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  Subjects -> AERONAUTICS AND SPACE FLIGHT (Total: 87 journals)
Acta Astronautica     Hybrid Journal   (Followers: 287)
Advances in Space Research     Full-text available via subscription   (Followers: 300)
Aeronautica     Open Access   (Followers: 5)
Aerospace     Open Access   (Followers: 3)
Aerospace and Electronic Systems, IEEE Transactions on     Hybrid Journal   (Followers: 53)
Aerospace Science and Technology     Hybrid Journal   (Followers: 310)
Affective Computing, IEEE Transactions on     Hybrid Journal   (Followers: 7)
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Air Force Magazine     Full-text available via subscription   (Followers: 3)
Air Medical Journal     Hybrid Journal   (Followers: 2)
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American Journal of Space Science     Open Access   (Followers: 35)
Artificial Satellites     Open Access   (Followers: 14)
Aviation     Hybrid Journal   (Followers: 3)
Aviation in Focus - Journal of Aeronautical Sciences     Open Access   (Followers: 1)
Aviation Psychology and Applied Human Factors     Hybrid Journal   (Followers: 5)
Aviation Week     Full-text available via subscription   (Followers: 9)
Aviation, Space, and Environmental Medicine     Full-text available via subscription   (Followers: 5)
Canadian Aeronautics and Space Journal     Full-text available via subscription   (Followers: 13)
CEAS Aeronautical Journal     Hybrid Journal   (Followers: 20)
Chinese Journal of Aeronautics     Open Access   (Followers: 11)
Control Systems     Hybrid Journal   (Followers: 18)
Cosmic Research     Hybrid Journal   (Followers: 2)
COSPAR Colloquia Series     Full-text available via subscription   (Followers: 1)
Egyptian Journal of Remote Sensing and Space Science     Open Access   (Followers: 4)
Elsevier Astrodynamics Series     Full-text available via subscription   (Followers: 1)
Fatigue of Aircraft Structures     Open Access   (Followers: 4)
Frontiers in Aerospace Engineering     Open Access   (Followers: 4)
Gyroscopy and Navigation     Hybrid Journal   (Followers: 11)
IEEE Aerospace and Electronic Systems Magazine     Full-text available via subscription   (Followers: 35)
IEEE Transactions on Circuits and Systems I: Regular Papers     Hybrid Journal   (Followers: 9)
International Journal of Aeroacoustics     Full-text available via subscription   (Followers: 6)
International Journal of Aerodynamics     Hybrid Journal   (Followers: 11)
International Journal of Aerospace Engineering     Open Access   (Followers: 40)
International Journal of Aerospace Innovations     Full-text available via subscription   (Followers: 10)
International Journal of Applied Geospatial Research     Full-text available via subscription   (Followers: 4)
International Journal of Aviation Management     Hybrid Journal  
International Journal of Aviation Psychology     Hybrid Journal   (Followers: 4)
International Journal of Aviation Technology, Engineering and Management     Full-text available via subscription  
International Journal of Crashworthiness     Hybrid Journal   (Followers: 5)
International Journal of Flow Control     Full-text available via subscription   (Followers: 2)
International Journal of Hypersonics     Full-text available via subscription   (Followers: 3)
International Journal of Micro Air Vehicles     Full-text available via subscription   (Followers: 3)
International Journal of Satellite Communications Policy and Management     Hybrid Journal  
International Journal of Space Science and Engineering     Hybrid Journal   (Followers: 2)
International Journal of Space Structures     Full-text available via subscription   (Followers: 2)
International Journal of Sustainable Aviation     Hybrid Journal  
International Journal of Turbo & Jet-Engines     Full-text available via subscription  
ISRN Astronomy and Astrophysics     Open Access   (Followers: 11)
Journal of Aerospace Computing, Information, and Communication     Full-text available via subscription   (Followers: 12)
Journal of Aerospace Engineering     Full-text available via subscription   (Followers: 125)
Journal of Aerospace Engineering & Technology     Full-text available via subscription  
Journal of Aerospace Operations     Hybrid Journal   (Followers: 3)
Journal of Aerospace Technology and Management     Open Access   (Followers: 1)
Journal of Aircraft     Full-text available via subscription   (Followers: 272)
Journal of Airline and Airport Management     Open Access   (Followers: 2)
Journal of Aviation Technology and Engineering     Open Access   (Followers: 6)
Journal of Guidance, Control, and Dynamics     Full-text available via subscription   (Followers: 50)
Journal of Konbin     Open Access  
Journal of Navigation     Hybrid Journal   (Followers: 18)
Journal of Propulsion and Power     Full-text available via subscription   (Followers: 230)
Journal of Space Weather and Space Climate     Open Access   (Followers: 3)
Journal of Spacecraft and Rockets     Full-text available via subscription   (Followers: 324)
Journal of Spatial Science     Hybrid Journal   (Followers: 1)
Journal of the American Helicopter Society     Full-text available via subscription   (Followers: 1)
Journal of the Astronautical Sciences     Hybrid Journal  
Microgravity Science and Technology     Hybrid Journal  
New Space     Hybrid Journal   (Followers: 2)
Nonlinear Dynamics     Hybrid Journal   (Followers: 5)
Population Space and Place     Hybrid Journal   (Followers: 2)
Proceedings of the Human Factors and Ergonomics Society Annual Meeting     Hybrid Journal  
Proceedings of the Institution of Mechanical Engineers Part G: Journal of Aerospace Engineering     Hybrid Journal   (Followers: 20)
Progress in Aerospace Sciences     Full-text available via subscription   (Followers: 45)
Propulsion and Power Research     Open Access   (Followers: 1)
Recent Patents on Space Technology     Full-text available via subscription  
Research & Reviews : Journal of Space Science & Technology     Full-text available via subscription  
Russian Aeronautics (Iz VUZ)     Hybrid Journal   (Followers: 12)
Space and Polity     Hybrid Journal   (Followers: 2)
Space Communications     Hybrid Journal   (Followers: 2)
Space Policy     Hybrid Journal   (Followers: 15)
Space Research Today     Full-text available via subscription   (Followers: 24)
Space Safety Magazine     Free   (Followers: 3)
Space Science Reviews     Hybrid Journal   (Followers: 10)
SpaceNews     Free   (Followers: 210)
Transportmetrica A : Transport Science     Hybrid Journal   (Followers: 1)
Вісник Національного Авіаційного Університету     Open Access   (Followers: 2)
Вестник УГАТУ     Open Access  
International Journal of Hypersonics
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     ISSN (Print) 1759-3107 - ISSN (Online) 1759-3107
     Published by Multiscience Homepage  [31 journals]
  • Performance Tests of JF-10 High-Enthalpy Shock Tunnel with a FDC Driver
    • Abstract: JF-10 detonation-driven high-enthalpy shock tunnel was re-built with a forward detonation cavity (FDC) driver and the experimental data from its performance tests are summarized and reported in this paper. Test-duration of high-enthalpy flows produced with the improved JF10 is found to be extended by two times under the condition that the FDC driver is about 40% shorter than the original one. The uniform pressure area of the thus-obtained hypersonic flows in a 500 mm diameter conical nozzle is about 700 mm in length and 400 mm in diameter. Incident shock wave decay in the driven section appears to be much less by comparing with the original JF-10 shock tunnel. The performance improvement of JF-10 high-enthalpy shock tunnel was demonstrated to be very successful and high quality hypervelocity flows can be generated for aero-thermochemistry experiments.
      Content Type Journal Article
      Category Research Article
      Pages 29-36

      DOI 10.1260/1759-3107.2.1.29

      Authors
      Z. Jiang, State Key Laboratory of High Temperature Gasdynamics Institute of Mechanics, Chinese Academy of Sciences, Beijing, 100190, China
      J. Lin, State Key Laboratory of High Temperature Gasdynamics Institute of Mechanics, Chinese Academy of Sciences, Beijing, 100190, China
      W. Zhao, State Key Laboratory of High Temperature Gasdynamics Institute of Mechanics, Chinese Academy of Sciences, Beijing, 100190, China
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 2
      Journal Issue Volume 2, Number 1 / March 2011
      PubDate: Wed, 18 Jul 2012 14:30:47 GMT
       
  • Effect of Injection Angle in Mixing and Combustion Characteristics of
           Scramjet Combustor
    • Abstract: Effect of injection angle in mixing and combustion in a scramjet combustor is numerically simulated. Three dimensional Navier Stokes equations alongwith k-ε turbulence model are solved using commercial CFD software. Both infinitely fast rate kinetics and single step finite rate kinetics are used to model chemical kinetics. Turbulence chemistry interaction is modeled by Eddy Dissipation Concept (EDC). Good agreement between the computed and experimental results for angular injection (30°) and perpendicular injection forms the basis of further analysis. More flow blockage has caused significant upstream interaction for perpendicular injection and terminal shock is seen to anchor upstream of combustor step; while for angular injection, the flow field is predominantly supersonic. Single step finite rate chemistry show comparatively low pressure and lesser upstream interaction because of the presence of backward reaction. Thermochemical variables are analysed to study the effect of angle of injection on nature of combustion (whether premixed or diffusive), heat release pattern, combustion efficiency etc.
      Content Type Journal Article
      Category Research Article
      Pages 15-28

      DOI 10.1260/1759-3107.2.1.15

      Authors
      M S R Chandra Murty, Directorate of Computational Dynamics, Defence Research and Development Laboratory Hyderabad, 500058, India
      Debasis Chakraborty, Directorate of Computational Dynamics, Defence Research and Development Laboratory Hyderabad, 500058, India
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 2
      Journal Issue Volume 2, Number 1 / March 2011
      PubDate: Wed, 18 Jul 2012 14:30:45 GMT
       
  • Numerical Study on Heat Reduction of Various Counterflowing Jets over
           Highly Blunt Cone in Hypersonic Flow
    • Abstract: In this paper, the effectiveness of counterflowing jets as heat-reduction devices for large-angle blunt cones flying at hypersonic Mach numbers is numerically simulated with various coolant jets. Different jet conditions have been chosen to investigate the effect of the counterflow jet on the surrounding flow field of nose cone. The compressible, unsteady, axisymmetric Navier-Stokes equations are solved with SST turbulence model for free stream Mach number of 5.75 at 0° angle of attack with and without gas injection. The coolant gas (air, Carbon Dioxide, and helium) is chosen to inject into the hypersonic flow at the nose of the model. The numerical results presented the surface heat reduction for different coolant jets. According to the investigation of various conditions of opposing jets, important phenomena of flow field and some effective jet conditions are found.
      Content Type Journal Article
      Category Research Article
      Pages 1-14

      DOI 10.1260/1759-3107.2.1.1

      Authors
      M. Barzegar Gerdroodbary, Department of Mechanical Engineering, Iran University of Science & Technology, Narmak, Tehran 16844, Iran
      M. A. Fayazbakhsh, School of Engineering Science, Simon Fraser University, Surrey, BC, Canada
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 2
      Journal Issue Volume 2, Number 1 / March 2011
      PubDate: Wed, 18 Jul 2012 14:30:44 GMT
       
  • Type-VI and Type-V Shock-Shock Interactions on Double-Wedge Geometries
           Using AUSM+ on Unstructured Grid
    • Abstract: The Euler equations are solved on unstructured triangular meshes for hypersonic flow over double-wedge geometries. The driving algorithm is an upwind biased cell centered finite volume method. AUSM+ method is used to split the fluxes. Edney (1968) studied the shock interactions by impinging an externally generated planar oblique shock on the bow shock generated by a cylinder. Depending upon the parametric conditions Edney classified the shock interactions in different types. Two interaction topologies, namely Type-VI and Type-V and the transition from Type-VI to Type-V are studied in details. Both six-shock and seven-shock configurations of Type-V interaction are presented.
      Content Type Journal Article
      Category Research Article
      Pages 225-244

      DOI 10.1260/1759-3107.1.4.225

      Authors
      Pabitra Halder, SM Laboratory, CSIR-CMERI, Durgapur, India
      Kalyan P. Sinhamahapatra, Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur, India
      Navtej Singh, Department of Aerospace Engineering, Indian Institute of Technology, Kharagpur, India
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 4 / December 2010
      PubDate: Fri, 03 Feb 2012 22:00:01 GMT
       
  • Investigations on Sonic Normal and Oblique Jets in Hypersonic Cross-Flow
    • Abstract: This paper presents the results of numerical and experimental investigations on sonic jet (nitrogen) injections into a hypersonic cross-flow of air. The simulations aim at finding suitable injection conditions consistent with the experimental facility at IISc from the viewpoint of combustion. Numerical results under predicted the measured jet penetration depth for normal injection. It is found from numerical simulations that the total pressure loss in case of oblique injection is less than the normal injection.
      Content Type Journal Article
      Category Research Article
      Pages 245-262

      DOI 10.1260/1759-3107.1.4.245

      Authors
      Ratan Joarder, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India
      G. Jagadeesh, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 4 / December 2010
      PubDate: Fri, 03 Feb 2012 22:00:01 GMT
       
  • Modeling of Plasma Assisted Combustion in Premixed Supersonic Gas Flow
    • Abstract: Amodel for plasma assisted combustion of ethylene-air mixtures at conditions typical for scramjet combustion chamber is developed combining classical mechanisms of thermal combustion with non-thermal plasma chemistry. Numerical simulations showed that sufficiently strong reduction of ignition induction time at a reasonable energy cost can be realized with help of filamentary discharges. Starting from the discharge region, the gas mixture is heated due to exothermic reactions involving atomic oxygen and secondary chemical radicals. Temperature increment to the end of this stage for ethylene-air mixture is relatively small. An important effect of this stage is not heating but production of transient species. Then, a period with slow growth of temperature follows, which terminates by fast combustion. Processes causing the first fast growth of gas temperature are analyzed, and intermediate species controlling acceleration of ignition are determined numerically for plasma assisted combustion of stoichiometric mixture of ethylene with air. The value of the calculated induction time defined as a moment of the fast combustion is rather sensitive to the particular combustion mechanism adopted. This manifests a necessity to refine combustion mechanisms for conditions typical for scramjet combustion chamber with plasma initiation - one atmosphere pressure, static gas temperature around 700 K and appearance of atomic oxygen&dR.
      Content Type Journal Article
      Category Research Article
      Pages 209-224

      DOI 10.1260/1759-3107.1.4.209

      Authors
      Maxim A. Deminsky, State Research Center RF "Kurchatov Institute", Moscow, Russia
      Igor V. Kochetov, State Research Center RF Troitsk Institute for Innovation and Thermonuclear Research (TRINITI), Troitsk, Moscow region, Russia
      Anatoly P. Napartovich, State Research Center RF Troitsk Institute for Innovation and Thermonuclear Research (TRINITI), Troitsk, Moscow region, Russia
      Sergey B. Leonov, Joint Institute for High Temperature RAS, Moscow, Russia
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 4 / December 2010
      PubDate: Fri, 03 Feb 2012 22:00:01 GMT
       
  • Self Ignition of Hydrogen-Air Mixtures with Inclined Porthole Injection in
           Supersonic Flows
    • Abstract: Experiments were performed in the T4 shock tunnel to investigate the self ignition of hydrogen in a supersonic air stream. Hydrogen was injected into the flow over an inclined flat plate for oncoming Mach numbers of 7.9 to 8.0. The nozzle-supply enthalpy was kept between 3.1 and 3.4 MJ/kg and two different pressure levels were used in the tests. Measurements of surface pressures were used to infer the location of ignition but only small pressure increases were obtained when combustion occurred. Therefore multiple tests at nominally the same condition were used so that statistical methods could be used to identify the ignition lengths. The ignition lengths of the hydrogen air mixture directly behind a strong leading edge shock indicate that Pergament's method is able to predict the ignition length to within 35% for the observed autoignition over the range of conditions tested.
      Content Type Journal Article
      Category Research Article
      Pages 199-208

      DOI 10.1260/1759-3107.1.4.199

      Authors
      Rainer M. Kirchhartz, Centre for Hypersonics, School of Mechanical and Mining Engineering, The University of Queensland, Brisbane, 4072, Australia
      Allan Paull, Centre for Hypersonics, School of Mechanical and Mining Engineering, The University of Queensland, Brisbane, 4072, Australia
      David J. Mee, Centre for Hypersonics, School of Mechanical and Mining Engineering, The University of Queensland, Brisbane, 4072, Australia
      Herbert Olivier, RWTH Aachen University, Aachen, 52060, Germany
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 4 / December 2010
      PubDate: Fri, 03 Feb 2012 22:00:00 GMT
       
  • Experimental and Numerical Investigation of a Non-Axisymmetric Strut Based
           Ejector
    • Abstract: Tests were performed in a non-axisymmetric, single nozzle, strut-based ejector to investigate mass flow entrainment, choking mechanisms and stream mixing as a function of primary (strut nozzle) to secondary (duct inlet) flow stagnation pressure ratio. Experimental results show a mass flow choke in the mixing duct rather than a traditional aerodynamic choke in the strut gap. The stream mixing length was constant for lower primary flow pressures, whereas mixing length varied with pressure at higher values. A companion numerical study was performed using Reynolds Averaged Navier-Stokes solutions to investigate several turbulence models. Based on both 2-D and 3-D simulation results, compressibility correction to conventional incompressible twoequation models was required for capturing the supersonic ejector mixing phenomena. The Baldwin-Lomax and the SST two-equation models were capable of capturing the essential flow features. Even with compressibility correction, the k-Σ model could not reproduce wall-dominated phenomena such as mixing duct pressure recovery.
      Content Type Journal Article
      Category Research Article
      Pages 181-198

      DOI 10.1260/1759-3107.1.3.181

      Authors
      M. S. Balasubramanyam, Propulsion Research Center, University of Alabama in Huntsville, Huntsville, AL 35899
      D. Lineberry, Propulsion Research Center, University of Alabama in Huntsville, Huntsville, AL 35899
      C. P. Chen, Department of Chemical & Materials Engineering, University of Alabama in Huntsville, Huntsville, AL 35899
      D. B. Landrum, Department of Mechanical and Aerospace Engineering, University of Alabama in Huntsville, Huntsville, AL 35899
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 3 / September 2010
      PubDate: Tue, 12 Apr 2011 21:20:50 GMT
       
  • Analysis of a Tomography Technique for a Scramjet Wind Tunnel
    • Abstract: An experimental activity is currently underway to develop a tunable diode laser absorption tomography (TDLAT) technique to measure flow properties in a supersonic combustion wind tunnel. The present study simulates the reconstruction of spectroscopic measurements to determine the effects of data collection geometry and ambient water vapor on reconstruction accuracy. The study also proposes a way to remove the effects of ambient water vapor absorption. Overall, results show that TDLAT data collection time can be significantly reduced while maintaining reconstruction accuracy by taking fewer projections with a high density of rays and by correcting for ambient water vapor absorption.
      Content Type Journal Article
      Category Research Article
      Pages 173-180

      DOI 10.1260/1759-3107.1.3.173

      Authors
      Elizabeth F. Martin, Department of Mechanical and Aerospace Engineering, University of Virginia, Charlottesville, Virginia, 22904, USA
      Christopher P. Goyne, Department of Mechanical and Aerospace Engineering, University of Virginia, Charlottesville, Virginia, 22904, USA
      Glenn S. Diskin, Chemistry and Dynamics Branch, NASA Langley Research Center
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 3 / September 2010
      PubDate: Tue, 12 Apr 2011 21:20:50 GMT
       
  • Study on the Mechanism of Quasi-Detonation
    • Abstract: In this paper, the mechanism of detonation to quasi-detonation transition was theoretically discussed, a new physical model to simulate quasi-detonation was proposed, and one-dimensional numerical simulation was conducted. This study first demonstrates that the quasi-detonation is of thermal choking. If the conditions of thermal choking are satisfied by the chemical release of energy and some disturbances, the supersonic flow is then unable to accept the additional thermal energy, and the CJ detonation becomes the unstable quasi-detonation precipitately. The kinetic energy loss consumed by this transition process is first considered in this new physical model. The numerical results are in good agreement with previous experimental observations qualitatively, which demonstrates that the quasi-detonation model is physically correct and the study is fundamentally important for detonation and supersonic combustion research.
      Content Type Journal Article
      Category Research Article
      Pages 145-156

      DOI 10.1260/1759-3107.1.3.145

      Authors
      Yunfeng Liu, Laboratory of High Temperature Gasdynamics, Chinese Academy of Sciences Institute of Mechanics, CAS, Beijing 100190, China
      Zonglin Jiang, Laboratory of High Temperature Gasdynamics, Chinese Academy of Sciences Institute of Mechanics, CAS, Beijing 100190, China
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 3 / September 2010
      PubDate: Tue, 12 Apr 2011 21:20:47 GMT
       
  • Valid Physical Processes from Numerical Discontinuities in Computational
           Fluid Dynamics
    • Abstract: Valid Physical Processes from Numerical Discontinuities in Computational Fluid Dynamics
      Content Type Journal Article
      Category Research Article
      Pages 157-172

      DOI 10.1260/1759-3107.1.3.157

      Authors
      Kun Xu, Department of Mathematics, The Hong Kong University of Science and Technology, Kowloon, Hong Kong
      Quanhua Sun, LHD, Institute of Mechanics, Chinese Academy of Sciences, Beijing, 100190, China
      Pubing Yu, Department of Mathematics, The Hong Kong University of Science and Technology, Kowloon, Hong Kong
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 3 / September 2010
      PubDate: Tue, 12 Apr 2011 21:20:47 GMT
       
  • Investigation of Heat-Flux in High Enthalpy Hypersonic Flow Over a
           Rearward-Facing Step
    • Abstract: Hypersonic laminar flow past a rearward facing step has been numerically investigated using computational fluid dynamics (CFD). The flow parameters were : total specific enthalpy ho ≈7.6 MJ/kg; unit Reynolds number Re ≈1.82 × 106 1/m ; and Mach number M∞ ≈7.6. A detailed grid independent study has been carried out to investigate the sensitivity of the surface heat flux in the regions of separation and reattachment. The nature of the flow in the close vicinity of the step is particularly emphasised. The influence of real-gas effects such as the thermal and chemical non-equilibrium are studied using Park's two-temperature model and finite-rate chemistry models respectively. The numerical results are then compared with the available experimental data of surface heat flux measurements.
      Content Type Journal Article
      Category Research Article
      Pages 115-134

      DOI 10.1260/1759-3107.1.2.115

      Authors
      Deepak N Ramanath, School of Engineering & IT, University of New South Wales, Australian Defence Force Academy, Canberra 2600, Australia
      Sudhir L Gai, School of Engineering & IT, University of New South Wales, Australian Defence Force Academy, Canberra 2600, Australia
      Andrew J Neely, School of Engineering & IT, University of New South Wales, Australian Defence Force Academy, Canberra 2600, Australia
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 2 / June 2010
      PubDate: Wed, 03 Nov 2010 15:16:24 GMT
       
  • CFD Analysis of the Aerodynamic Interaction Effects Due to Lateral Jet
           Injection in to Hypersonic Flow
    • Abstract: Reentry vehicle often uses reaction control system for providing necessary critical forces during reentry. The effect of lateral jet due to reaction control system on aerodynamic characteristics especially stability aspect of a reentry vehicle has been investigated .CFD analysis of the interaction of a lateral jet on Leeward side has been investigated on a reentry body with a circular sonic air jet injected normally in to hypersonic flow from the body surface. A systematic numerical analysis for a lateral jet interaction was performed at angles of attack 0, 2, 5, 8, and 10 degrees at free stream Mach number 8.1. The methodology has also be verified by comparing the pressure distribution at an angle of attack of 20 degrees with experimental data. The effect of lateral jet on aerodynamic characteristic has been studied by comparing the variation of aerodynamic characteristic along the length with and without lateral jet. The aerodynamic coefficients variation of aerodynamic characteristics along the axial length is studied with and without jet. Force coefficients, pitching moment coefficient and centre of pressure are studied with jet and without jet conditions by varying the angle of attack. The Mach contours, velocity vectors and path lines represent the effect of lateral jet. The computational results are validated here to compare the experimental results obtained from open literature.
      Content Type Journal Article
      Category Research Article
      Pages 135-143

      DOI 10.1260/1759-3107.1.2.135

      Authors
      Prasad.S Srinivas, Mahindra Satyam, Hyderabad
      R.K. Sharma, Dr., Scientist G, DRDL, Hyderabad
      D.K. Yadav, Scientist D, DRDL, Hyderabad
      G.V. Ramana Murty, Dr., GM, B.H.E.L (R&D), Hyderabad
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 2 / June 2010
      PubDate: Wed, 03 Nov 2010 15:16:24 GMT
       
  • Experimental Investigation of the Effects of Aerospike Geometry on
           Aerodynamic Drag and Heat Transfer Rates for a Blunt Body Configuration at
           Hypersonic Mach Numbers
    • Abstract: The effects of aerospike geometry on the drag reduction and heat transfer rates for a large-angle blunt cone flying at hypersonic Mach numbers are investigated in a hypersonic shock tunnel. Two spike geometries are considered. The first is a plain spike with a conical tip and the second is a telescopic aerospike fitted with discs of decreasing diameter in the direction opposite to the flow direction. These aerospikes are fitted to a 120° apex-angle blunt cone and results are investigated at free stream Mach numbers of 5.75 and 7.9 for different angles of attack. The aerodynamic forces are measured using an accelerometer-based force balance system and the heat transfer rates are measured using platinum thin film sensors. It is found that the telescopic aerospike has better drag reduction performance at angles of attack beyond 2° while the performance of the plain aerospike is better for angles of attack closer to zero degrees.
      Content Type Journal Article
      Category Research Article
      Pages 93-114

      DOI 10.1260/1759-3107.1.2.93

      Authors
      S Srinath, Department of Aerospace Engineering, Indian Institute of Science, Bangalore-560012, India
      K. P. J Reddy, Department of Aerospace Engineering, Indian Institute of Science, Bangalore-560012, India
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 2 / June 2010
      PubDate: Wed, 03 Nov 2010 15:16:23 GMT
       
  • Short Duration Propulsion Test and Evaluation (Hy-V) Program
    • Abstract: The Short Duration Propulsion Test and Evaluation (SDPTE) Program and the Hy-V Program have recently been combined with the aim of examining the influence of ground test facilities on scramjet performance. The combined program includes both research and educational activities that are being conducted by a consortium of university, industry and government participants. The objectives of the combined program are to; 1) Resolve ground testing issues related to the effects of test medium on dual-mode scramjet engine performance, 2) Resolve ground testing issues related to the duration of the test flow on dual-mode scramjet engine performance, and 3) Educate and motivate a new generation of aerospace engineers through student participation and research. This paper provides an overview and status of the combined program but focuses on objectives 1) and 2). The ground testing issues associated with these objectives are being examined using a range of facilities. These include a continuous-flow direct connect facility, a freejet blowdown facility and an impulse facility. By testing in a range of facilities, the effects of combustion generated test medium vitiates and test flow duration on the operation of two dual-mode scramjet flowpaths will be examined. The experiments will focus on flowpath operation at conditions equivalent to a flight Mach number of 5. However, some Mach 7 freejet testing will also take place. The program will conclude with a Mach 5 flight experiment of both scramjet flowpaths aboard a sounding rocket such that differences between ground and flight performance data can also be isolated.
      Content Type Journal Article
      Category Research Article
      Pages 77-92

      DOI 10.1260/1759-3107.1.2.77

      Authors
      Christopher P. Goyne, University of Virginia, Charlottesville, VA, 22904-4248, USA
      Daniel Cresci, Alliant Techsystems Inc. (ATK GASL), Ronkonkoma, NY, 11779, USA
      Thomas P. Fetterhoff, AEDC, Arnold AFB, TN, 37389-9011, USA
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 2 / June 2010
      PubDate: Wed, 03 Nov 2010 15:16:23 GMT
       
  • Editorial
    • Abstract: Editorial
      Content Type Journal Article
      Category Editorial
      Pages i-ii

      DOI 10.1260/1759-3107.1.1.i

      Authors
      K. P. J. Reddy, Department of Aerospace Engineering, Indian Institute of Science, Bangalore-560012, India
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 1 / March 2010
      PubDate: Wed, 21 Apr 2010 17:39:02 GMT
       
  • Counterflow Drag Reduction Studies for a Blunt Cone in High Enthalpy Flow
    • Abstract: Drag reduction by counterflow supersonic jet for a 60-degree apex angle blunt cone in high enthalpy flow is investigated in a free piston driven hypersonic shock tunnel, HST3. For flow Mach number of 8 with specific flow enthalpy of 5 MJ/kg, it has been observed that the drag force decreases with increase in the ratio of supersonic jet total pressure to the freestream pitot pressure until the critical injection pressure ratio is reached. Maximum percentage drag reduction of 44 is measured at the critical injection pressure ratio of 22.36. Further increase in injection pressure ratio has reduced the percentage drag reduction. Experimentally obtained drag signals portray the change in nature of the flowfield, around the model, across the critical injection pressure ratio.
      Content Type Journal Article
      Category Research Article
      Pages 69-76

      DOI 10.1260/1759-3107.1.1.69

      Authors
      Vinayak Kulkarni, Department of Mechanical Engineering, Indian Institute of Technology Guwahati, INDIA
      K. P. J. Reddy, Department of Aerospace Engineering, Indian Institute of Science, Bangalore, INDIA
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 1 / March 2010
      PubDate: Wed, 21 Apr 2010 17:39:01 GMT
       
  • Measurement of Drag on a Scramjet Engine in a Shock Tunnel
    • Abstract: The net drag on a non-fuelled, internal compression, constant-area combustor scramjet engine was measured using a single-component accelerometer balance in a shock tunnel at a freestream Mach number of 8 and a flow total enthalpy of 1.35 MJ/kg. The flow fields of the model were simulated using a commercial CFD code in order to understand the aerodynamics of the engine and compare with the measured net drag co-efficient. Measured and computed values of the net drag co-efficient were found to be in a good agreement.
      Content Type Journal Article
      Category Research Article
      Pages 59-68

      DOI 10.1260/1759-3107.1.1.59

      Authors
      K. K. N. Anbuselvan, Department of Aerospace Engineering, Indian Institute of Technology Bombay, Powai, Mumbai 400076, INDIA
      V. Menezes, Department of Aerospace Engineering, Indian Institute of Technology Bombay, Powai, Mumbai 400076, INDIA
      K. S. N. Abhinav Kumar, Department of Aerospace Engineering, Indian Institute of Technology Bombay, Powai, Mumbai 400076, INDIA
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 1 / March 2010
      PubDate: Wed, 21 Apr 2010 17:39:01 GMT
       
  • Force Measurement Techniques for Hypersonic Flows in Shock Tunnels
    • Abstract: Recent advances in hypersonic research activities have led to the development in ground based test facilities for simulating near-realistic flight conditions in the laboratory. Basic performance data such as drag, lift, thrust etc., are usually obtained from ground-based experimentation for physical understanding of the flow fields and subsequent prototype developments. Hypersonic flows are produced for a very short time in impulse facilities such as shock tunnels, free-piston shock tunnels and expansion tubes. The test times are in the order of few milliseconds in the shock tunnel and for the expansion tubes, it is still less (~50 μs). The force measurements in these facilities are very challenging due the need of fast response sensors and instrumentations. In this review paper, two force measurement techniques are discussed that are best suited for short duration facilities namely; accelerometer balance and stress-wave force balance system.
      Content Type Journal Article
      Category Research Article
      Pages 31-58

      DOI 10.1260/1759-3107.1.1.31

      Authors
      Niranjan Sahoo, Department of Mechanical Engineering, Indian Institute of Technology Guwahati, Guwahati - 781 039, INDIA
      K. P. J. Reddy, Department of Aerospace Engineering, Indian Institute of Science, Bangalore - 560 012, INDIA
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 1 / March 2010
      PubDate: Wed, 21 Apr 2010 17:39:00 GMT
       
  • Numerical Simulation of Liquid Fueled SCRAMJET Combustor Flow Fields
    • Abstract: Numerical simulations were carried out for various reacting flow fields related to scramjet propulsion system using commercial CFD Software. Three-dimensional Navier stokes equations were solved along with the K-ε turbulence model. Modeling of the turbulence chemistry interaction is done through infinitely fast rate chemical kinetics. The software was validated extensively by comparing different experimental conditions for scramjet combustor to find its error band and range of application. Good agreement between the experimental and computational values were obtained for the scramjet combustor flow field with strut, pylon and cavity injection system with both hydrogen and hydrocarbon fuel. The validated CFD tool was applied in the design exercise of flight-sized kerosene fuel scramjet combustor of a hypersonic airbreathing mission. Significant improvement of combustion efficiency and thrust could be achieved by relocating the fuel injection system through the analysis of various thermochemical variables in the scramjet combustor.
      Content Type Journal Article
      Category Research Article
      Pages 13-30

      DOI 10.1260/1759-3107.1.1.13

      Authors
      Debasis Chakraborty, Directorate of Computational Dynamics, Defence Research and Development Laboratory, Hyderabad - 500058, INDIA
      Journal International Journal of Hypersonics

      Print
      ISSN 1759-3107
      Journal Volume Volume 1
      Journal Issue Volume 1, Number 1 / March 2010
      PubDate: Wed, 21 Apr 2010 17:38:59 GMT
       
 
 
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