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  • 1
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    Aerothermodynamics of blunt body entry vehicles (2012)
    Elsevier
    Details
    Publication Date: 2012-01-01
    Print ISSN: 0376-0421
    Electronic ISSN: 1873-1724
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    Aerothermodynamics of Blunt Body Entry Vehicles (2011)
    In:  CASI
    Details
    Publication Date: 2018-06-28
    Description: In this chapter, the aerothermodynamic phenomena of blunt body entry vehicles are discussed. Four topics will be considered that present challenges to current computational modeling techniques for blunt body environments: turbulent flow, non-equilibrium flow, rarefied flow, and radiation transport. Examples of comparisons between computational tools to ground and flight-test data will be presented in order to illustrate the challenges existing in the numerical modeling of each of these phenomena and to provide test cases for evaluation of Computational Fluid Dynamics (CFD) code predictions.
    Keywords: Astrodynamics
    Type: Assessment of Aerothermodynamic Flight Prediction Tools Through Ground and Flight Experimentation; 3-1 - 3-32; AC/323(AVT-136)TP/388
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Laminar, Transitional, and Turbulent Heating on Mid Lift-to-Drag Ratio Entry Vehicles (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The boundary-layer transition characteristics and convective aeroheating levels on mid lift-to-drag ratio entry vehicle configurations have been studied through wind-tunnel testing. Several configurations were investigated, including elliptically blunted cylinders with both circular and elliptically flattened cross sections, biconic geometries based on launch vehicle dual-use shrouds, and parametrically optimized analytic geometries. Vehicles of this class have been proposed for high-mass Mars missions, such as sample return and crewed exploration, for which the conventional sphere-cone entry-vehicle geometries of previous Mars missions are insufficient. Testing was conducted at Mach 6 over a range of Reynolds numbers sufficient to generate laminar, transitional, and turbulent flow. Transition onset locations, both straight-line and cross-flow, and heating rates were obtained through global phosphor thermography. Supporting computations were performed to obtain heating rates for comparison with the data. Laminar data and predictions agreed to well within the experimental uncertainty. Fully turbulent data and predictions also agreed well. However, in transitional flow regions, greater differences were observed.
    Keywords: Aerodynamics
    Type: NF1676L-22328 , Journal of Spacecraft and Rockets; 50; 5; 937-959|AIAA Fluid Dynamics Conference and Exhibit; Jun 25, 2012 - Jun 28, 2012; New Orleans, LA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Assessment of Laminar, Convective Aeroheating Prediction Uncertainties for Mars-Entry Vehicles (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An assessment of computational uncertainties is presented for numerical methods used by NASA to predict laminar, convective aeroheating environments for Mars-entry vehicles. A survey was conducted of existing experimental heat transfer and shock-shape data for high-enthalpy reacting-gas CO2 flows, and five relevant test series were selected for comparison with predictions. Solutions were generated at the experimental test conditions using NASA state-of-the-art computational tools and compared with these data. The comparisons were evaluated to establish predictive uncertainties as a function of total enthalpy and to provide guidance for future experimental testing requirements to help lower these uncertainties.
    Keywords: Statistics and Probability; Numerical Analysis; Fluid Mechanics and Thermodynamics; Spacecraft Design, Testing and Performance
    Type: AIAA Paper 2011-3144 , NF1676L-22324 , AIAA Thermophysics Conference; Jun 27, 2011 - Jun 30, 2011; Honolulu, HI; United States|Journal of Spacecraft and Rockets; 50; 1; 56-68
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  • 5
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    Laminar, Transitional, and Turbulent Heating on Mid Lift-to-Drag Ratio Entry Vehicles (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The boundary-layer transition characteristics and convective aeroheating levels on mid lift-to-drag ratio entry vehicle configurations have been studied through wind tunnel testing. Several configurations were investigated, including elliptically-blunted cylinders with both circular and elliptically-flattened cross sections, biconic geometries based on launch vehicle dual-use shrouds, and parametrically-optimized analytic geometries. Vehicles of this class have been proposed for high-mass Mars missions, such as sample return and crewed exploration, for which the conventional sphere-cone entry-vehicle geometries of previous Mars missions are insufficient. Testing was conducted at Mach 6 over a range of Reynolds numbers sufficient to generate laminar, transitional, and turbulent flow. Transition onset locations - both straight-line and cross-flow - and heating rates were obtained through global phosphor thermography. Supporting computations were performed to obtain heating rates for comparison with the data. Laminar data and predictions agreed to well within the experimental uncertainty. Fully-turbulent data and predictions also agreed well. However, in transitional flow regions, greater differences were observed. Additional aerodynamic performance data were also generated through Modified-Newtonian analyses of the geometries.
    Keywords: Aerodynamics
    Type: NF1676L-13809 , 42nd AIAA Fluid Dynamics Conference and Exhibit; Jun 25, 2012 - Jun 28, 2012; New Orleans, LA; United States
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    NASA TECHNICAL REPORTS
  • 6
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    Assessment of Laminar, Convective Aeroheating Prediction Uncertainties for Mars Entry Vehicles (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An assessment of computational uncertainties is presented for numerical methods used by NASA to predict laminar, convective aeroheating environments for Mars entry vehicles. A survey was conducted of existing experimental heat-transfer and shock-shape data for high enthalpy, reacting-gas CO2 flows and five relevant test series were selected for comparison to predictions. Solutions were generated at the experimental test conditions using NASA state-of-the-art computational tools and compared to these data. The comparisons were evaluated to establish predictive uncertainties as a function of total enthalpy and to provide guidance for future experimental testing requirements to help lower these uncertainties.
    Keywords: Lunar and Planetary Science and Exploration
    Type: AIAA Paper 2011-3144 , NF1676L-11674 , 42nd AIAA Thermophysics Conference; Jun 27, 2011 - Jun 30, 2011; Honolulu, HI; United States
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  • 7
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    Compression Pad Cavity Heating Augmentation on Orion Heat Shield (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An experimental study has been conducted to assess the effects of compression pad cavities on the aeroheating environment of the Project Orion Crew Exploration Vehicle heat shield. Testing was conducted in Mach 6 and 10 perfect-gas wind tunnels to obtain heating measurements in and around the compression pads cavities using global phosphor thermography. Data were obtained over a wide range of Reynolds numbers that produced laminar, transitional, and turbulent flow within and downstream of the cavities. The effects of cavity dimensions on boundary-layer transition and heating augmentation levels were studied. Correlations were developed for transition onset and for the average cavity-heating augmentation.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 2009-3843 , NF1676L-13369 , 41st AIAA THermophysics Conference; Jun 22, 2009 - Jun 25, 2009; San Antonio, TX|Journal of Thermophysics and Heat Transfer; 25; 3; 329-340
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  • 8
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    Mars Science Laboratory Heatshield Aerothermodynamics: Design and Reconstruction (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Mars Science Laboratory heatshield was designed to withstand a fully turbulent heat pulse based on test results and computational analysis on a pre-flight design trajectory. Instrumentation on the flight heatshield measured in-depth temperatures in the thermal protection system. The data indicate that boundary layer transition occurred at 5 of 7 thermocouple locations prior to peak heating. Data oscillations at 3 pressure measurement locations may also indicate transition. This paper presents the heatshield temperature and pressure data, possible explanations for the timing of boundary layer transition, and a qualitative comparison of reconstructed and computational heating on the as-flown trajectory. Boundary layer Reynolds numbers that are typically used to predict transition are compared to observed transition at various heatshield locations. A uniform smooth-wall transition Reynolds number does not explain the timing of boundary layer transition observed during flight. A roughness-based Reynolds number supports the possibility of transition due to discrete or distributed roughness elements on the heatshield. However, the distributed roughness height would have needed to be larger than the pre-flight assumption. The instrumentation confirmed the predicted location of maximum turbulent heat flux near the leeside shoulder. The reconstructed heat flux at that location is bounded by smooth-wall turbulent calculations on the reconstructed trajectory, indicating that augmentation due to surface roughness probably did not occur. Turbulent heating on the downstream side of the heatshield nose exceeded smooth-wall computations, indicating that roughness may have augmented heating. The stagnation region also experienced heating that exceeded computational levels, but shock layer radiation does not fully explain the differences.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NF1676L-15617 , AIAA Thermophysics Conference; Jun 24, 2013 - Jun 27, 2013; San Diego, CA; United States
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  • 9
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    Experimental Aeroheating Study of Mid-L/D Entry Vehicle Geometries: NASA LaRC 20-Inch Mach 6 Air Tunnel Test 6966 (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Aeroheating data on mid lift-to-drag ratio entry vehicle configurations has been obtained through hypersonic wind tunnel testing. Vehicles of this class have been proposed for high-mass Mars missions, such as sample return and crewed exploration, for which the conventional sphere-cone entry vehicle geometries of previous Mars missions are insufficient. Several configurations were investigated, including elliptically-blunted cylinders with both circular and elliptical cross sections, biconic geometries based on launch vehicle dual-use shrouds, and parametrically-optimized analytic geometries. Testing was conducted at Mach 6 over a range of Reynolds numbers sufficient to generate laminar, transitional, and turbulent flow. Global aeroheating data were obtained using phosphor thermography. Both stream-wise and cross-flow transition occured on different configurations. Comparisons were made with laminar and turbulent computational predictions generated with an algebraic turbulence model. Predictions were generally in good agreement in regions of laminar or fully-turbulent flow; however for transitional cases, the lack of a transition onset prediction capability produced less accurate comparisons. The data obtained in this study are intended to be used for prelimary mission design studies and the development and validation of computational methods.
    Keywords: Aerodynamics; Fluid Mechanics and Thermodynamics
    Type: NASA/TM-2014-218549 , L-20433 , NF1676L-19207
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Entry, Descent, and Landing Aerothermodynamics: NASA Langley Experimental Capabilities and Contributions (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A review is presented of recent research, development, testing and evaluation activities related to entry, descent and landing that have been conducted at the NASA Langley Research Center. An overview of the test facilities, model development and fabrication capabilities, and instrumentation and measurement techniques employed in this work is provided. Contributions to hypersonic/supersonic flight and planetary exploration programs are detailed, as are fundamental research and development activities.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper-2014-1154 , NF1676L-16744 , AIAA Aerospace Sciences Meeting; Jan 13, 2014 - Jan 17, 2014; National Harbor, MD; United States
    Format: application/pdf
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