights in terms of typical trip correlating parameters. Leading-edge roughness was well-correlated with the R-bar-star parameter. This correlation was used to ... |
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| Analysis of EAW and ReComm Communication Schemes for Hypersonic Flight: Status Report 1 |
01-Dec-2009 |
20 pages |
| Authors:
D V Rose; C Thoma; V Sotnikov; VOSS SCIENTIFIC LLC ALBUQUERQUE NM
|
| We summarize progress in our analysis of proposed communication schemes for hypersonic vehicles in flight. Investigations into the electron-acoustic wave (EAW) communication scheme have yielded a dispersion analysis indicating that EAW modes can be generated and propagate in the plasma layer [D. V. Rose et al., Voss Sci. Rep. No. VSL-0737, Nov. 2007]. These modes can be coupled to electromagnetic waves at the plasma layer boundary for the assumption of ... |
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| Non-Equilibrium Gas Dynamics - From Physical Models to Hypersonic Flights (Dynamique des gaz non- equilibres - Des modeles physiques jusqu'au vol hypersonique) |
Sep 2009 |
|
| Authors:
NATO RESEARCH AND TECHNOLOGY ORGANIZATION NEUILLY-SUR-SEINE (FRANCE)
|
 | In-depth knowledge of gas dynamics at hypersonic speeds is required to define the environment and requirements for the design and safe operation of space vehicles, planetary probes, and rockets. Development of physical models and numerical methods has enabled major advancements in our approach to the design of vehicles, and has minimized the needs for extensive flight tests. However, there remain many challenges in our ability to model the hypersonic regime. ... |
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| Scramjet Fuel Injection Array Optimization Utilizing Mixed Variable Pattern Search With Kriging Surrogates |
Mar-2008 |
106 pages |
| Authors:
Bryan Sparkman; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
|
| Fuel-air mixing analysis of scramjet aircraft is often performed through experimental research or computational fluid dynamics (cfd) algorithms. Design optimization with these approaches is often impossible under a limited budget due to their high cost per run. This investigation uses jetpen, a known inexpensive analysis tool, to build upon a previous case study of scramjet design optimization. Mixed Variable Pattern Search (mvps) is compared to evolutionary algorithms in the optimization ... |
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| NAVO MSRC Navigator. Spring 2008 |
Jan-2008 |
25 pages |
| Authors:
NAVAL OCEANOGRAPHIC OFFICE STENNIS SPACE CENTER MS MAJOR SHARED RESOURCE CENTER
|
| FEATURED ARTICLES: Hypersonic Continuum/DSMC Methodology for Steady/Transient Missile and Re-Entry Vehicle Flowfields by J. L. Papp, R. G. Wilmoth, D. B. VanGilder, S. M. Dash, and K. Kennedy; Using ParaView for Remote Visualization on IBM AIX by Sean Ziegler; Global and Mesoscale Ensemble Forecasts of Tropical Cyclones by C. A. Reynolds, J. D. Doyle, J. Goerss, C. Amerault, C. H. Bishop, T. Holt and J. G. McLay; EINSTEIN and DAVINCI ... |
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| Laboratory Determination of Thermal Protection System Materials Surface Catalytic Properties |
01 JUL 2007 |
33 pages |
| Authors:
Jochen Marschall; SRI INTERNATIONAL MENLO PARK CA MOLECULAR PHYSICS LAB
|
| Different experimental approaches to measuring catalytic reaction efficiencies on thermal protection system materials are reviewed. Special emphasis is given to the theory and application of the diffusion tube side-arm reactor technique. In this technique, reactants diffuse into a dead-end tube and are progressively removed from the gas phase by surface reactions on the walls, establishing unique steady-state concentration profiles along the length of the tube. Reactant loss probabilities are determined ... |
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| Numerical Implementation of Surface Catalysis, Reaction, and Sublimation |
01 JUL 2007 |
21 pages |
| Authors:
Chul Park; KOREA ADVANCED INST OF SCIENCE AND TECHNOLOGY DAEJEON (KOREA)
|
| This lecture consists of three parts: 1) quantification of rates of gas-surface interaction, 2) formulation of gas-surface balance conditions, and 3) survey of the gas-surface interaction problems in the entry flights of various planets. The first part reviews the role of surface rates and flow parameters in Goulard's theory, the catalytic rates for Martian entry problem, the reaction rates for oxidation and nitridation of carbon, rough surfaces, and the relationship ... |
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| Low Cost, High-Temperature Conformal Antennas |
23 JUN 2007 |
2 pages |
| Authors:
NATIONAL CENTER FOR DEFENSE MANUFACTURING AND MACHINING LATROBE PA
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| Due to a critical need for the development of high-temperature conformal antennas to enable hypersonic flight (in excess of MACH 4), Alliant Techsystems (ATK) is evaluating materials for forming these complex shapes. The objective of this project was to develop a conformal antenna solution to meet the demands of aerodynamic heating. The project focused on the development of two formulations of HotBlox with ideal dielectric properties of 2.0 and 4.0 ... |
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| Mixing and Evaporation of Multiple Size Group JP-7 Fuel Droplets Injected into a Supersonic Air Stream - Efficiency of Cylindrical versus Rectangular Combustion Chamber |
03 May 2007 |
43 pages |
| Authors:
Fadl H Moukalled; AMERICAN UNIV BEIRUT (LEBANON)
|
| This report deals with the formulation, implementation, and testing of three numerical techniques based on (i) a full multiphase approach, (ii) a MUlti-SIze Group (MUSIG) approach, and (iii) a Heterogeneous MUSIG (H-MUSIG) approach for the prediction of mixing and evaporation of liquid droplets injected into a stream of air flowing inside a combustion chamber. The numerical procedures are formulated following a Eulerian approach, within a pressure-based fully conservative Finite Volume ... |
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| Australian DefenceScience. Volume 15, Number 4, Summer |
Jan-2007 |
|
| Authors:
DEFENCE SCIENCE AND TECHNOLOGY ORGANISATION CANBERRA (AUSTRALIA)
|
| CONTENTS: A drier Tiger is a healthier flyer - The Army's Tiger Armed Reconnaissance Helicopter (ARH), soon to be permanently based at Robertson Barracks in Darwin, faces a greatly increased threat of corrosion in the wet tropics environment of its new home. DSTO is looking into ways of reducing this threat with dehumidified hangar facilities. ANZACS declared fit for long life at sea - Since ANZAC class frigates first took ... |
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| Report from the Workshop on Communications Through Plasma During Hypersonic Flight |
29-Aug-2006 |
25 pages |
| Authors:
Charles H Jones; TEST SUPPORT SQUADRON ( 812TH) EDWARDS AFB CA
|
| This workshop concentrated on a specific problem: how to communicate through the plasma sheath generated around an air vehicle at high Mach numbers. This plasma sheath is generated at about Mach number 10 and higher and introduces a high attenuation factor--often leading to full blackout--for standard radio frequencies used in telemetry and other communications. The attendees were either experts in this field or people actively involved in applications that require ... |
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| Assessing the Potential for Improved Scramjet Performance Through Application of Electromagnetic Flow Control |
23 MAR 2006 |
176 pages |
| Authors:
Martin F. Lindsey; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
|
| Hypersonic flight using scramjet propulsion bridges the gap between turbojets and rockets. Recent efforts focus on magnetogasdynamic (MGD) flow control to mitigate the problems of high thermomechanical loads and low efficiencies associated with scramjets. This research is the first flight-scale, three-dimensional computational analysis of a realistic scramjet to assess how MGD flow control improves scramjet performance. Developing a quasi-one dimensional design tool culminated in the first open source scramjet geometry. ... |
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| Integrated Hypersonic Aerothermoelastic Methodology for Trans Atmospheric Vehicle (TAV)/Thermal Protection System (TPS) Structural Design and Optimization. Thermal Protection System Optimization (TPSOPT) |
JAN 2006 |
244 pages |
| Authors:
P. C. Chen; Xiaowei W. Gao; K. T. Chang; ZONA TECHNOLOGY INC SCOTTSDALE AZ
|
| This report was developed under a SBIR contract. The objective of this project was to develop a hypersonic aerothermoelastic methodology that optimizes the Thermal Protection System (TPS) for the Trans Atmospheric Vehicles (TAV) in the re-entry/maneuver flight phases. The outcome of this project is a Thermal Protection System Optimization (TPSOPT) software system that integrates multiple disciplines, including the hypersonic aerodynamics, aerothermodynamics, heat transfer, aeroelasticity, with an automatic optimization technique for ... |
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| Aerothermodynamic Reentry Flight Experiments - EXPERT |
OCT 2005 |
130 pages |
| Authors:
J. Muylaert; L. Walpot; H. Ottens; F. Cipollini; EUROPEAN SPACE AGENCY NOORDWIJK (NETHERLANDS)
|
| The paper addresses the ESA in flight Aerothermodynamic (ATD) research programme referred to as EXPERT: the European EXPerimental Re-entry Testbed. The objective of this in-flight research programme is to design and instrument generic configurations, for in-flight measurements of critical ATD phenomena using state-of-the-art instrumentation. Hypersonic flight data are required for improved understanding of the following critical ATD phenomena : 1) Transition, 2) Catalicity and oxidation, 3) Real gas effects on ... |
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| Analysis of the DEBI Flight Data |
02 JUN 2005 |
5 pages |
| Authors:
Peter Erdman; EMBRY-RIDDLE AERONAUTICAL UNIV DAYTONA BEACH FL
|
| The investigation of hypervelocity shocks that began with the highly successful Bowshock I and II atmospheric sounding rocket experiments continued with the DEBI flight experiment. Instruments aboard the earlier vehicles performed measurements of the ultraviolet and vacuum ultraviolet emission excited in the high temperature gas produced by the shock ahead of the hypervelocity body. With the DEBI experiment, we developed the experimental techniques and the instruments necessary to expand those ... |
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| Study of Magnetogasdynamic Flow Acceleration in a Scramjet Nozzle |
JUN 2005 |
81 pages |
| Authors:
Erik K. Ross; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
|
| The research project studied the benefits of Magnetogasdynamic (MGD) acceleration on a scramjet nozzle. MGD is a technology that relies on electromagnetic fields to extract and/or add energy to flow fields. The scramjet engine in the "AJAX" concept proposed by D.I. Brichkii et al. (2001) of St. Petersburg, Russia would utilize an MGD power generator in the diffuser user which could potentially provide electrical power for the aircraft support systems ... |
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| Test Methods for Short-Range Lethality Evaluation of Full-Scale Hypersonic Kinetic-Energy Missiles |
DEC 2004 |
8 pages |
| Authors:
G. L. Johnson; L. M. Brooks; J. L. Morton; ARMY RESEARCH DEVELOPMENT AND ENGINEERING COMMAND REDSTONE ARSENAL AL
|
| Lethality evaluation tests of anti-armor missile systems require flight-test of tactical missiles against threat targets under highly controlled impact conditions. Variables such as terminal dive angle, impact velocity, missile orientation at impact, hit-point on the target, and shot-line through the target all must be carefully controlled and documented to properly evaluate and analyze the damage caused and extrapolate this data to other impact conditions. Development missile systems have difficulty achieving ... |
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| Model and Igniter Development for Plasma Assisted Combustion |
21 JUN 2004 |
11 pages |
| Authors:
Skip Williams; Svetozar Popovic; Leposava Vuskovic; Campbell D. Carter; Lance Jacobson; AIR FORCE RESEARCH LAB HANSCOM AFB MA SPACE VEHICLES DIRECTORATE
|
| Recent progress on the authors' efforts to develop a detailed kinetic mechanism for C(sub 8)H(sub m) hydrocarbons and practical plasma igniters for plasma-assisted combustion are discussed. Shock tube validation experiments made in argon using a fixed stoichiometry (PHI = 1.0), pressures of approximately 0. 95 and 1.05 atm, and temperatures ranging from 850 to 1200 K (post-reflected shock) are presented. The mechanism is being expanded to include electron kinetics and ... |
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| Magnetogasdynamic Flow Control of a Mach Reflection |
MAR 2004 |
98 pages |
| Authors:
Brian E. Earp; AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH DEPT OF AERONAUTICS AND ASTRONAUTICS
|
| Two-dimensional regular and Mach reflections have been studied in the Mach 4.96 dual-solution domain for a 25 and 26 double-fin inlet. The steady-state computational Mach and regular reflections were subjected to magnetogasdynamic forces to determine whether these forces could be used as a possible flow control mechanism. The numerical code employed for this research solved the inviscid Euler equations with added source terms for the ponderomotive force and accompanying energy ... |
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| Magneto-Aerodynamic Hypersonics |
DEC 2003 |
7 pages |
| Authors:
F. Witzeman; AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AIR VEHICLES DIRECTORATE
|
| Favorable interactions of electromagnetic fields and weakly ionized air for flow control have been recognized since the late 1950s. Potential applications of flow control to hypersonic flight vehicles were recently demonstrated by Russian research and concepts. The scientific knowledge base of this interdisciplinary area (i.e., fluid dynamics, electromagnetics, and chemical and thermal nonequilibrium gas dynamics) is extremely sparse. Therefore, controversy and even misunderstandings are abundant in the research community. This ... |
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| 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 ... |
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| Calibration and Optimization of Constant Voltage Hot-Wire Anemometer in Hypersonic Flows |
OCT 2003 |
58 pages |
| Authors:
Ndaona Chokani; NORTH CAROLINA STATE UNIV AT RALEIGH OFFICE OF CONTRACTS AND GRANTS
|
| Freestream and boundary layer measurements are made in a supersonic flow using both constant temperature (CTA) and constant voltage (CVA) anemometry. The performance of both anemometers is systematically made by operating the same hot-wire under identical conditions and applying post-test software corrections to the fluctuating measurements. In the case of the CVA the in situ time constant of the hot wire is measured to compensate the measured CVA output. The ... |
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| Study to Determine the Effective and Cost of a Laser-Propelled Lightcraft Vehicle System - Results to Guide Future Developments |
OCT 2003 |
13 pages |
| Authors:
Froning; Pike; McKinney; Frank Mesad Jr.; Bill Larson; FLIGHT UNLIMITED FLAGSTAFF AZ
|
| This document is a report of a study to determine the effective and cost of a laser-propelled lightcraft vehicle system - results to guide future developments. |
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| 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. |
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| Feasibility of SCRAMJET Technology for an Intermediate Propulsive Stage of an Expendable Launch Vehicle |
SEP 2002 |
119 pages |
| Authors:
Michael D. Schafer; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| The single largest contributor to the cost of pulling objects into space is that of the launch portion. The currently available chemical rockets are only capable of specific impulse (Isp) values on the average of 300-350 seconds, with a maximum of 450 seconds. In order to improve the performance of the current families of launch vehicles, it is necessary to increase the performance of the rocket motors, and conversely the ... |
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| Endothermic Heat-Sink of Hydrocarbon Fuels for Scramjet Cooling AIAA 2002-3871 |
JUL 2002 |
|
| Authors:
H. Huang; D. R. Sobel; L. J. Spadaccini; UNITED TECHNOLOGIES RESEARCH CENTER EAST HARTFORD CT
|
| Storable liquid hydrocarbon fuels, such as JP-7, JP-8+ 100, and JP- 10, that can undergo endothermic reactions may provide sufficient heat sink to enable hypersonic flight without having to resort to cryogenic fuels. The objective of this research is to develop and demonstrate the endothermic potential of these fuels for hypersonic scramjet cooling. A high- pressure bench-scale reactor was used to determine the overall heat sinks (including endotherm), endothermic reforming ... |
|
| JANNAF Airbreathing Propulsion Subcommittee Meeting (26th) Held in Bayside Inn, The Sandestin Resort, Eglin Air Force Base, Destin, Florida on 8-12 April 2002. Volume I |
APR 2002 |
|
| Authors:
Ronald S. Fry; Mary T. Gannaway; CHEMICAL PROPULSION INFORMATION AGENCY COLUMBIA MD
|
| This volume, the first of four volumes, is a collection of 28 unclassified/unlimited-distribution papers which were presented at the Joint Army-Navy-NASA-Air Force (JANNAF) 26th Airbreathing Propulsion Subcommittee (APS) was held jointly with the 38th Combustion Subcommittee (CS), 20th Propulsion Systems Hazards Subcommittee (PSHS), and 2nd Modeling and Simulation Subcommittee. The meeting was held 8-12 April 2002 at the Bayside Inn at The Sandestin Golf & Beach Resort and Eglin Air ... |
|
| 38TH JANNAF Combustion Subcommittee Meeting. Volume I |
APR 2002 |
|
| Authors:
Ronald S. Fry; Debra S. Eggleston; Mary T. Gannaway; CHEMICAL PROPULSION INFORMATION AGENCY COLUMBIA MD
|
| This volume, the first of two volumes, is a collection of 55 unclassified/unlimited-distribution papers which were presented at the Joint Army-Navy-NASA-Air Force (JANNAF) 38th Combustion Subcommittee (CS), 26th Airbreathing Propulsion Subcommittee (APS), 20th Propulsion Systems Hazards Subcommittee (PSHS), and 2nd Modeling and Simulation Subcommittee. The meeting was held 8-1 2 April 2002 at the Bayside Inn at The Sandestin Golf & Beach Resort and Eglin Air Force Base, Destin, Florida. ... |
|
| 2ND JANNAF Modeling & Simulation Subcommittee Meeting. Volume I |
APR 2002 |
|
| Authors:
CHEMICAL PROPULSION INFORMATION AGENCY COLUMBIA MD
|
| This volume, the first of two volumes, is a collection of 26 unclassified/unlimited-distribution papers which were presented at the Joint Army-Navy-NASA-Air Force (JANNAF) 2nd Modeling and Simulation Subcommittee (MSS) held jointly with the 38th Combustion Subcommittee (CS), 26th Airbreathing Propulsion Subcommittee (APS), and 20th Propulsion Systems Hazards Subcommittee (PSHS). The meeting was held 8-12 April 2002 at the Bayside Inn at The Sandestin Golf & Beach Resort and Eglin Air ... |
|
| Reevaluation of Window-Cooling Test Data: HEDI Window-Cooling Test in the AEDC HR Arc Heater |
09 NOV 2000 |
11 pages |
| Authors:
J. H. Stewart; E. J. Felderman; SVERDRUP TECHNOLOGY INC ARNOLD AFS TN
|
| Multiple experiments were conducted in the late 1980's and early 1990's to determine the effectiveness of transpiration and film cooling on the temperature control of an infrared (IR) seeker window during a missile's hypersonic flight. These efforts were made in support of the United States Army Space and Strategic Defense Command (USA SSDC) High-Endoatmospheric Defense Interceptor (HEDI) program. The experiments were designed as a series of complementary tests in several ... |
|
| JANNAF 25th Airbreathing Propulsion Subcommittee, 37th Combustion Subcommittee and 1st Modeling and Simulation Subcommittee Joint Meeting. Volume 1 |
NOV 2000 |
|
| Authors:
Ronald S. Fry; Dorothy L. Becker; CHEMICAL PROPULSION INFORMATION AGENCY COLUMBIA MD
|
| Volume I, the first of three volumes, is a compilation of 24 unclassified/unlimited-distribution technical papers presented at the Joint Army-Navy-NASA-Air Force (JANNAF) 25th Airbreathing Propulsion Subcommittee, 37th Combustion Subcommittee and 1st Modeling and Simulation Subcommittee (MSS) meeting held jointly with the 19th Propulsion Systems Hazards Subcommittee. The meeting was held 13-17 November 2000 at the Naval Postgraduate School and Hyatt Regency Hotel, Monterey, California. Topics covered include: a Keynote Address ... |
|
| Extrapolation from High Enthalpy Tests to Flight Based on the Concept of Local Heat Transfer Simulation |
APR 2000 |
14 pages |
| Authors:
A. F. Kolesnikov; INSTITUTE FOR PROBLEMS IN MECHANICS MOSCOW (USSR)
|
| The concept of the local heat transfer simulation (LHTS) of the high enthalpy flow action on a vehicle stagnation point formulated in refs. 1, 2 is based on the requirement to locally provide in a ground test the same boundary layer on the model at the stagnation point as at the re- entry conditions. The present methodology of the extrapolation from ground to flight consists of the three main parts: ... |
|
| Coordinated Development of DSMC Plume and Contamination Models |
27 JAN 2000 |
15 pages |
| Authors:
Jay Levine; Ingrid Wysong; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST
|
|
| Aerospace Technologies of the 21st Century: New Technologies of Experimental Research and Simulation Held in Berlin, Germany on 8-9 June 2000 |
2000 |
120 pages |
| Authors:
TSAGI ZHUKOVSKY (RUSSIA)
|
| The Final Proceedings for Aerospace Technologies of the XXI Century New Technologies of Experimental Research & Simulation, 8 June 2000 - 9 June 2000 This is an interdisciplinary conference. Topics include: Test Facilities and New Capabilities for Experimental Research; New Technologies of Experimental Research; Advances in the Field of Simulation; Investments in Aerospace; Advanced Technologies Commercialisation. |
|
| High-Speed Flight and the Military |
APR 1999 |
60 pages |
| Authors:
Matthew H. Molloy; AIR COMMAND AND STAFF COLL MAXWELL AFB AL
|
| This paper makes a qualitative assessment of NASA's High-Speed Research program and its associated High-Speed Civil Transport (HSCT) program to answer the question of whether or not this Mach 2.4-class, 300 passenger transport and its supersonic business jet (SSBJ) counterpart could have value to future military operations. This research found that supersonic transports such as the HSCT and the SSBJ could be in production within 10-20 years. Based on the ... |
|
| Development of the Aerodynamic/Aeroservoelastic Modules in ASTROS. Volume 3. ZAERO Applications Manual |
04 FEB 1999 |
120 pages |
| Authors:
P. C. Chen; D. Sarhaddi; D. D. Liu; A. G. Striz; ZONA TECHNOLOGY INC SCOTTSDALE AZ
|
| This report is a part of the documentations which describe the complete development of an STTR Phase 2 effort entitled, Development of the Aerodynamic/Aeroservoelastic Modules in ASTROS. This report is one of four manuals that comprise the final report. The remaining reports consist of the ZAERO User's Manual (Volume 1), the ZAERO Programmer's Manual (Volume 3) and the ZAERO Theoretical Manual (Volume 4). ASTROS is the ... |
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| Development of the Aerodynamic/Aeroservoelastic Modules in ASTROS. Volume 1. ZAERO User's Manual |
04 FEB 1999 |
88 pages |
| Authors:
P. C. Chen; D. Sarhaddi; D. D. Liu; ZONA TECHNOLOGY INC SCOTTSDALE AZ
|
| This report is a part of the documentations which describe the complete development of an STTR Phase 2 effort entitled, Development of the Aerodynamic/Aeroservoelastic Modules in ASTROS. This report is one of four manuals that comprise the final report. The remaining reports consist of the ZAERO Programmer's Manual (Volume 2), the ZAERO Applications Manual (Volume 3) and the ZAERO Theoretical Manual (Volume 4). ASTROS is ... |
|
| Development of the Aerodynamic/Aeroservoelastic Modules in ASTROS. Volume 2. ZAERO Programmer's Manual |
04 FEB 1999 |
105 pages |
| Authors:
P. C. Chen; D. Sarhaddi; D. D. Liu; ZONA TECHNOLOGY INC SCOTTSDALE AZ
|
| This report is a part of the documentations which describe the complete development of an STTR Phase 2 effort entitled, Development of the Aerodynamic/Aeroservoelastic Modules in ASTROS. This report is one of four manuals that comprise the final report. The remaining reports consist of the ZAERO User's Manual (Volume 1), the ZAERO Applications Manual (Volume 3) and the ZAERO Theoretical Manual (Volume 4). ASTROS is the ... |
|
| Development of the Aerodynamic/Aeroservoelastic Modules in ASTROS. Volume 4. ZAERO Theoretical Manual |
04 FEB 1999 |
160 pages |
| Authors:
P. C. Chen; D. Sarhaddi; D. D. Liu; ZONA TECHNOLOGY INC SCOTTSDALE AZ
|
| This report is a part of the documentations which describe the complete development of an STTR Phase 2 effort entitled, Development of the Aerodynamic/Aeroservoelastic Modules in ASTROS. This report is one of four manuals that comprise the final report. The remaining reports consist of the ZAERO User's Manual (Volume 1), the ZAERO Programmer's Manual (Volume 2) and the ZAERO Applications Manual (Volume 3). ASTROS is the ... |
|
| Direct Fuel Cooled Composite Structure |
1999 |
6 pages |
| Authors:
Denis G. Medwick; Joaquin H. Castro; David R. Sobel; Jean-Pierre Vidal; Guy Boyet; PRATT AND WHITNEY WEST PALM BEACH FL
|
| One of the more challenging aspects of hypersonic propulsion systems is the development of lightweight structure that can withstand the severe conditions associated with flight up to Mach 8. Currently, the Pratt & Whitney expendable scramjet engine concept utilizes a metallic combustor, based upon high temperature alloys with integral, endothermic fuel cooling. There is the potential for reduction in propulsion system weight and cost, and ... |
|
| Hypersonic Missile Propulsion System |
NOV 1998 |
|
| Authors:
Richard R. Kazmar; PRATT AND WHITNEY WEST PALM BEACH FL
|
| Pratt & Whitney is developing the technology for hypersonic components and engines. A supersonic combustion ramjet (scramjet) database was developed using hydrogen fueled propulsion systems for space access vehicles and serves as a point of departure for the current development of hydrocarbon scramjets. The Air Force Hypersonic Technology (HyTech) Program has put programs in place to develop the technologies necessary to demonstrate the operability, performance and ... |
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| Space Shuttle East Coast Abort Modes for High Inclination Launches |
DEC 1997 |
89 pages |
| Authors:
Richard K. Neufang; AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH
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| This study investigated the possibility of abort landing the Space Shuttle at east coast airports when launched at inclinations of 51.6 degrees or more. Computer modeling was used to characterize both the Shuttle launch out of Cape Canaveral and two methods of unpowered abort descents from various points in the launch following Solid Rocket Booster (SRB) separation. The first method used varying values of pitch and roll held constant to ... |
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| Concept of a Synergetic Air-Breathing Engine for Hypersonic Flight |
AUG 97 |
29 pages |
| Authors:
Yury Lobanovsky; CENTRAL AERODYNAMIC INST MOSCOW (RUSSIA)
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| This report results from a contract tasking Central Aerohydrodynamics Institute as follows: The contractor will investigate an analysis of main characteristics of turbo-compressor engine new design for hypersonic flight as per his 8 Mar 95 proposal. |
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| CO2 Vibrational Relaxation Effects in a Laser Heated Hypersonic Flow |
JUN 1997 |
17 pages |
| Authors:
C. C. Limbaugh; J. A. Drakes; SVERDRUP TECHNOLOGY INC ARNOLD AFS TN
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| The establishment of flow conditions characteristic of hypersonic flight in a ground test facility by conventional means requires plenum conditions that have very high temperatures and give rise to a variety of materials problems. A well-known approach to solving these problems is to use high-pressure, moderate temperature plenum conditions and add energy as the flow expands through a carefully designed nozzle. A modern approach (Radiatively Heated Wind Tunnel) uses an ... |
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| Propulsion and Energy Issues for the 21st Century |
MAR 97 |
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| Authors:
ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRAN CE)
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| The report provides an overall projection and perspective of possible propulsion and energy technological capabilities. The 'Hypersonic Air Breathing Missile' is propelled by a liquid hydrocarbon fueled scramjet engine for Mach numbers of 5-8. An overview of merits, payoffs and critical technology development and demonstration needs of such an air breathing hypersonic missile, and Key Technology Development Requirements are presented. Technology Overviews are also presented on: turbomachinery propulsion; advanced technology ... |
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Reports by Keyword(s)
HYPERSONIC FLIGHT
