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  • 1
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    Navier-Stokes simulations of Orbiter aerodynamic characteristics including pitch trim and bodyflap (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: An analysis of the longitudinal aerodynamics of the shuttle orbiter in the hypersonic flight regime is made through the use of computational fluid dynamics. Particular attention is given to establishing the cause of the 'pitching moment anomaly,' which occurred on the orbiter's first flight, and to computing the aerodynamics of a complete orbiter configuration at flight conditions. Data from ground-based facilities as well as orbiter flight data are used to validate the computed results. Analysis shows that the pitching moment anomaly is a real-gas chemistry effect that was not simulated in ground-based facilities, which used air as a test gas. Computed flight aerodynamics for the orbiter are within 5% of the measured flight values and trim bodyflap deflections are predicted to within 10%.
    Keywords: SPACE TRANSPORTATION
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 31; 3; p. 355-366
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Multiblock analysis for Shuttle Orbiter reentry heating from Mach 24 to Mach 12 (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: A multiblock, laminar heating analysis for the shuttle orbiter at three trajectory points ranging from Mach 24.3 to Mach 12.86 on reentry is described. The analysis is performed using the Langley Aerothermodynamic Upwind Relaxation Algorithm with a seven species chemical nonequilibrium model. A finite-catalytic-wall model appropriate for shuttle tiles at a radiative equilibrium wall temperature is applied. Computed heating levels are generally in good agreement with the flight data, although a few rather large discrepancies remain unexplained. The multiblock relaxation strategy partitions the flowfield into manageable blocks requiring a fraction of the computational resources (time and memory) required by a full domain approach. In fact, the computational cost for a solution at even a single trajectory point would be prohibitively expensive at the given resolution without the multiblock approach. Converged blocks are reassembled to enable a fully coupled converged solution over the entire vehicle, starting from a nearly converged initial condition.
    Keywords: SPACE TRANSPORTATION
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 31; 3; p. 367-377
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Application of axisymmetric analog for calculating heating in three-dimensional flows (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 24; 296-302
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Computed and experimental surface pressure and heating on 70-deg sphere cones (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 24; 385-393
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Aeroassisted Flight Experiment aerodynamic characteristics at flight conditions (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The success of NASA's Aeroassisted Flight Experiment project depends on the suitable placement of instrumentation on the vehicle surface and the ability of the vehicle to fly the maximum science payload. The initial aerodynamic data base was established using wind tunnel data and CFD analyses, where the influence of real-gas effects precluded the use of ground-facility data. More recently, a viscous thermochemical nonequilibrium flow analysis about the complete vehicle, including the wake, has updated the vehicle aerodynamic data base.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 27; 684-686
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  • 6
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    Aerothermodynamics at NASA-Langley Research Center (2001)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Aerothermodynamics Branch at NASA - Langley Research Center is tasked with developing, assessing and applying aerothermodynamic technologies to enable the development of hypersonic aircraft, launch vehicles, and planetary/earth entry systems. To accomplish this mission, the Branch capitalizes on the synergism between the experimental and computational facilities/tools which reside in the branch and a staff that can draw on five decades of experience in aerothermodynamics. The Aerothermodynamics Branch is staffed by 30 scientists/engineers. The staff, of which two-thirds are less than 40 years old, is split evenly between experimentalists and computationalists. Approximately 90 percent of the staff work on space transportation systems while the remainder work on planetary missions. The Branch manages 5 hypersonic wind tunnels which are staffed by 14 technicians, numerous high end work stations and a SGI Origin 2000 system. The Branch also utilizes other test facilities located at Langley as well as other national and international test sites. Large scale computational requirements are met by access to Agency resources.
    Keywords: Aerodynamics
    Type: The Tenth Thermal and Fluids Analysis Workshop; NASA/CP-2001-211141
    Format: application/pdf
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  • 7
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    Predicted aerodynamics for a proposed personnel launch vehicle (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Langley Aerothermodynamic Upwind Relaxation Algorithm has been modified to compute equilibrium flows over shapes at hypersonic velocities. As an initial test of the modified code, solutions were obtained for a paraboloid at Mach 6 wind-tunnel test conditions in CF4 gas and at Mach 16.85 flight conditions in equilibrium air that approximated the normal shock density ratio for the experimental test. Solutions for a lifting-body concept that is proposed for a Personnel Launch System were compared with test results at Mach 6 in CF4 over an angle-of-attack range of 15 to 35 deg and with results for nominal entry flight conditions at Mach 15.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-1668
    Format: text
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  • 8
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    A high angle of attack inviscid shuttle orbiter computation (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As a preliminary step toward predicting the leeside thermal environment for winged reentry vehicles at flight conditions, a computational solution for the flow about the Shuttle Orbiter at wind tunnel conditions was made using a point-implicit, finite volume scheme known as the Langley Aerothermodynamic Upwind Relaxation Algorithm (LAURA). The surface pressures resulting from the computational solution are compared with wind tunnel data. The results indicate that the dominant inviscid flow features are being accurately predicted on the leeside of the Shuttle Orbiter at a moderately high angle of attack.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-107606 , NAS 1.15:107606
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Assured Crew Return Vehicle flowfield and aerodynamic characteristics (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A lifting body has been proposed as a candidate for the Assured Crew Return Vehicle which will serve as crew rescue vehicle for the Space Station. The focus of this work is on body surface definition, surface and volume grid definition, and the computation of inviscid flowfields about the vehicle at wind-tunnel conditions. Very good agreement is shown between the computed aerodynamic characteristics of the vehicle at a freestream Mach number of 10 and those measured in wind-tunnel tests.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-0229
    Format: text
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  • 10
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    Single block three-dimensional volume grids about complex aerodynamic vehicles (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper presents an alternate approach for the generation of volumetric grids for supersonic and hypersonic flows about complex configurations. The method uses parametric two dimensional block face grid definition within the framework of GRIDGEN2D. The incorporation of face decomposition reduces complex surfaces to simple shapes. These simple shapes are combined to obtain the final face definition. The advantages of this method include the reduction of overall grid generation time through the use of vectorized computer code, the elimination of the need to generate matching block faces, and the implementation of simplified boundary conditions. A simple axisymmetric grid is used to illustrate this method. In addition, volume grids for two complex configurations, the Langley Lifting Body (HL-20) and the Space Shuttle Orbiter, are shown.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-108986 , NAS 1.15:108986
    Format: application/pdf
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