X-43C Plans and Status

Moses, Paul L.

doi:10.2514/6.2003-7084

Cited by 8 publications

(4 citation statements)

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“…The hypersonic inlet/isolator, an essential component of the scramjet engine, plays a significant role in the stable and safe operation of aircraft [1][2][3][4][5][6][7]. During flights, because of the complex wind field environment [8][9][10][11], aircraft frequently encounter atmospheric disturbances, such as gusts, wind shear, three-dimensional wind, vortices, and continuous turbulence.…”

Section: Introductionmentioning

confidence: 99%

Transient Flow Evolution of a Hypersonic Inlet/Isolator with Incoming Windshear

Gao,

Huang,

Meng

et al. 2023

Aerospace

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In this paper, a novel flow perturbation model meant to investigate the effects of incoming wind shear on a hypersonic inlet/isolator is presented. This research focuses on the transient shock/boundary layer interaction and shock train flow evolution in a hypersonic inlet/isolator with an on-design Mach number of 6.0 under incoming wind shear at high altitudes, precisely at an altitude of 30 km with a magnitude speed of 80 m/s. Despite the low intensity of wind shear at high altitudes, the results reveal that wind shear significantly disrupts the inlet/isolator flowfield, affecting the shock wave/boundary layer interaction in the unthrottled state, which drives the separation bubble at the throat to move downstream and then upstream. Moreover, the flowfield behaves as a hysteresis phenomenon under the effect of wind shear, and the total pressure recovery coefficients at the throat and exit of the inlet/isolator increase by approximately 10% to 12%. Furthermore, this research focuses on investigating the impact of wind shear on the behavior of the shock train. Once the inlet/isolator is in a throttled state, wind shear severely impacts the motion of the shock train. When the downstream backpressure is 135 times the incoming pressure (p0), the shock train first moves upstream and gradually couples with a cowl shock wave/boundary layer interaction, resulting in a more significant separation at the throat, and then moves downstream and decouples from the separation bubble at the throat. However, if the downstream backpressure increases to 140 p0, the shock train enlarges the separation bubble, forcing the inlet/isolator to fall into the unstart state, and it cannot be restarted. These findings emphasize the need to consider wind shear effects in the design and operation of hypersonic inlet/isolator.

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Section: Introductionmentioning

confidence: 99%

Transient Flow Evolution of a Hypersonic Inlet/Isolator with Incoming Windshear

Gao,

Huang,

Meng

et al. 2023

Aerospace

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“…Hypersonic flight vehicles on which variable-geometry inlets were proposed include the National Aero-Space Plane (NASP) and the X-43C [5,6]. The Ground Demonstrator Engine-Build 2 (GDE-2) included a rotating cowl flap that performed well in the Mach 4.5 to 6.5 range using realistic flight hardware including high-temperature seals [6]. A configurable inlet/isolator experiment was tested by Emami et al [7] in which the cowl length and angle could be changed between test runs.…”

Section: Introductionmentioning

confidence: 99%

Performance Analysis of Variable-Geometry Scramjet Inlets Using a Low-Order Model

Dalle¹,

Torrez²,

Driscoll³

2011

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…1,2 A secondary goal is to evaluate the experimental [3][4][5][6] and computational [7][8][9][10] techniques used in the design and analysis of the Hyper-X vehicle in order to facilitate future hypersonic and launch vehicle programs. 1,11,12 The flight experiment mission profile is shown in Fig. 1, and takes place in the Western Test Range over the Pacific Ocean.…”

Section: Introductionmentioning

confidence: 99%

Hyper-X Post-Flight Trajectory Reconstruction

Karlgaard

Tartabini

Blanchard

et al. 2004

AIAA Atmospheric Flight Mechanics Conference and Exhibit

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This paper discusses the formulation and development of a trajectory reconstruction tool for the NASA X-43A/Hyper-X high speed research vehicle, and its implementation for the reconstruction and analysis of flight test data. Extended Kalman filtering techniques are employed to reconstruct the trajectory of the vehicle, based upon numerical integration of inertial measurement data along with redundant measurements of the vehicle state. The equations of motion are formulated in order to include the effects of several systematic error sources, whose values may also be estimated by the filtering routines. Additionally, smoothing algorithms have been implemented in which the final value of the state (or an augmented state that includes other systematic error parameters to be estimated) and covariance are propagated back to the initial time to generate the best-estimated trajectory, based upon all available data. The methods are applied to the problem of reconstructing the trajectory of the Hyper-X vehicle from flight data.

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X-43C Plans and Status

Cited by 8 publications

References 0 publications

Transient Flow Evolution of a Hypersonic Inlet/Isolator with Incoming Windshear

Transient Flow Evolution of a Hypersonic Inlet/Isolator with Incoming Windshear

Performance Analysis of Variable-Geometry Scramjet Inlets Using a Low-Order Model

Hyper-X Post-Flight Trajectory Reconstruction

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