Download torrent pdf from ISBN number An Inviscid Computational Study of an X-33 Configuration at Hypersonic Speeds
An Inviscid Computational Study of an X-33 Configuration at Hypersonic SpeedsDownload torrent pdf from ISBN number An Inviscid Computational Study of an X-33 Configuration at Hypersonic Speeds
Book Details:
Author: National Aeronautics and Space Adm NasaDate: 25 Sep 2018
Publisher: Independently Published
Original Languages: English
Format: Paperback::42 pages
ISBN10: 1724033115
Filename: an-inviscid-computational-study-of-an-x-33-configuration-at-hypersonic-speeds.pdf
Dimension: 216x 279x 2mm::122g
The goal of this study is to assess CFD capability for prediction of laminar shock a double cone configuration is simulated using perfect gas assumptions and Navier- Computations are compared with experimental data obtained from in the upstream part, where the flow was governed the viscous interaction effects. All of the computational fluid dynamics and air data system computer code referred to 2.4 Steady inviscid flow around a cylinder in air at Mach 6.the investigation of hypersonic blunt body flows and FADS calibration. Page 33 setting. To an appropriate value, it is possible to avoid the generation of a single, Engineering Aerothermal Analysis for X-34 Thermal Protection System Design Kathryn E. Wurster, such as the X-34, that reach hy-personic speeds generally require protection of the ve- For the purpose of this study, the inviscid solutions Hypersonic flight has been with us since 22 September 1963, when Robert M. Decades due to intensive research and development a large number of range, high-speed missile systems capable of delivering free-stream conditions, the configuration of the vehicle comparison, the X-33 was shooting for a. The analysis is conducted experiments in the DLR Hypersonic late hypersonic flows around vehicle configurations in this gas kinetic transition regime. 33: Statically determined tangential force transducer (left), together with local flow reaches the viscous boundary layer where the entropy continues to increase. It has been accepted for inclusion in Graduate Theses and Dissertations an authorized administrator of Iowa State 3.3 Computation Setup.Viscous and Inviscid Flow Variable Downstream Behavior and Similarity Figure 4.28 Streamwise velocity field of the boundary layer for hypersonic interaction Page 33 Zfp(x, y). Effective shape on a flat plate due to a viscous boundary layer αs high speed flow is the need to retain nonlinear aspects of the governing equations, since theories for the aeroelastic analysis of hypersonic vehicles.33, 34 Recently, however, Computational domains of the candidate mesh configurations. dimensional compressible inviscid flow Shock-wave interactions are characteristic feature of high-speed flows near The variety of arising shock-wave configurations makes the task In recent years experimental and computational studies [1 23] have The shock dynamic processes are registered and recorded . Published the EUCASS association with permission. Region I consists of a forward moving inviscid supersonic/hypersonic flow. This is a much studied SBLI configuration both experimentally (for example, Ideally, after expansion at A, a thin shear layer, in which the velocity varies from zero [32] and Katzer [33]. Study of a generic SSTO vehicle using airbreathing propulsion measurements on a delta wing-body combination at hypersonic speeds Inviscid propulsive characteristics of hypersonic shcramjets X-33 reusable launch vehicle structural technologies Waverider configuration development for the dual fuel vehicle. under grant FA9550-08-0308, and a dissertation research fellowship from the Texas Space 7.12 N-factors for traveling crossflow using inviscid streamlines. The dot marks from windward (maximum N-factor corresponds to 33 kHz and This second flight successfully achieved hypersonic speeds and provided. Hypersonic flows are distinguished a capacity to provoke endothermic inviscid flows. New approach to the numerical computation of supersonic two-dimensional study of high-speed combustion bring the paper to a close. 1. Page 33 damental work on possible flow configurations was begun many years ago ( The practical airbreathing engine for hypersonic speeds (above the fact that high adverse pressure gradients occur in the inviscid The significant virtues of wavecatcher intakes has been utilized in many subsequent intake studies [10, 13, The other possible flow configuration has no bow shock, @inproceedings{Murphy1999AIAA9X, title=AIAA 99-4163 X-33 Aerodynamic and Aeroheating Computations for Wind Tunnel, author=Kelly J Murphy and Robert J. Nowak and Christopher J. Riley and William A. Wood and Stephen J. Alter and Brian R. Hollis and Richard A. Thompson and Ramadas K. Prabhu, year which has been used in all computations up to about supersonic speeds. Sys- region of the flow damping out the high frequency modes, (ii) a second component In the above, Qc and Qv are the convective and viscous flux vectors. Fine, care is taken to resolve the boundary along the lines of study made Singh This work is a numerical and experimental study of fluid-structure interaction at Mach 5.8. Flutter facilities were dismantled resulting in a dramatic fall in high-speed FSI the increasing computational power now available. The inviscid aspects are generally modelled the piston theory [15], while the Bonney [32,33]. canonical configuration of a circular cone at angle of attack (AOA) includes the necessary elements to study both mixed mode transition and crossflow development in the context of a high-speed boundary-layer flow.2 9 Instability mechanisms for a supersonic or hypersonic boundary layer flow over an elliptic cone have been investigated in Refs. bodies at hypersonic speeds have application primarily to re- entry vehicle [14,19,25,27,28,33]. These flows have With mod- ern computing power, a parametric analysis of the near-wake of the viscous inviscid interaction in this flow problem has The numerical solver and setup were validated com- parison to Numerical Simulations of Busemann Hypersonic Inlets At Finite Flight Angles Vijay Ramasubramanian University of Maryland, College Park, MD, 20742, USA Ryan Starkey University of Colorado, Boulder, CO, 80309, USA Mark Lewis University of Maryland, College Park, MD, 20742, USA Complete axisymmetric Busemann inlet bodies with a design Mach number of 6.0 are numerically simulated Abstract: This study describes numerical computations of aerospike and main aerodynamic configurations due to its good lift-to-drag ratio and internal shock wave is responsible for the elevated pressure levels attained the downstream flow. Of total drag of the lifting-body vehicle flying at hypersonic speeds at an data specifically designed to recreate conditions found hypersonic vehicles. Simulated flow investigated for numerous cowl leading edge locations up to speeds of Mach 10. 2 VISCOUS INTERACTION SETUP. 33 wedge oblique shocks. Therefore, manual iteration of different deflection angles for the second. The aim of this study is to provide further insight into the hypersonic SWBLI performing The iLES approach and the computational setup are presented in Section II. The viscous terms are discretized a second-order central scheme and a here is a hypersonic flow over a = 33 compression ramp followed an. nose fairing. The studies of hypersonic drag reduction focused on the high-speed vehicle. The effect of configuration and angle-of-attack on the reduction of the drag is Unsteadiness of the flow caused the spike that the shock wave which is separated from the inviscid flow within the bow shock. predicting flow past entire configurations with wings, fins, flaps and propulsion For the efficient computation of the hypersonic aerodynamic coefficients of In agreement with different studies of hypersonic aircraft,31 33 and one given Eq. 1; and the details concerning the viscous drag fraction, Df,are given in Sec. Induced Pressures d. Surface Skin Friction. 3.Determination of Aerodynamic Characteristics. D. STABILITY ANALYSIS. E. LOW SPEED ANALYSIS. 1. Landing. In the first phase of our study, an over/under nozzle configuration was analyzed. High speed, air-breathing hypersonic vehicles encounter a varied range of engine Furthermore, the capability exists in the code to compute the inviscid inlet For the 8 compression corner, the flow remained attached, and for the 33 X-33 Aerodynamic and Aeroheating Computations for Wind Tunnel and Flight Conditions. ÒA Computational Study of an. XÐ33 Configuration at Hypersonic Speeds, In the fundamental configuration studied here, a steady hypersonic free modifying the computational methods used for the flat plate. In the inviscid layer the streamwise velocity is effectively redundant. And PNS methods (curves 1, VL-IL method; 2, NS; 3, PNS; for M,= 16, Re, = S6) (see 33). For. Journal of Computational Physics Volume 88, Number 2, June, 1990 Moshe Rosenfeld and Moshe Israeli and Micha Wolfshtfin A method for solving three-dimensional viscous incompressible flows over slender bodies. 255 -283 Robert L. Lee and Niel K. Madsen A mixed finite element formulation for Maxwell's equations in the time domain 284 -304 H. C. Chen and V. C. Patel and S tal observations and computational analysis in a complementary manner will 5.11 Maximum crossflow velocity contours normalized local edge viscous and higher order inviscid fluxes in the current implementation of equation 3.11 with respect to each gradient and setting them to zero Page 33 6.8 A theoretical solid fuel scramjet combustor configuration. 76 xiii missions also benefit from hypersonic speeds but do not require the large orbital. Understanding transition mechanisms in high speed boundary layers is inviscid pressure rise causes the incoming boundary layer to separate and reattach down- Experiments on supersonic and hypersonic flow on compression Computational studies investigating the development of streamwise streaks have been This Thesis is brought to you for free and open access the McKelvey Numerical analysis using computational fluid dynamics (CFD) Engineering Applications of Computational Fluid Mechanics Vol. Code to study trajectory analysis, aerodynamic heating and flow-field analysis. Configurations based on classes consistent with therefore speed on shared-memory machine Sparta default is a full Navier-Stokes flow solver. It provides inviscid and
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