Analysis of Dynamic Data from Supersonic Retropropulsion Experiments in NASA Langley's Unitary Plan Wind Tunnel

Codoni, Joshua R.; Berry, Scott A.

doi:10.2514/6.2012-2706

Cited by 8 publications

(7 citation statements)

References 11 publications

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“…The unceriainty analysis results for the UPWT data that allows quantitative comparisons with CFD predictions have been completed and published [12]. A detailed analysis of the high-frequency data has also been published [13]. A second wind-tunnel test in the Ames 9x7 Supersonic Wind Tunnel was also completed, which provides overlap conditions from two facilities to further assess experimental uncertainties.…”

Section: Additional Discussionmentioning

confidence: 98%

“…Codoni and Berry [13] provide a separate, deeper review of the high-frequency data. For the a = 0 deg case discussed earlier, predominant frequencies from the forebody Kulite measurements range from 1.7 to 2.3 kHz depending on forebody location.…”

Section: Center Nozzle Configurationmentioning

confidence: 99%

“…During the last decade, general guidelines for the design and execution of validation experiments have been put forth in [9][10][11][12][13][14][15][16][17]. The following six validation experiment guidelines were taken from [17].…”

Section: Cfd Validation Experimentsmentioning

confidence: 99%

“…These model design aspects will be discussed in further detail in subsequent sections, along with UPWT experimental results and observations relevant to the overall theme of validation results. Initial attempts at CED validation comparisons [10,11] and additional experimental results from this first test entry [12,13] have been published separately. Furthermore, a follow-up study in the Ames 9x7 supersonic wind tunnel has been completed [14], along with comparisons to CED results [15].…”

mentioning

confidence: 99%

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Supersonic Retropropulsion Validation Experiment in the NASA Langley Unitary Plan Wind Tunnel

Berry

Rhode

Edquist

2014

Journal of Spacecraft and Rockets

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The development of snpersonic retropropulsión, an enabling technology for heavy payload exploration missions to Mars, is the focus of the present paper. A new experimental model, intended to provide computational fluid dynamics model validation data, was recently designed for the Langley Research Center Unitary Plan Wind Tunnel test section 2. Pretest analyses using modern computational fluid and thermal analysis tools were instrumental for sizing and refining the model, over the Mach number range of 2.4-4.6, such that tunnel blockage and internal flow separation issues would be minimized. A 5-in.-diam 70 deg sphere-cone forebody, which accommodates up to four 4:1 area ratio nozzles, followed by a 9.55-in.-long cylindrical aftbody, was developed for this study based on the computational results. The model was designed to allow for a large number of surface pressure measurements on the forebody and afthody. Supplemental data included high-speed schlieren video and internal pressures and temperatures. The run matrix was developed to allow for the quantification of various sources of experimental uncertainty, such as random errors due to run-to-run variations and bias errors due to flowfield or model misalignments. Observations and trends from this initial test in the Unitary Plan Wind Tunnel are presented. c,, CT M P q Re r,9

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Section: Additional Discussionmentioning

confidence: 98%

Section: Center Nozzle Configurationmentioning

confidence: 99%

Section: Cfd Validation Experimentsmentioning

confidence: 99%

mentioning

confidence: 99%

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Supersonic Retropropulsion Validation Experiment in the NASA Langley Unitary Plan Wind Tunnel

Berry

Rhode

Edquist

2014

Journal of Spacecraft and Rockets

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“…High frequency pressure transducer data are also available, and have been studied more thoroughly for the LRC UPWT test [37] than for the ARC UPWT test. Comparisons of dominant frequencies of certain runs were discussed in references [15] and [17].…”

Section: Introductionmentioning

confidence: 99%

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

Schauerhamer

Zarchi

Kleb

et al. 2013

2013 IEEE Aerospace Conference

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Abstract-A validation study of Computational Fluid Dynamics (CFD) for Supersonic Retropropulsion (SRP) was conducted using three Navier-Stokes flow solvers (DPLR, FUN3D, and OVERFLOW). The study compared results from the CFD codes to each other and also to wind tunnel test data obtained in the NASA Ames Research Center 9 ×7 Unitary Plan Wind Tunnel. Comparisons include surface pressure coefficient as well as unsteady plume effects, and cover a range of Mach numbers, levels of thrust, and angles of orientation. The comparisons show promising capability of CFD to simulate SRP, and best agreement with the tunnel data exists for the steadier cases of the 1-nozzle and high thrust 3-nozzle configurations.

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Investigation of Hypersonic Retropropulsion Using Planar Laser-Induced Iodine Fluorescence

Codoni¹

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Analysis of Dynamic Data from Supersonic Retropropulsion Experiments in NASA Langley's Unitary Plan Wind Tunnel

Cited by 8 publications

References 11 publications

Supersonic Retropropulsion Validation Experiment in the NASA Langley Unitary Plan Wind Tunnel

Supersonic Retropropulsion Validation Experiment in the NASA Langley Unitary Plan Wind Tunnel

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

Investigation of Hypersonic Retropropulsion Using Planar Laser-Induced Iodine Fluorescence

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