Numerical Simulation of Laminar Hypersonic Flow Past Blunt Bodies Including High Temperature Effects PDF Download
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Author: S. Riedelbauch
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Category :
Languages : en
Pages :
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Author: S. Riedelbauch
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Ernst Heinrich Hirschel
Publisher: Springer Science & Business Media
ISBN: 3540265198
Category : Technology & Engineering
Languages : en
Pages : 419
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Book Description
The last two decades have brought two important developments for aeroth- modynamics. One is that airbreathing hypersonic flight became the topic of technology programmes and extended system studies. The other is the emergence and maturing of the discrete numerical methods of aerodyn- ics/aerothermodynamics complementary to the ground-simulation facilities, with the parallel enormous growth of computer power. Airbreathing hypersonic flight vehicles are, in contrast to aeroassisted re-entry vehicles, drag sensitive. They have, further, highly integrated lift and propulsion systems. This means that viscous eflFects, like boundary-layer development, laminar-turbulent transition, to a certain degree also strong interaction phenomena, are much more important for such vehicles than for re-entry vehicles. This holds also for the thermal state of the surface and thermal surface effects, concerning viscous and thermo-chemical phenomena (more important for re-entry vehicles) at and near the wall. The discrete numerical methods of aerodynamics/aerothermodynamics permit now - what was twenty years ago not imaginable - the simulation of high speed flows past real flight vehicle configurations with thermo-chemical and viscous effects, the description of the latter being still handicapped by in sufficient flow-physics models. The benefits of numerical simulation for flight vehicle design are enormous: much improved aerodynamic shape definition and optimization, provision of accurate and reliable aerodynamic data, and highly accurate determination of thermal and mechanical loads. Truly mul- disciplinary design and optimization methods regarding the layout of thermal protection systems, all kinds of aero-servoelasticity problems of the airframe, et cetera, begin now to emerge.
Author: S. Riedelbauch
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Jean-Antoine Desideri
Publisher: Springer
ISBN: 9783540544289
Category : Science
Languages : en
Pages : 268
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One of the most challenging problems of modern engineering is undoubtedly the prediction of hypersonic flows around space vehicles in reentry conditions. Indeed, the difficulties are numerous: first of all, these flows are very difficult to model, since very complex physical and chemical phenomena take place during the reentry phase; secondly, temperature, velocity and enthalpy are very high and densities are very low, making the reentry process very difficult to reproduce in ground-based experiments. The past three decades have seen important efforts in computational fluid dynam ics relying on the use of supercomputers to simulate these very complicated flows. The numerical simulation based on imperfect models and methods which were es sentially designed for transonic and supersonic flows has still a long way to go in order to be able to predict these hypersonic reentry flows very accurately. This situation has motivated very strong international cooperative efforts with, as the most visible consequences, the EuropelUnited States Short Courses on Hy personics, which were held in Paris, in 1987 [1,2], Colorado Springs in 1989 [3], and Aachen in 1990 [3]. The workshop on Hypersonics whose results are presented and analysed in these volumes is also a direct consequence of this international cooperation. This scien tific event was an initiative of P. Perrier, Head of the Theoretical Aerodynamics Department of DASSAULT AVIATION, who played a key role in the identification of the critical problems and the realisation of experiments, within the Hermes R&D program framework.
Author: J.S. Shang
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Goetz H. Klopfer
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 16
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Author: Jean-Antoine Desideri
Publisher: Springer Science & Business Media
ISBN: 3642765270
Category : Science
Languages : en
Pages : 1231
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This entry describes the experimental work conducted in the Department of Aeronautics at Imperial College in connection with Test Problems 1 and 2 of the "Workshop on Hypersonic Flows for Reentry Problems, Part I". These are defined as follows: Test Problem 1 Flow Over a Slender Cone Test Problem 2 Turbulent Base Flow The main requirement of this text is to present the experimental data for direct comparison with the predictions of CFD codes. We have therefore concentrated mainly on a factual statement of measuring techniques and results, together with an assessment of experimental accuracy. Future publications will be devoted to more extensive physical interpretations and discussions of the results. We have produced a large volume of data, some of which were categorised as "MANDATORY" and some as "OPTIONAL" for the purposes of CFD validation. However, only the "MANDATORY" data are presented here, although the other data are available and will be published separately later. 2. EXPERIMENTAL ARRANGEMENT 2. 1 The Test Facility The experiments were conducted in the Imperial College No. 2 Gun tunnel. This facility is a conventional intermittent blowdown tunnel with a contoured Mach 9 (nominal) axisymmetric nozzle fed by a free piston compression heater. The operating condition under which the data contained in this report were obtained is presented in Table 1. Test 2 T (oK) M b. Mlm Po (N/m ) Re/m T (oK) IX) IX) Case IX) w 1. 1 7 7 +0. 14 9. 16 6. 67x10 5. 5xl0 59.
Author: Michael E. Tauber
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 44
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Author: Torstein Kjell Fannelöp
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 232
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Contents: First- and second-order boundary-layer theory fundamental equations and parameters; Finite-difference methods; Solutions to the first- and second-order equations near a plane stagnation point; Some first-order finite-difference solutions; Complete first- and second-order boundary-layer solutions for simple blunt bodies in hypersonic flow.
Author: Victor Zakkay
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 66
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