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  • 1
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    Raman scattering applied to hypersonic air flow (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The Raman scattering technique was applied to measure the local static temperature and gas number density over a sharp-edge flat-plate model in a Mach 5 nozzle of the Langley nozzle test chamber with air as the test gas. The angle of attack varied from -5 to 15 deg, and the stagnation temperature varied from 317 to 442 K, with stagnation pressures ranging from 170 kN to 2.8 MN/sq m. The measured values of static temperature and density ranged from 60 to 100 K and from 0.03 to 0.8 kg/cu m, respectively. A comparison with calculated values based on static pressure measurements along the model shows that the Raman scattering technique is a viable measurement method in applications to high-speed three-dimensional flows.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA Journal; 12; Aug. 197
    Format: text
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  • 2
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    Use of moderate-length hot wires to survey a hypersonic boundary layer. (1967)
    In:  Other Sources
    Details
    Publication Date: 2011-08-11
    Description: Transition region of hypersonic boundary layer on flat plate surveyed with hot wires, giving analysis for limited wire calibration
    Keywords: FLUID MECHANICS
    Type: AIAA JOURNAL
    Format: text
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  • 3
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    Use of discrete sonic jets as boundary-layer trips in hypersonic flow (1970)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Discrete sonic jets as boundary layer trips producing turbulent hypersonic flows with negligible intrinsic drag and downstream distortions
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; SEARCH(
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  • 4
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    Effect of mass injection into a cavity on hypersonic boundary-layer transition. (1966)
    In:  Other Sources
    Details
    Publication Date: 2011-08-11
    Description: Effect of mass injection into cavity on hypersonic boundary layer transition and on heating downstream
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA JOURNAL
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  • 5
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    Evidence of imbedded vortices in a three-dimensional shear flow (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Vortex phenomena encountered in an investigation of the streamwise development of the three-dimensional wake region behind the tip of a three-dimensional wedge model are reported. Pressure profiles were measured by pitot probes downstream of a tip with a nearly constant surface pressure level and a nearly continuous surface curvature in a blowdown air tunnel operating at Mach 6. Rather than the simple three-dimensional quasi-parallel shear flow expected, the measurements indicated the presence of a flow with large deficits in longitudinal pitot pressure, which are usually associated with the core region of quasi-steady longitudinal vortices. Vapor screen flow visualizations also support the presence of longitudinal vortices located primarily in the tip region and evidently forming in the vicinity of the wake neck. An increase in overall wake thickness by 100% is also observed. The origin of the vortices as quasi-steady Taylor-Gortler vortices generated in the concavely curved shear layer near the wake neck is considered. It is pointed out that the existence of longitudinal vortexes suggests that three-dimensional turbulence modeling may be much more difficult than previously supposed.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Mar. 198
    Format: text
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  • 6
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    Roughness induced transition criteria for space shuttle-type vehicles (1976)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Tripping effectiveness of surface roughness on a delta wing shuttle orbiter model at 20 deg angle of attack is compared to that on plane and axisymmetrical bodies with and without longitudinal pressure gradients. The experimental data presented are compared on the basis of effective roughness Reynolds number since this parameter is not sensitive to flow conditions downstream of the roughness. The discussion covers the effective roughness Reynolds number as a function of roughness position Reynolds number, effective size ratio as a function of pressure gradient and distance from vehicle nose, and effect of spanwise roughness position on roughness effectiveness. It is shown that conventional criteria for sizing roughness elements which promote transition in two-dimensional zero-pressure gradient flows are insufficient for high-pressure gradient flows and three-dimensional flows. Roughness much smaller than that given by conventional criteria can cause transition and significantly increase the heating load.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 13; Feb. 197
    Format: text
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  • 7
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    Transition fixing for hypersonic flow (1967)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: GENERAL
    Type: Conf. on Hypersonic Aircraft Technol.; p 203-222
    Format: application/pdf
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  • 8
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    Aerodynamic characteristics of a family of multistage missiles at a mach number of 6.0 (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Wind tunnel investigation of aerodynamic characteristics of cone-cylinder-flare multistage missile configurations at supersonic speed
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-2853
    Format: application/pdf
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  • 9
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    Effects of cone surface waviness and freestream noise on transition in supersonic flow (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A comparison of transition on wavy-wall and smooth-wall cones in a Mach 3.5 wind tunnel is made under conditions of either low freestream noise (quiet flow) or high freestream noise (noisy flow). The noisy flow compares to that found in conventional wind tunnels while the quiet flow gives transitional Reynolds numbers on smooth sharp cones comparable to those found in flight. The waves were found to have a much smaller effect on transition than similar sized trip wires. A satisfatory correlating parameter for the effect of waves on transition was simply the wave height-to-length ratio. A given value of this ratio was found to cause the same percentage change in transition location in quiet and noisy flows.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-1086
    Format: text
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  • 10
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    Roughness effects on boundary-layer transition for blunt-leading-edge plates at Mach 6 (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Effects of controlled roughness on boundary layer transition for upswept blunted plates in free stream
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-3517
    Format: application/pdf
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