Generation of the Ares I-X Flight Test Vehicle Aerodynamic Data Book and Comparison To Flight

Bauer, Steven X. S.; Krist, Steven E.; Compton, W. B.

doi:10.2514/6.2011-11

Cited by 20 publications

(9 citation statements)

References 2 publications

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“…Although limited to a small region, such comparisons provide some degree of confidence in the numerical predictions of the surface flow characteristics. Prior to the recent Ares-IX flight test [26], there was no experimental data available for this class of vehicles at flight Re that could be used to validate the computational results. As a result, an effort was initiated to measure a limited set of high Re surface Cp, that reached to approximately one tenth of the appropriate flight level, from the Langley's National Transonic Facility (NTF) at subsonic and transonic speeds (i.e., 0.5 < M < 1.1) to aid anchoring the slope of the extrapolation curve at the lower end.…”

Section: Adac-2b (A103)mentioning

confidence: 99%

Overview of Ares-I CFD Ascent Aerodynamic Data Development And Analysis Based on USM3D

Abdol-Hamid

Ghaffari

Parlette³

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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An overview of the computational results obtained from the NASA Langley developed unstructured grid, Reynolds-averaged Navier-Stokes flow solver USM3D, in support of the Ares-I project within the NASA's Constellation program, are presented. The numerical data are obtained for representative flow conditions pertinent to the ascent phase of the trajectory at both wind tunnel and flight Reynolds number without including any propulsion effects. The USM3D flow solver has been designated to have the primary role within the Ares-I project in developing the computational aerodynamic data for the vehicle while other flow solvers, namely OVERFLOW and FUN3D, have supporting roles to provide complementary results for fewer cases as part of the verification process to ensure code-to-code solution consistency. Similarly, as part of the solution validation efforts, the predicted numerical results are correlated with the aerodynamic wind tunnel data that have been generated within the project in the past few years. Sample aerodynamic results and the processes established for the computational solution/data development for the evolving Ares-I design cycles are presented.

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Section: Adac-2b (A103)mentioning

confidence: 99%

Overview of Ares-I CFD Ascent Aerodynamic Data Development And Analysis Based on USM3D

Abdol-Hamid

Ghaffari

Parlette³

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…The generation of the Ares I-X FTV aerodynamic database and the compadson of preflight and postflight computations with flight data are detailed in [32]. Over the entire Ares I-X project, more than 5000 USM3D solutions have been generated based on gdds that consisted of 70 X 10* to 140 X 10* tetrahedral cells.…”

Section: Ares I-x Flight-test Vehicle Configurationmentioning

confidence: 99%

“…Orion project LAS 60-AA wind-tunnel model mounted in the NASA Ames Research Center 11 ft tunnel.Ares IX FTV Pressure CoefficientRoCS: cw FS Motor: of USM3D surface pressures with the flight-test data for the Ares I-X FTV using two turbulence models (RoCS firing in clockwise direction, from[32]). Fig.…”

mentioning

confidence: 99%

Enhancements to TetrUSS for NASA Constellation Program

Pandya

Frink

Abdol-Hamid

et al. 2012

Journal of Spacecraft and Rockets

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The NASA Constellation program is utilizing Computational Fluid Dynamics (CFD) predictions for generating aerodynamic databases and design loads for the Ares I, Ares I-X, and Ares V launch vehicles and for aerodynamic databases for the Orion crew exploration vehicle and its launch abort system configuration. This effort presents several challenges to applied aerodynamicists due to complex geometries and flow physics, as well as from the juxtaposition of short schedule program requirements with high fidelity CFD simulations. NASA TetrUSS codes (GridTool/VGRID/USM3D) have been making extensive contributions in this effort. This paper will provide an overview of several enhancements made to the various elements of TetrUSS suite of codes. Representative TetrUSS solutions for selected Constellation program elements will be shown. Best practices guidelines and scripting developed for generating TetrUSS solutions in a production environment will also be described.

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“…The Ares I-X Flight-Test Vehicle (FTV) was developed as a first flight demonstration of the Ares I concept and therefore presents a very similar configuration. Details about the Ares I project and the Ares I-X flight test are reported by Hall et al [1] and Bauer et al [2], respectively. The first and USs are connected by the interstage, characterized by a diameter change from the large US to the smaller FS SRB diameter.…”

mentioning

confidence: 99%

Ares I and Ares I-X Stage Separation Aerodynamic Testing

Pinier¹

2012

Journal of Spacecraft and Rockets

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The aerodynamics of the Ares I crew launch vehicle (CLV) and Ares I-X flight test vehicle (FTV) during stage separation was characterized by testing 1%-scale models at the Arnold Engineering Development Center's (AEDC) von Karman Gas Dynamics Facility (VKF) Tunnel A at Mach numbers of 4.5 and 5.5. To fill a large matrix of data points in an efficient manner, an injection system supported the upper stage and a captive trajectory system (CTS) was utilized as a support system for the first stage located downstream of the upper stage. In an overall extremely successful test, this complex experimental setup associated with advanced postprocessing of the wind tunnel data has enabled the construction of a multi-dimensional aerodynamic database for the analysis and simulation of the critical phase of stage separation at high supersonic Mach numbers. Additionally, an extensive set of data from repeated wind tunnel runs was gathered purposefully to ensure that the experimental uncertainty would be accurately quantified in this type of flow where few historical data is available for comparison on this type of vehicle and where Reynolds-averaged Navier-Stokes (RANS) computational simulations remain far from being a reliable source of static aerodynamic data. Nomenclature

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Generation of the Ares I-X Flight Test Vehicle Aerodynamic Data Book and Comparison To Flight

Cited by 20 publications

References 2 publications

Overview of Ares-I CFD Ascent Aerodynamic Data Development And Analysis Based on USM3D

Overview of Ares-I CFD Ascent Aerodynamic Data Development And Analysis Based on USM3D

Enhancements to TetrUSS for NASA Constellation Program

Ares I and Ares I-X Stage Separation Aerodynamic Testing

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