Supersonic retropropulsion CFD validation with Ames Unitary Plan Wind Tunnel test data

Schauerhamer, Daniel G.; Zarchi, Kerry A.; Kleb, William L.; Edquist, Karl T.

doi:10.1109/aero.2013.6496859

Cited by 3 publications

(3 citation statements)

References 33 publications

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“…This is not observed in the zero-nozzle case because the grid topology was entirely different from the nozzle cases. This is also not seen in follow-on three-nozzle configuration DPLR cases with different topologies [7,8,12,13]. The difference at the nose between FUN3D and OVERFLOW is about 30%.…”

Section: Three-nozzle Configurationmentioning

confidence: 78%

“…This is the first step in what will become a series of validation efforts. Please refer to [7][8][9] for a continuation of this work, which focuses on validation and testing efforts of these CFD codes.…”

mentioning

confidence: 99%

“…The complexities of the flow, with shocks, shear layers, and recirculation and stagnation regions, make it a challenge for flow prediction tools. The validation process chosen by the SRP team includes using multiple CFD codes to compare to historic and recent wind-tunnel tests [11][12][13]. Code-to-code and code-to-test comparisons, based on good practices in gridding, numerical method selection, and solution advancement, help reduce uncertainties in the computations, thereby allowing the focus to be on the physics of the flowfields and validity of the math models.…”

mentioning

confidence: 99%

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Analysis of Navier–Stokes Codes Applied to Supersonic Retropropulsion Wind-Tunnel Test

Zarchi

Schauerhamer

Kleb

et al. 2014

Journal of Spacecraft and Rockets

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Advancement of supersonic retropropulsion as a technology will rely heavily on the ability of computational methods to accurately predict vehicle aerodynamics during atmospheric descent, where supersonic retropropulsion will be employed. A wind-tunnel test at the NASA Langley Unitary Plan Wind Tunnel was specifically designed to aid in the support of Navier-Stokes codes for supersonic retropropulsion applications. Three computational fluid dynamics codes [data parallel line relaxation, fully unstructured Navier-Stokes three-dimensional, and overset grid flow solver] were exercised for multiple nozzle configurations for a range of freestream Mach numbers and nozzle thrust coefficients. The computational fluid dynamics pretest analysis of this wind-tunnel test aided in the test model design process by identifying the potential for tunnel blockage or unstart, of liquefaction within the plume, and of separation occurring at the internal fingers of the nozzles. This analysis led to a reduced model diameter, heating of the plenum, and reducing the nozzle area ratio, and the requirement to radius the corners at the fingers, to counter these potentials, respectively. Comparisons to test data were used to determine the existing capability of the codes to accurately model this complex flow, identify modeling shortcomings, and gain insight into the computational requirements necessary for correctly computing these flows. All three codes predict similar surface pressure coefficients and flowfield structures, such as jet termination shock, interface, bow shocks, and recirculation regions. However, the codes differ on the level of unsteadiness predicted.

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Section: Three-nozzle Configurationmentioning

confidence: 78%

mentioning

confidence: 99%

mentioning

confidence: 99%

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Analysis of Navier–Stokes Codes Applied to Supersonic Retropropulsion Wind-Tunnel Test

Zarchi

Schauerhamer

Kleb

et al. 2014

Journal of Spacecraft and Rockets

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Development and Experimental Evaluation of a Quad-Tilt-Wing Flying Robot Platform

Aihaitijiang

Önal

2019

Volume 5B: 43rd Mechanisms and Robotics Conference

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In this paper, we present the mechanical design and control system of a new indoor and outdoor Quad-Tilt-Wing flying robot. The proposed flying robot can achieve vertical takeoff, hovering, and long duration horizontal high-speed flight. All of these flight modes can be achieved by simply changing the angle of the rotors and wings by a tilt mechanism. We present the details on design and prototyping, the attitude control system, and experimental results, including wind-tunnel experiments, full flight tests, and performance tests. The experimental results show that our Quad-Tilt-Wing flying robot successfully achieves full conversion flight: vertical and rapid takeoff, high-speed cruise, and vertical landing. Performance test results show that during horizontal flight, the wings generate lift and effectively reduce energy use compared to a fixed quad rotor architecture. Consequently, the proposed platform combines unique features of multi-rotor and fixed wing systems to achieve long-duration flight with low-energy compared to a conventional multi-rotor UAV.

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Large Eddy Simulation (LES) of Aerospike Nozzle assisted Supersonic Retro-Propulsion (SRP)

Ghosh

Gunasekaran

2021

Aiaa Aviation 2021 Forum

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Supersonic retropropulsion CFD validation with Ames Unitary Plan Wind Tunnel test data

Cited by 3 publications

References 33 publications

Analysis of Navier–Stokes Codes Applied to Supersonic Retropropulsion Wind-Tunnel Test

Analysis of Navier–Stokes Codes Applied to Supersonic Retropropulsion Wind-Tunnel Test

Development and Experimental Evaluation of a Quad-Tilt-Wing Flying Robot Platform

Large Eddy Simulation (LES) of Aerospike Nozzle assisted Supersonic Retro-Propulsion (SRP)

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