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Hypersonic aerodynamics Aerodynamic Engine/Airframe Integration for High Performance Aircraft and Missiles This is Research and Technology Organization (RTO) AGARD-CP-498, dated September 1992. The objective of the symposium was to review the state-of-the-art in aerodynamic engine/airframe integration techniques and to report on the progress which has been achieved during engineering project work in recent years. Because the treatment of this subject requires an interdisciplinary approach, both experimentalists and theoreticians were invited to contribute to the meeting. Six sessions were organized to cover the essential subdisciplines requiring aerodynamic engine/airframe integration during the concept-assessment and design phases for new aerospace vehicles. For individual titles, see N93-13200 through N93-13231. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (** MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. Aerothermodynamics and Propulsion Integration for Hypersonic Vehicles This is Research and Technology Organization (RTO) AGARD Report, AGARD-R-813, dated October 1996. It was sponsored by the Advisory Group for Aerospace Research and Development for the AGARD Fluid Dynamics Panel (FDP). The following topics are covered: Aerothermodynamics of radiation-cooled surfaces; real-gas and strong interaction phenomena; hypersonic laminar-turbulent transition and turbulence modeling; configurational aerothermodynamics of reentry vehicles (winged and capsule) as well as RAM and SCRAM propelled vehicles; RAM and SCRAM inlet and propulsion integration; hypersonic missile aerothermodynamics and stage separation for two-stage launch configurations. In addition, the Hypersonic Aerothermodynamic Program at VKI was presented as well as a Navier Stokes-solver for hypersonic applications. The material assembled in this report was prepared under the combined sponsorship of the AGARD Fluid Dynamics Panel, the Consultant and Exchange Program of AGARD, and the von Karman Institute (VKI) for Fluid Dynamics. For individual titles, see N97-14778 through N97-14790. Bibliographic details and an abstract are available in HTML format and the full text is available in PDF format (29 Mb)from the RTO's web site. Allied Aerospace The Company provides a broad range of aerospace and defence products, services, and testing facitities. Allied Aerospace was formed in 1999 by the acquisition of GASL, Inc., Dynamic Engineering Inc., and Micro Craft, Inc. The company has five primary business areas: Propulsion Systems; test rigs and components (fans, compressors, turbines); Aerospace Systems; prototype and test hardware (fixed wing aircraft, rotary wing aircraft, missiles); Wind Tunnel Test Services (two wind tunnels providing low speed, transonic, and supersonic flows); Unmanned Systems (UAVs); and Field Services (technical and management services to NASA and DoD). Perhaps Allied's best known products to date are the X-43 family of hypersonic test vehicles for NASA's Hyper-X Programme. The web site describes the company's products and services and provides news and employment information. Analysis of Hypersonic Aircraft Inlets Using Flow Adaptive Mesh Algorithms This web site provides access to a North Carolina State University PhD dissertation in Aerospace Engineering, by Michael Dean Neaves, dated March 27, 2001. The study consists of numerical investigation into the dynamics of unsteady inlet flowfields applied to a three-dimensional scramjet inlet-isolator-diffuser geometry designed for hypersonic type applications. Bibliographic and abstract details are available in HTML format. The title page, contents and the full text of the document are accessible online in PDF format (4,355,762 Bytes). This title is part of North Carolina State University's Electronic Theses and Dissertations Project. Capsule Aerothermodynamics This is Research and Technology Organization (RTO) AGARD Report, AGARD-R-808, dated May 1997. The material assembled in this report was prepared under the combined sponsorship of the AGARD Fluid Dynamics Panel, the Consultant and Exchange Program of AGARD, and the von Karman Institute (VKI) for Fluid Dynamics. Aerodynamic design aspects related to planetary probe and capsule configurations are covered, as well as critical phenomena occurring during the different regimes of flight. The impact of real gas and rarefaction on capsule aerothermodynamics, and in particular on forebody and wake flow, is addressed. Bibliographic details and an abstract are available in HTML format and the full text is available in PDF format (68 Mb)from the RTO's web site. Computational Aerodynamic Analysis of the Flow Field About a Hypervelocity Test Sled This is the full text of a thesis by Andrew J. Lofthouse which was presented to the Air Force Institute of Technology (AFIT) in 2002. The flow field about the nose section of a hypervelocity test sled is computed using computational fluid dynamics. The numerical model of the test sled corresponds to the Nike O/U narrow gage sled used in the upgrade program at the High Speed Test Track facility, Holloman Air Force Base, New Mexico. The high temperatures and pressures resulting from the aerodynamic heating and loading affect the sled structure and the performance of the vehicle. The sled transitions from an air environment to a helium environment at a speed of approximately 3,300 feet per second (Mach 3 in air, Mach 1.02 in helium) to reduce the effects of high Mach number flows. Steady, three-dimensional, inviscid flow solutions are computed for Mach numbers of 2 and 3 in air (2,200 and 3,300 feet per second), and for Mach numbers of 1.02, 2.5 and 3.1 in helium (3,300, 8,076 and 10,000 feet per second). Mesh adaptation is used to obtain a mesh-independent solution. Second-order solutions are obtained for the Mach 3 in air and Mach 1.02 in helium cases. The unsteady transition from air to helium at 3,300 feet per second is also modeled. Mach 3 in air computations are compared with analytical results. [Taken from abstract]. The full text of the thesis is available in PDF format and is provided by the Air University ResearchWeb site. Computational and Experimental Assessment of Jets in Cross Flow This is Research and Technology Organization (RTO) AGARD-CP-534, dated November 1993. The 37 papers prepared for the AGARD Fluid Dynamics Panel (FDP) Symposium on Computational and Experimental Assessment of Jets in Cross Flow are included. The primary objective of the Symposium was to provide a forum for assessing advances made in the technology and application of jets in cross flow which have occurred since the last meeting on this subject. Major topics covered included enhanced descriptions of the fundamental flow structure of jets in cross flow, experimental methods, thrust vectoring, jet impingement and exhaust gas reingestion, hypersonic crossflow, and numerics and turbulence modeling. For individual titles, see N94-28004 through N94-28040. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (108.25MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. Critical Technologies for Hypersonic Vehicle Development This is a NATO Research and Technology Organization (RTO) Educational Note, RTO-EN-AVT-116, Paris, December 2005. The material in this publication was assembled to support a Lecture Series under the sponsorship of the Applied Vehicle Technology Panel (AVT) held at the von Kármán Institute, Rhode-St-Genèse, Belgium, 14-18 May 2004. This RTO/VKI Lecture Series was focused on critical technologies in hypersonic vehicle development, including ground test, numerical simulation and flight test. The introduction comprised a historical overview on hypersonic vehicle development as well as a thorough review of ongoing vehicle development and flight-testing programs. To provide sufficient background information, lectures were presented on compressible flows of perfect and imperfect gases, with special attention given to shock-wave boundary-layer interactions, laminar to turbulent transition, and high temperature gas properties. Advancements in computational modeling capabilities for hypersonic vehicle design were addressed, and the ongoing need for validation data, as well as a consistent validation methodology, where highlighted. Specific critical technology areas, including trajectory aerothermal environment definition, system trade studies, propulsion systems, aerodynamic control laws, flight instrumentation, thermal protection systems and flight experiments were all addressed in separate lectures given by international experts. In all of the presentations the needs of future hypersonic flight vehicle development programs were addressed. Bibliographic and abstract details are available in HTML format. A table of contents, individual papers and the full text of the document (41.5 Mb) can be accessed online in PDF format DARPATech 2004 This site provides the slides and scripts of presentations (PDF format) given at the DARPATech symposium which was held in Anaheim, California on 9-11 March 2004. Topics addressed include hypersonic flight, precision urban combat, tactical surveillance, chemical, biological and radiological defence, optical sensing and exploitation, advanced intelligence, surveillance and reconnaissance (ISR), integrated microsystems, microelectromechanical systems (MEMS) and joint unmanned combat air vehicle systems. Experiment, Modeling and Simulation of Gas-Surface Interactions for Reactive Flows in Hypersonic Flights This is a Research and Technology Organization (RTO) Educational Note RTO-EN-AVT-142, dated July 2007. The lecture series addressed the chemical non-equilibrium phenomena in the context of hypersonic re-entry flow. The objectives were to review the up-to-date experimental techniques, the theoretical models, as well as the numerical simulation strategies involved in the treatment of the chemical characters of high temperatures gases. Focusing on re-entry situation the presentations dealt with high temperature gas chemistry and also on gas-surface interaction known as catalytic effects for space vehicles. A systematic review has been presented from the detailed modeling of the microscopic level phenomena to the implementation of models for applied CDF on re-entry vehicles. As a first conclusion it appears that the bridge from the lower scale to the macroscopic surface recombination properties need further studies to be efficiently establish. A table of contents, and the full text of the document can be accessed online in HTML format. The document is contained in the RTO's Full Text Publication Library. Flight Experiments for Hypersonic Vehicle Development This is a Research and Technology Organization (RTO) Educational Note RTO-EN-AVT-130, dated June 2007. This RTO-AVT/VKI Lecture Series brought together specialists from Europe, USA, and Russia to discuss flight experiments that pertain to the development of hypersonic vehicles. The notes of this Lecturer Series provide an important resource for researchers interested in the development and interpretation of reliable flight experiments. Following a discussion of ground-test strategies that complement flight experiments and basic instrumentation issues, past and current flight experiment programs are presented with detailed discussion of the results, or expected results. Finally, advanced instrumentation concepts that are being developed to study critical aerothermodynamic phenomena on future hypersonic flight experiments are described. The lecture notes were prepared under the combined sponsorship of the RTO AVT Panel, the von Karman Institute for Fluid Dynamics, and the European Office of Air Force Research and Development. A table of contents, and the full text of the document can be accessed online in HTML format. The document is contained in the RTO's Full Text Publication Library. Future Aerospace Technology in the Service of the Alliance This is Research and Technology Organization(RTO) AGARD Conference Proceedings, AGARD-CP-600-Vol-1, dated December 1997. This proceedings was sponsored by the Advisory Group for Aerospace Research and Development. This is one of the three volumes containing the unclassified papers presented at a conference at Palaiseau, near Paris, France, 14-17 April 1997. The conference took the form of three parallel symposia and three plenary sessions. This volume contains the papers from the three plenary sessions: Future Directions in Aerospace Systems Future NATO Trends and Mission Scenarios Human Machine Interaction in the Future and the symposium on "Affordable Combat Aircraft", which had sessions on: Affordability of Procurement, Combat Effectiveness, Affordability of Ownership, The Human Element. Volume 2 contains the papers on "Mission Systems Technologies". Volume 3 contains the papers on "Sustained Hypersonic Flight". Bibliographic and abstract details are available in HTML format. A table of contents, and the full text of the document (153 Mb) can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. Future Aerospace Technology in the Service of the Alliance: Sustained Hypersonic Flight This is Research and Technology Organization(RTO) AGARD Conference Proceedings, AGARD-CP-600-Vol-3, dated December 1997. One of three volumes containing the unclassified papers presented at a conference on "Future Aerospace Technology in the Service of the Alliance" organised by AGARD (NATO's Advisory Group for Aerospace Research and Development) at Palaiseau, near Paris, France, 14-17 April 1997. The conference took the form of three parallel symposia and three plenary sessions. This volume contains the papers from the symposium on "Sustained Hypersonic Flight", which had introductory overview papers on "Mission Needs and Operational Scenarios for Hypersonic Vehicles", and on "Vehicle Configurations and Aerothermodynamic Challenges", and sessions on: •Propulsion for Hypersonic Flight •External Hypersonic Aerodynamics and Design Challenges •Military ramjet Applications •Test Facilities for Ramjets •Configurational Design and Flight Validation •Engine/Airframe Integration •System Challenges Volume 1 contains the papers from the three plenary sessions: "Future Directions in Aerospace Systems", "Future NATO Trends and Mission Scenarios", and "Human Machine Interaction in the Future"; and the papers on "Affordable Combat Aircraft". Volume 2 contains the papers on "Mission Systems Technologies". Bibliographic and abstract details are available in HTML format. A table of contents, and the full text of the document (118 Mb) can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. Hypersonic Experimental and Computational Capability, Improvement and Validation This is Research and Technology Organization (RTO) AGARD Advisory Report, AGARD-AR-319-01, dated May 1996. It was sponsored by the Advisory Group for Aerospace Research and Development. The results of the phase 1 effort conducted under AGARD Working Group 18 on Hypersonic Experimental and Computational Capability, Improvement and Validation are presented in this report. A discussion of issues and problems classified into seven topic areas precedes the individual sections on Shock/Boundary-Layer Interactions, Laminar-Turbulent Transition, Rarefield Flow, Real-Gas Effects, Facility Calibration Procedures, Extrapolation to Flight and Hypersonic Test Facilities. Recommendations for future work in these areas is included at the end of each section. Conclusions for the work conducted during the phase 2 of this Working Group will be presented in Volume 2. Bibliographic details and an abstract are available in HTML format and the full text is available in PDF format (94 Mb)from the RTO's web site. Hypersonic Experimental and Computational Capability, Improvement and Validation This Advisory Report, AGARD-AR-319-02, dated December 1998, under the NATO Research and Technology Organisation was prepared at the request of the Fluid Dynamics Panel.The results of the phase II effort conducted under AGARD Working Group 18 on Hypersonic Experimental and Computational Capability, Improvement and Validation are presented in this report. The first volume, published in May 1996, mainly focused on the design methodology, plans and some initial results of experiments that had been conducted to serve as validation benchmarks. The current volume presents the detailed experimental and computational data base developed during this effort. A table of contents, and the full text of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. Investigation of Hypervelocity Gouging This is the full text of a thesis by David J. Laird which was presented to the Air Force Institute of Technology (AFIT) in 2002. The slipper/rail interface of a hypervelocity rocket sled is subject to immense forces due to dynamic loads and impact of the slipper with the rail. In addition, tremendous heating due to aerodynamic and frictional effects is produced at the interface. Under these severe loading conditions, the material in the rail will sometimes experience large non-linear deformations known as gouging. To successfully model the gouging phenomenon, the high strain, high strain-rate, high temperature conditions and shock wave behavior present in high velocity impact dynamics must be effectively dealt with. Constitutive laws modeling inelastic material response and an appropriate equation of state also need to be considered to model these effects. [Taken from abstract]. The full text of the thesis is avialable in PDF format and is provided by the Air University ResearchWeb site. NASA : Hypersonic X-43A Takes Flight The X-43A is a hypersonic, scramjet-powered research aircraft designed to fly at speeds up to Mach 10. This is a NASA mission web site which brings together the latest news, features and supporting resources. There are a number of high resolution images, as well as video clips, including that of the historic flight of November 16 2004 during which the X-43A's scramjet air breathing engine pushed the aircraft to nearly Mach 9.8, or 7,000 mph, as it flew at about 110,000 feet. The site also provides access to a PDF format X-43A Fact Sheet. Numerical Simulation of the Transition Region in Hypersonic Flow This web site provides access to a Virginia Polytechnic Institute and State University Department of Aerospace and Ocean Engineering PhD dissertation, by Scott Andrew McKeel, dated 1 February 1996. The dissertation describes the analysis of six transition region models using GASP, a compressible Navier-Stokes code. The results from the six models are compared against experimental test data. Bibliographic and abstract details are available in HTML format. The full text of the document is accessible online in PDF format [3.30 Mb]. This title is part of Virginia Tech�s Electronic Thesis and Dissertation Collection (VT ETD). Simulation of Flow Around Hypersonic Blunt-Nosed Vehicles for the Calibration of Air Data Systems This web site provides access to a University of Queensland, Department of Mechanical Engineering PhD thesis, by Ian Alexander Johnston, submitted January 1999. The thesis describes the development of a new computational fluid dynamics code for the primary purpose of calibrating surface pressure models for use with flush air data systems. The hypersonic flight experiment (HYFLEX) vehicle is used as a case study. Bibliographic and abstract details are available in HTML format. The title page, contents and the full text of the document are accessible online in PDF format. This title is part of the Australian Digital Theses (ADT) Program Special course on Shock Wave/Boundary Layer Interactions in Supersonic and Hypersonic Flows This is Research and Technology Organization (RTO) AGARD-R-792 , dated August 1993. Notes for the AGARD Fluid Dynamics Panel (FDP) Special Course on 'Shock-Wave/Boundary-Layer Interactions in Supersonic and Hypersonic Flows' are presented. The objective was to report on results from recent research programs providing a consolidated review of these activities and a sound basis for developing more reliable methodologies for future vehicle design. The course also provided a focused review of recent progress for swept interactions in both laminar and turbulent flows, including discussions: flowfield structure; scaling and similarity laws; effect of shock strength on flow feature; effect of shock generator geometry for a given shock strength; techniques for investigating swept interactions, particularly optical techniques; and contributions of numerical simulations to the understanding of swept interactions. The effects of turbulence and turbulence modeling on the flowfields are provided. For individual titles, see N94-15197 through N94-15203. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (48.50MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. Special Course on Unstructured Grid Methods for Advection Dominated Flows This is Research and Technology Organization (RTO) AGARD-R-787 , dated May 1992. Lecture notes for the AGARD Fluid Dynamics Panel (FDP) Special Course on 'Unstructured Grid Methods for Advection Dominated Flow' have been assembled in this report. The objective of this course was to provide state of the art information, as well as recent developments in unstructured grid methods, suitable for the computation of high Reynolds number compressible and incompressible flows, and other related subjects. A wide range of applications is presented, which includes incompressible free surface problems, transonic aerodynamics, and hypersonic reentry flows. For individual titles, see N92-27672 through N92-27680. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (56.05MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. Study of Magnetogasdynamic Flow Acceleration in a Scramjet Nozzle This is the full text of a Master's thesis by Ensign Erik K. Ross, USN, AFIT/GAE/ENY/05-J11, which was presented to the Faculty of the Department of Aeronautics and Astronautics of Air University's Air Force Institute of Technology (AFIT), in June 2005. 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 and an MGD accelerator in the nozzle of the engine. Using an AFRL/VAAC CFD code that was modified for MGD computations, this project investigated the effect conductivity and load factor had on the specific thrust and efficiency of an MGD accelerator composed of segmented electrodes in the nozzle of a scramjet engine. For a load factor of 1:6, results showed a 95% increase in specific thrust. When MGD generation was employed at a load factor of 0:8, a 31% decrease in specific thrust was calculated. The solutions included high wall temperatures which need more investigation for MGD acceleration to be practical. [Taken from abstract]. The full text is available in PDF format on the Scientific and Technical Information Network (STINET) which is provided by the Defense Technical Information Center (DTIC). Technologies for Propelled Hypersonic Flight This web site provides access to a NATO Research and Technology Organization (RTO) Technical Report, RTO-TR-AVT-007-V3, prepared by the Applied Vehicle Technology Panel (AVT) Working Group 10, Subgroup 3, January 2006. Dating back to 1998 the aim of WG 10 is to: address selected critical issues related to propelled hypersonic flight, review the associated state of the art for analysis and design; and recommend activities for further developments. Three subgroups were created to structure the activities. This report presents the findings of Sub-group 3 which screened and repeated a large number of test cases for CFD validation for areas where CFD validation was deemed essential, such as transition, real gas flows, laminar and turbulent shock-boundary layer interaction, as well as base flows with and without plumes. High standards for the selection and evaluation of test cases for CFD validation were applied, resulting in an unprecedented effort to improve technologies for hypersonic flight. Citation and abstract details are in HTML format, and the full text is available online if PDF format (63.53). Individual papers are also available as separate files. Technologies for Propelled Hypersonic Flight This web site provides access to a NATO Research and Technology Organization (RTO) Technical Report, RTO-TR-AVT-007-V1, prepared by the Applied Vehicle Technology Panel (AVT) Working Group 10, Subgroup 1, January 2006. Dating back to 1998 the aim of WG 10 is to: address selected critical issues related to propelled hypersonic flight, review the associated state of the art for analysis and design; and recommend activities for further developments. Three subgroups were created to structure the activities. This report presents the findings of sub-group 1 which was responsible for reviewing fundamental aspects on plug nozzles, analysing altitude adaptation aspects and wake closure phenomena, studying influence of external flow on thrust, and addressing design methods including thrust vector control and flight extrapolation. Three test cases for CFD validation were identified: Axisymmetric full length annular plug, a truncated plug nozzle, and a 3-D linear clustered plug nozzle. Computational contributors from Europe and US participated in detailed validation activities, addressed shortcomings, and conclusions were drawn on the applicability of CFD tools for design and verification. Citation and abstract details are in HTML format, and the full text is available online if PDF format (4.48 Mbytes). Technologies for Propelled Hypersonic Flight This web site provides access to a NATO Research and Technology Organization (RTO) Technical Report, RTO-TR-AVT-007-V2, prepared by the Applied Vehicle Technology Panel (AVT) Working Group 10, Subgroup 2, January 2006. Dating back to 1998 the aim of WG 10 is to: address selected critical issues related to propelled hypersonic flight, review the associated state of the art for analysis and design, and recommend activities for further developments. Three subgroups were created to structure the activities. This report presents the findings of Sub-group 2 which addressed the physical modelling aspects associated with scram combustion. A review was carried out on fuels, turbulence mixing, ignition and flame holding prediction capabilities as well as vitiation. In particular, the Subgroup discussed the approach to be used in the design process: how to combine tests and numerical simulations to design scram engines with required margins; components modeling and testing; performance prediction; tip to tail computations etc. Citation and abstract details are in HTML format, and the full text is available online if PDF format (12.96 Mb). The individual chapters are also available as separate files. Theoretical and Experimental Methods in Hypersonic Flows This is Research and Technology Organization (RTO) AGARD-CP-514, dated April 1993. Papers prepared for the AGARD Fluid Dynamics Panel Symposium on theoretical and experimental methods in hypersonic flows held on 4-8 May 1992 are presented. The objectives of the Symposium were to (1) report and assess the advances being made by the AGARD community on the development and application of theoretical methods and experimental techniques for simulating hypersonic flows over aerospace vehicles; (2) highlight outstanding problem areas; and (3) establish pointers to aid in the planning and implementation of future research programs. Major topics covered by the Symposium were testing techniques and instrumentation, computational methods and physical modeling, and validation and accuracy assessment. For individual titles, see N94-10422 through N94-10465. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (117.34MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. Transiting from Air to Space : The North American X-15 The web site provides access to a chapter written by Robert S. Houston, Richard P. Hallion, and Ronald G. Boston. This is an excerpt from, The Hypersonic Revolution: Case Studies in the History of Hypersonic Technology, published by the Air Force History and Museums Program, 1998. The text recounts the development of the X-15 research aircraft and its flight test programme. The full text is available online in HTML format. Undergraduate Computer Programs This is the download page for a number of Java programs and applets which were designed by staff at the NASA Glenn Research Center to help undergraduate engineering students to learn about the basics of aerodynamics and propulsion. Mach and Speed of Sound Calculator allows you to specify the altitude and speed (or Mach) of an aircraft and the program uses the standard day atmosphere mathematical model to determine the speed of sound and the Mach number (speed) of your aircraft. EngineSimU is a simulator that performs a Brayton Cycle analysis of a turbine engine or ramjet. It works in design mode and test mode so that a wide range of design variables and flight conditions can be simulated. There is an even more powerful version of EngineSimU which is available for very experienced users. This program is a Java application, not an applet. It runs stand alone and you must have Java installed on your computer to run this program. FoilSim II is a simulator that performs a Kutta-Joukowski analysis to compute the lift of an airfoil. The user can control the shape, size, and inclination of the airfoil and the atmospheric conditions in which the airfoil is flying. Sound Wave Simulator allows you to explore the doppler effect and the formation of Mach waves. Interactive Nozzle Simulator solves the isentropic flow equations for the flow through a rocket nozzle, a converging- diverging turbine nozzle or a converging turbine nozzle. Shock Wave Simulator solves the flow equations for supersonic flow past a wedge. Input variables include the Mach number, and wedge angle. Multiple Shock Wave Simulator solves the flow equations for supersonic flow past multiple wedges. Input variables include the Mach number, wedge angles, and the spacing between the wedges. The icon at the top of each section will take you to a web page which contains a simulator or calculator for an aerodynamics problem. The web page assumes that you understand the problem and contains only the applet and a couple of hyperlinks to additional pages which describe the science and math behind each problem and some additional instructions on the program operation. The linked pages will take a little longer to load into your browser. If you follow the instructions provided you can download a copy of each program to your computer and you can then run the programs off-line. |
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