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  • 1
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    Turbulent Aeroheating Measurements on a 7-deg Half-Angle Sphere-Cone in a High-Enthalpy CO2 Expansion Tunnel (2018)
    In:  CASI
    Details
    Publication Date: 2019-08-01
    Description: A database of heating and pressure measurements on a 7-deg half-angle cone in a highenthalpy expansion tunnel in CO2 has been generated to support development and validation of computational models to be employed in the design of future Mars missions. Laminar, transitional, and turbulent simulations were performed at the test conditions for comparisons with the data. Close agreement was obtained for both fully-laminar and fully turbulent conditions. For the remaining transitional/turbulent conditions, agreement to within, or slightly more than, the estimated experimental uncertainty was demonstrated. The influence of transition intermittency and transition length models on predicted heating levels was demonstrated, as were differences in turbulent heating predictions generated using various algebraic, one-equation, and two-equation turbulence models. These comparisons provide some measure of confidence in turbulent simulation capabilities; however, because the data were not obtained on a relevant entry vehicle geometry, it is not possible to fully quantify computational uncertainties for the definition of Mars mission aerothermodynamic environments at this time
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NF1676L-29376 , AIAA SciTech Forum: 2018 AIAA Aerospace Sciences Meeting
    Format: application/pdf
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  • 2
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    Space Launch System Base Heating Test: Environments and Base Flow Physics (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-19
    Description: The NASA Space Launch System (SLS) vehicle is composed of four RS-25 liquid oxygen- hydrogen rocket engines in the core-stage and two 5-segment solid rocket boosters and as a result six hot supersonic plumes interact within the aft section of the vehicle during ight. Due to the complex nature of rocket plume-induced ows within the launch vehicle base during ascent and a new vehicle con guration, sub-scale wind tunnel testing is required to reduce SLS base convective environment uncertainty and design risk levels. This hot- re test program was conducted at the CUBRC Large Energy National Shock (LENS) II short-duration test facility to simulate ight from altitudes of 50 kft to 210 kft. The test program is a challenging and innovative e ort that has not been attempted in 40+ years for a NASA vehicle. This presentation discusses the various trends of base convective heat ux and pressure as a function of altitude at various locations within the core-stage and booster base regions of the two-percent SLS wind tunnel model. In-depth understanding of the base ow physics is presented using the test data, infrared high-speed imaging and theory. The normalized test design environments are compared to various NASA semi- empirical numerical models to determine exceedance and conservatism of the ight scaled test-derived base design environments. Brief discussion of thermal impact to the launch vehicle base components is also presented.
    Keywords: Spacecraft Design, Testing and Performance
    Type: M16-5594 , AIAA Young Professionals Symposium; Oct 20, 2016 - Oct 21, 2016; Huntsville, AL; United States
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  • 3
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    Scaled Rocket Testing in Hypersonic Flow (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA's Space Launch System (SLS) uses four clustered liquid rocket engines along with two solid rocket boosters. The interaction between all six rocket exhaust plumes will produce a complex and severe thermal environment in the base of the vehicle. This work focuses on a recent 2% scale, hot-fire SLS base heating test. These base heating tests are short-duration tests executed with chamber pressures near the full-scale values with gaseous hydrogen/oxygen engines and RSRMV analogous solid propellant motors. The LENS II shock tunnel/Ludwieg tube tunnel was used at or near flight duplicated conditions up to Mach 5. Model development was strongly based on the Space Shuttle base heating tests with several improvements including doubling of the maximum chamber pressures and duplication of freestream conditions. Detailed base heating results are outside of the scope of the current work, rather test methodology and techniques are presented along with broader applicability toward scaled rocket testing in supersonic and hypersonic flow.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: M15-4744 , AIAA International Space Planes and Hypersonic Systems and Technologies Conference (Hypersonics 2015); Jul 06, 2015 - Jul 09, 2015; Glasgow, Scotland; United Kingdom
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  • 4
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    Optical Diagnostic Imaging of Multi-Rocket Plume-Induced Base Flow Environments (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Non-intrusive optical diagnostic imaging was used for the first time to visualize multi-rocket plume-induced reacting base flows to simulate launch vehicle ascent from sea-level to 250,000 ft. In particular, planar laser induced florescence (PLIF) and infrared (IR) imaging were implemented for the first time to visualize and quantify base flow and rocket plume environments from sub-scale, short-duration propulsion models within a shock tunnel facility. This report discusses the successful imaging diagnostic methods for capturing base flow features and dynamics as a function of altitude. Important base flow and plume features were captured with PLIF and IR diagnostics to develop a conceptual base flow physics model. This imaging data specifically provides insight into the Space Launch System vehicle core-stage and Exploration Upper Stage base environments and further validates short-duration ground test techniques and computational modeling.
    Keywords: Spacecraft Propulsion and Power
    Type: M17-6080 , Aviation Conference (2017); Jun 05, 2017 - Jun 09, 2017; Denver, CO; United States
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  • 5
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    Optical Diagnostic Imaging of Multi-Rocket Plume-Induced Base Flow Environments (2017)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics; Launch Vehicles and Launch Operations
    Type: M17-6208 , Thermal and Fluids Analysis Workshop (TFAWS 2017); Aug 21, 2017 - Aug 25, 2017; Huntsville, AL; United States
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  • 6
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    High Enthalpy Studies of Capsule Heating in an Expansion Tunnel Facility (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Measurements were made on an Orion heat shield model to demonstrate the capability of the new LENS-XX expansion tunnel facility to make high quality measurements of heat transfer distributions at flow velocities from 3 km/s (h(sub 0) = 5 MJ/kg) to 8.4 km/s (h(sub 0) = 36 MJ/kg). Thirty-nine heat transfer gauges, including both thin-film and thermocouple instruments, as well as four pressure gauges, and high-speed Schlieren were used to assess the aerothermal environment on the capsule heat shield. Only results from laminar boundary layer runs are reported. A major finding of this test series is that the high enthalpy, low-density flows displayed surface heating behavior that is observed to be consistent with some finite-rate recombination process occurring on the surface of the model. It is too early to speculate on the nature of the mechanism, but the response of the gages on the surface seems generally repeatable and consistent for a range of conditions. This result is an important milestone in developing and proving a capability to make measurements in a ground test environment and extrapolate them to flight for conditions with extreme non-equilibrium effects. Additionally, no significant, isolated stagnation point augmentation ("bump") was observed in the tests in this facility. Cases at higher Reynolds number seemed to show the greatest amount of overall increase in heating on the windward side of the model, which may in part be due to small-scale particulate.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: JSC-CN-26523 , 43rd AIAA Thermophysics Conference; Jun 25, 2012 - Jun 28, 2012; New Orleans, LA; United States
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  • 7
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    Blunt-Body Aerothermodynamic Database from High-Enthalpy CO2 Testing in an Expansion Tunnel (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An extensive database of heating, pressure, and flow field measurements on a 70-deg sphere-cone blunt body geometry in high-enthalpy, CO2 flow has been generated through testing in an expansion tunnel. This database is intended to support development and validation of computational tools and methods to be employed in the design of future Mars missions. The test was conducted in an expansion tunnel in order to avoid uncertainties in the definition of free stream conditions noted in previous studies performed in reflected shock tunnels. Data were obtained across a wide range of test velocity/density conditions that produced various physical phenomena of interest, including laminar and transitional/turbulent boundary layers, non-reacting to completely dissociated post-shock gas composition and shock-layer radiation. Flow field computations were performed at the test conditions and comparisons were made with the experimental data. Based on these comparisons, it is recommended that computational uncertainties on surface heating and pressure, for laminar, reacting-gas environments can be reduced to +/-10% and +/-5%, respectively. However, for flows with turbulence and shock-layer radiation, there were not sufficient validation-quality data obtained in this study to make any conclusions with respect to uncertainties, which highlights the need for further research in these areas.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NF1676L-22933 , AIAA Aviation 2016; Jun 13, 2016 - Jun 17, 2016; Washington, DC; United States
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  • 8
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    Space Launch System Base Heating Test: Tunable Diode Laser Absorption Spectroscopy (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the Tunable Diode Laser Absorption Spectroscopy (TDLAS) measurement of several water transitions that were interrogated during a hot-fire testing of the Space Launch Systems (SLS) sub-scale vehicle installed in LENS II. The temperature of the recirculating gas flow over the base plate was found to increase with altitude and is consistent with CFD results. It was also observed that the gas above the base plate has significant velocity along the optical path of the sensor at the higher altitudes. The line-by-line analysis of the H2O absorption features must include the effects of the Doppler shift phenomena particularly at high altitude. The TDLAS experimental measurements and the analysis procedure which incorporates the velocity dependent flow will be described.
    Keywords: Launch Vehicles and Launch Operations; Fluid Mechanics and Thermodynamics
    Type: M16-4999 , AIAA SciTech Forum and Exposition, Special Session: Space Launch System (SLS) Induced Environments I; Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
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  • 9
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    Space Launch System Base Heating Test: Tunable Diode Laser Absorption Spectroscopy (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the Tunable Diode Laser Absorption Spectroscopy (TDLAS) measurement of several water transitions that were interrogated during a hot-fire testing of the Space Launch Systems (SLS) sub-scale vehicle installed in LENS II. The temperature of the recirculating gas flow over the base plate was found to increase with altitude and is consistent with CFD results. It was also observed that the gas above the base plate has significant velocity along the optical path of the sensor at the higher altitudes. The line-by-line analysis of the H2O absorption features must include the effects of the Doppler shift phenomena particularly at high altitude. The TDLAS experimental measurements and the analysis procedure which incorporates the velocity dependent flow will be described.
    Keywords: Spacecraft Design, Testing and Performance; Lasers and Masers
    Type: M16-5003 , AIAA SciTech Forum and Exposition, Special Session: Space Launch System (SLS) Induced Environments I; Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
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  • 10
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    Unknown
    Space Launch System Base Heating Test: Environments and Base Flow Physics (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The NASA Space Launch System (SLS) vehicle is composed of four RS-25 liquid oxygen-hydrogen rocket engines in the core-stage and two 5-segment solid rocket boosters and as a result six hot supersonic plumes interact within the aft section of the vehicle during flight. Due to the complex nature of rocket plume-induced flows within the launch vehicle base during ascent and a new vehicle configuration, sub-scale wind tunnel testing is required to reduce SLS base convective environment uncertainty and design risk levels. This hot-fire test program was conducted at the CUBRC Large Energy National Shock (LENS) II short-duration test facility to simulate flight from altitudes of 50 kft to 210 kft. The test program is a challenging and innovative effort that has not been attempted in 40+ years for a NASA vehicle. This paper discusses the various trends of base convective heat flux and pressure as a function of altitude at various locations within the core-stage and booster base regions of the two-percent SLS wind tunnel model. In-depth understanding of the base flow physics is presented using the test data, infrared high-speed imaging and theory. The normalized test design environments are compared to various NASA semi-empirical numerical models to determine exceedance and conservatism of the flight scaled test-derived base design environments. Brief discussion of thermal impact to the launch vehicle base components is also presented.
    Keywords: Spacecraft Design, Testing and Performance; Fluid Mechanics and Thermodynamics; Launch Vehicles and Launch Operations
    Type: M16-5004 , AIAA SciTech Forum and Exposition, Special Session: Space Launch System (SLS) Induced Environments I; Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
    Format: application/pdf
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