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  • Other Sources  (8)
  • THERMODYNAMICS AND COMBUSTION  (6)
  • RESEARCH AND SUPPORT FACILITIES (AIR)  (2)
  • 1
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    Orderly three-dimensional processes in turbulent boundary layers on ablating bodies (1968)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Orderly three dimensional processes in turbulent boundary layers on biconic, concave, and convex ablating bodies in Mach 7 airstream
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AGARD HYPERSONIC BOUNDARY LAYERS AND FLOW FIELDS MAY 1968 (SEE N69-10186 01-01)
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Theory for radiatively driven harmonic acoustic waves in a confined gas. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A detailed theoretical study is made of radiatively driven acoustic waves inside a closed cylindrical tube. The formulation accounts for all the essential phenomena for a gas in vibrational equilibrium - namely, gas motion, longitudinal and radial viscous dissipation, longitudinal and radial heat conduction, and radiative transfer with spectral detail included. An approximate expression is derived for the pressure response. This solution is applicable to arbitrary spectral distribution of the radiative absorption coefficient, under conditions attainable in the laboratory. The solution includes both tuned and untuned acoustic conditions as well as the spectrophone limit - that is, the condition where the length of the tube is much smaller than the length of the acoustic wave. The influence of spectral detail on the pressure response is illustrated.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AD-776848 , AFOSR-74-0403TR , Physics of Fluids; 16; Aug. 197
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    NASA TECHNICAL REPORTS
  • 3
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    The shock tube as a device for testing transonic airfoils at high Reynolds numbers (1978)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A performance analysis of gas-driven shock tubes shows that transonic airfoil flows with chord Reynolds numbers in the range of 100 million can be generated behind the primary shock in a large shock tube. A study of flow over simple airfoils has been carried out at low and intermediate Reynolds numbers to assess the testing technique. Results obtained from schlieren photos and airfoil pressure measurements show that steady transonic flows similar to those observed for the airfoils in wind tunnels can be generated within the available testing time in a shock tube with either properly-contoured test section walls or a properly-designed slotted-wall test section. The study indicates that the shock tube is a useful facility for studying two-dimensional high Reynolds number transonic airfoil flows.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 78-769 , Aerodynamic Testing Conference; Apr 19, 1978 - Apr 21, 1978; San Diego, CA
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  • 4
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    Use of shock tubes in high Reynolds number transonic testing (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The shock tube as a device to fulfill current needs for testing of transonic airfoils at high Reynolds numbers is considered. Performance analysis of a gas-driven shock tube shows that transonic airfoil flows with chord Reynolds numbers in the range of 100 million can be produced. A study of flow development over a simple airfoil has been carried out in a shock tube at low and intermediate Reynolds numbers to assess the testing technique. Results obtained from schlieren photography and airfoil pressure measurements show that steady transonic flows similar to those produced for the same airfoil in a wind tunnel can be generated within the available testing time in a shock tube with properly contoured test section walls. The study indicates that the shock tube is a viable alternative as a facility for studying high Reynolds number transonic airfoil flows.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: Modern developments in shock tube research; Jul 14, 1975 - Jul 16, 1975; Kyoto; Japan
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  • 5
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    Experiments on radiatively driven harmonic acoustic waves in a confined gas. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Measurements are presented of the acoustic pressure resulting from the periodic absorption and emission of radiative energy by an infrared-active gas contained in a closed, cylindrical tube. The acoustic waves are generated by means of an external, sinusoidally time-modulated blackbody source. The pressure measurements are for both resonant and nonresonant conditions at acoustic frequencies from about 60 to 600 Hz. Comparison of the measurements with predictions shows that the response is due primarily to the modified-classical acoustic wave, but that a small contribution from the so-called radiation-induced wave can be measured in certain of the tests. Strong effects of vibrational nonequilibrium, similar to those observed previously in spectrophone studies, were found in some of the tests.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Physics of Fluids; 16; Aug. 197
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  • 6
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    Ballistic range tests of ablating and nonablating slender cones (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Ballistic range tests to study ablation effects on aerodynamic characteristics of ablating and nonablating slender cones
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 69-179 , ; ADEMIE DES SCIENCES|AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE SCIENCES MEETING, 7TH; Jan 20, 1969 - Jan 22, 1969; NEW YORK, NY
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  • 7
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    Ballistic range tests of ablating and nonablating slender cones. (1969)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Ballistic range tests to study ablation effects on aerodynamic characteristics of ablating and nonablating slender cones
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 69-179 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE SCIENCES MEETING; Jan 20, 1969 - Jan 22, 1969; NEW YORK, NY
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  • 8
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    Orderly three-dimensional processes in turbulent boundary layers on ablating bodies (1968)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Flow model for three dimensional processes in turbulent boundary layers of ablating hypersonic Plexiglas bodies
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-61188 , SPEC. MEETING ON HYPERSONIC BOUNDARY LAYERS AND FLOW FIELDS; May 01, 1968 - May 03, 1968; LONDON
    Format: application/pdf
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