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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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  • 2
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    HL-20 computational fluid dynamics analysis (1993)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: The essential elements of a computational fluid dynamics analysis of the HL-20/personnel launch system aerothermal environment at hypersonic speeds including surface definition, grid generation, solution techniques, and visual representation of results are presented. Examples of solution technique validation through comparison with data from ground-based facilities are presented, along with results from computations at flight conditions. Computations at flight points indicate that real-gas effects have little or no effect on vehicle aerodynamics and, at these conditions, results from approximate techniques for determining surface heating are comparable with those obtained from Navier-Stokes solutions.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 30; 5; p. 558-566.
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  • 3
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    Approximate method for calculating heating rates on three-dimensional vehicles (1994)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: An approximate method for calculating heating rates on three-dimensional vehicles at angle of attack is presented. The method is based on the axisymmetric analog for three-dimensional boundary layers and uses a generalized body-fitted coordinate system. Edge conditions for the boundary-layer solution are obtained from an inviscid flowfield solution, and because of the coordinate system used, the method is applicable to any blunt body geometry for which an inviscid flowfield solution can be obtained. The method is validated by comparing with experimental heating data and with thin-layer Navier-Stokes calculations on the shuttle orbiter at both wind-tunnel and flight conditions and with thin-layer Navier-Stokes calculations on the HL-20 at wind-tunnel conditions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 31; 3; p. 345-354
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  • 4
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    Comparison of heating calculations with experimental data on a modified Shuttle Orbiter (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 208-215
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  • 5
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    Viscous equilibrium computations using program LAURA (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: Modifications have been made to the Langley Aerothermodynamic Upwind Relaxation Algorithm (LAURA) that enable it to compute viscous airflows under the assumption of thermal and chemical equilibrium. Equilibrium thermodynamic and transport property information are input to the code via curve fits. The periodic updating of this information enables the equilibrium algorithm to perform at a computational rate that is only a small percentage larger than the rate associated with the perfect-gas algorithm. Presented in this article are the results of the initial validation of the modified code. Solutions for surface pressure and heating are presented for the flow over slender and blunt cones at realistic reentry conditions. LAURA solutions are compared with those produced by a viscous shock-layer method, and, for one case considered, with heat transfer data from a flight experiment. For both pressure and heating, the agreement is good. In general, differences in pressure of a few percent were noted, while differences in heating rates were in the 5-10 percent range.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 5; p. 627-632.
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  • 6
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    Predicted aerodynamics for a proposed personnel launch vehicle (1990)
    In:  Other Sources
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    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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  • 7
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    Viscous equilibrium computations using program LAURA (1991)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The Langley Aerothermodynamic Upwind Relaxation Algorithm (LAURA) has been modified to compute viscous equilibrium flow. Periodic calls to the thermodynamic and transport property curve-fits enable solutions to be computed for small percentage increase in computer time when compared with perfect gas times. The code is used to compute the hypersonic flow over slender and blunt cones, and solutions are compared with other computational techniques and flight data.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-1389
    Format: text
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  • 8
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    Assured Crew Return Vehicle flowfield and aerodynamic characteristics (1990)
    In:  Other Sources
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    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
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  • 9
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    Numerical analysis and simulation of an assured crew return vehicle flow field (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A lifting body was proposed as a candidate for the Assured Crew Return Vehicle (ACRV) which will serve as a crew rescue vehicle for the Space Station Freedom. The focus is on body surface definition, both surface and volume grid definition, and the computation of inviscid flow fields about the vehicle at wind tunnel conditions. Very good agreement is shown between the computed aerodynamic characteristics of the vehicle at M(sub infinity) = 10 and those measured in wind tunnel tests at high Reynolds numbers.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TP-3101 , L-16836 , NAS 1.60:3101
    Format: application/pdf
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  • 10
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    A computational study of the flowfield surrounding the Aeroassist Flight Experiment vehicle (1987)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A symmetric total variation diminishing (STVD) algorithm has been applied to the solution of the three-dimensional hypersonic flowfield surrounding the Aeroassist Flight Experiment (AFE) vehicle. Both perfect-gas and chemical nonequilibrium models have been used. The perfect-gas flows were computed at two different Reynolds numbers, including a flight trajectory point at maximum dynamic pressure, and on two different grids. Procedures for coupling the solution of the species continuity equations with the Navier-Stokes equations in the presence of chemical nonequilibrium are reviewed and tested on the forebody of the AFE and on the complete flowfield assuming noncatalytic wall and no species diffusion. Problems with the STVD algorithm unique to flows with variable thermodynamic properties (real gas) are identified and algorithm modifications are suggested. A potential heating problem caused by strong flow impingement on the nozzle lip in the near wake at 0-deg angle of attack has been identified.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-1575
    Format: text
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