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  • 1
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    Convective heat transfer to a blunt lifting body (1960)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: GENERAL
    Type: Joint Conf. on Lifting Manned Hypervelocity and Reentry Vehicles, part 1; p 121-140
    Format: text
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  • 2
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    Low aspect ratio wing code validation experiment (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 31; 10; p. 1744-1752.
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  • 3
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    Effects of roughness on heating and boundary-layer transition. Part 1: Effects of simulated panel joints on boundary-layer transition (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: The effects of distributed roughness, arising from space shuttle orbiter panel joints, on boundary layer transition are investigated. The North American Rockwell 134B delta wing shuttle configuration was used for the study. Results show: (1) Premature boundary layer transition occurred in models having simulated heat shield panels with rased joints. (2) Laminar flow was maintained with slot type panel joint models to a Reynolds number twice that at which transition occurred in raised joints. (3) Significant increases in peak surface temperature and the time during which turbulent flow occurs may result from distributed roughness of heat shield panel joints. (4) Laminar and turbulent heating levels were predicted within available theories. (5) A complex interference between the wing and fuselage flow was observed in the delta wing model.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 375-394
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  • 4
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    Shock interference heating and density-ratio effects. Part 1 - Flow field visualization, thermocouple measurements, and analysis (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Flow visualization, thermocouple measurements, and analyses of shock interference heating effects on straight wing space shuttle model
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 1 APR. 1971; P 185-215
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  • 5
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    Flow fields and aerodynamic heating of space shuttle orbiters (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Wind tunnel simulations of flow fields and aerothermodynamics of space shuttle orbiters
    Keywords: FLUID MECHANICS
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 1 APR. 1971; P 21-73
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  • 6
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    Features of a reattaching turbulent shear layer in divergent channel flow (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Experimental data have been obtained in an incompressible turbulent flow over a rearward-facing step in a diverging channel flow. Mean velocities, Reynolds stresses, and triple products that were measured by a laser Doppler velocimeter are presented for two cases of tunnel wall divergence. Eddy viscosities, production, convection, turbulent diffusion, and dissipation (balance of kinetic energy equation) terms are extracted from the data. These data are compared with various eddy-viscosity turbulence models. Numerical calculations incorporating the k-epsilon and algebraic-stress turbulence models are compared with the data. When determining quantities of engineering interest, the modified algebraic-stress model (ASM) is a significant improvement over the unmodified ASM and the unmodified k-epsilon model; however, like the others, it dramatically overpredicts the experimentally determined dissipation rate.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal (ISSN 0001-1452); 23; 163-171
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  • 7
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    Static aerodynamics, flow fields and aerodynamic heating of space shuttle orbiters (1970)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Wind tunnel tests of aerodynamic stability, boundary layer transition, and heat transfer in space shuttle orbiters
    Keywords: AERODYNAMICS
    Type: SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 1 JUL. 1970; P 142-193
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  • 8
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    Seeding subsonic, transonic and supersonic flows with 0.5 micron polystyrene spheres (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Polystyrene latex particles have been successfully used as laser velocimetry seed material for flows in the Ames High Reynolds Channels (HR) 1 and 2, the pilot channel, and the one-foot low speed tunnel. These facilities provide test flows with Mach numbers from 0.1 to 3.0 and test section sizes from 4 inches by 6 inches to 18 inches by 24 inches. Tunnel mass flow in the HR-2 channel can approach 1000 lb/sec. The latex particles have the following favorable characteristics: size of 0.35 to 0.55 microns diameter; spherical shape; specific gravity of 1.05; excellent flow trackability; low toxicity; and low cost. they have the disadvantage of being packaged as an aqueous suspension which must be diluted and introduced into the test flow as an atomized mist. This must occur sufficiently far upstream of the test section to minimize flow disturbances and permit the liquid mist to evaporate before reaching the model. Several techniques which have been developed to accomplish satisfactory seeding will be described.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Langley Research Center Wind Tunnel Seeding Systems for Laser Velocimeters; p 179-187
    Format: application/pdf
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  • 9
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    Development of a new laser Doppler velocimeter for the Ames High Reynolds Channel No. II (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A new two-channel laser Doppler velocimeter developed for the Ames High Reynolds Channel No. 2 is described. Design features required for the satisfactory operation of the optical system in the channel environment are discussed. Fiber optics are used to transmit the megahertz Doppler signal to the photodetectors located outside the channel pressure vessel, and provision is made to isolate the optical system from pressure and thermal strain effects. Computer-controlled scanning mirrors are used to position the laser beams in the channel flow. Techniques used to seed the flow with 0.5-micron-diam polystyrene spheres avoiding deposition on the test-section windows and porous boundary-layer removal panels are described. Preliminary results are presented with a discussion of several of the factors affecting accuracy.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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  • 10
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    A supercritical airfoil experiment (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this investigation is to provide a comprehensive data base for the validation of numerical simulations. The objective of the present paper is to provide a tabulation of the experimental data. The data were obtained in the two-dimensional, transonic flowfield surrounding a supercritical airfoil. A variety of flows were studied in which the boundary layer at the trailing edge of the model was either attached or separated. Unsteady flows were avoided by controlling the Mach number and angle of attack. Surface pressures were measured on both the model and wind tunnel walls, and the flowfield surrounding the model was documented using a laser Doppler velocimeter (LDV). Although wall interference could not be completely eliminated, its effect was minimized by employing the following techniques. Sidewall boundary layers were reduced by aspiration, and upper and lower walls were contoured to accommodate the flow around the model and the boundary-layer growth on the tunnel walls. A data base with minimal interference from a tunnel with solid walls provides an ideal basis for evaluating the development of codes for the transonic speed range because the codes can include the wall boundary conditions more precisely than interference connections can be made to the data sets.
    Keywords: Aerodynamics
    Type: OTN-035236 , OTN-BIBL-AGARD-AR-303-Vol-2
    Format: text
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