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  • 1
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    Preliminary measurements and flow visualization studies of pressure fluctuations on space shuttle configurations (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Transonic wind tunnel investigation of flow characteristics and pressure fluctuation of space shuttle launch and reentry configurations
    Keywords: STRUCTURAL MECHANICS
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 3 APR. 1971; P 293-314
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    In-flight aeroacoustic environments on prospective space shuttle vehicles (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The problem of in-flight aerodynamic noise has been studied by reliable estimates of full scale surface-pressure fluctuations from scale model tests in wind tunnels. Scaling relationships have been verified, and many details of the fluctuating pressure characteristics such as spatial correlation and convection velocities are understood. The effects of the wind tunnel environmental turbulence and noise have also been investigated sufficiently so that threshold levels of usable data are known.
    Keywords: AERODYNAMICS
    Type: NASA Space Shuttle Technol. Conf.; p 71-96
    Format: text
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  • 3
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    An analysis of the rotor blade stresses of the three stage compressor of the Ames Research Center 11- by 11-foot transonic wind tunnel (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The static and dynamic rotor blade stresses of the three stage compressor were measured. Data are presented in terms of total blade stress for the complete operational range of compressor speeds and tunnel total pressures. Modal frequencies and variations with tunnel conditions were measured. Phase angles and coherences between various gage combinations are also presented. Recommendations for improvements are given for future rotor blade experimental investigations.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-152083
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Overall fluctuating pressure levels on prospective space shuttle launch configurations at Mach numbers from 0.8 to 2.2 (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Overall fluctuating pressure levels of seven space shuttle launch configurations are presented. The model was a 4-percent-scale space shuttle vehicle, tested in both a 11- by 11-foot transonic wind tunnel and a 9- by 7-foot supersonic wind tunnel. Mach numbers varied from 0.8 to 2.2, and the angle of attack range was from -8 deg to 8 deg at angles of sideslip of -5 deg, and 5 deg. The model configurations included both series-burn and parallel-burn configurations, two canopy configurations, two positions of the orbiter nose relative to the HO tank nose and two HO tank nose-cone angles (15 deg and 20 deg). The fluctuating pressure levels are presented in three forms.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-62280
    Format: application/pdf
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  • 5
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    Wind tunnel measurements of surface pressure fluctuations at Mach numbers of 1.6, 2.0, and 2.5 using 12 different transducers (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The turbulent boundary layer on the wall of a 9 by 7 foot wind tunnel was measured with 12 different transducers at Mach numbers of 1.6, 2.0, and 2.5. The results indicated that the wall surface-pressure-fluctuation field was more homogeneous at a Mach number of 2.5 than at Mach numbers of 1.6 or 2.0. A comparison of power-spectral-density data at Mach 2.5 with a summary of similar data (Mach 0.1 to 3.45) showed good agreement. The measurement uncertainty was greatest when frequencies were low and the surface-pressure-fluctuation field was homogeneous. The uncertainty at higher frequencies increased as the surface-pressure-fluctuation field became more inhomogeneous. Since transducer mounting effects and system noise levels were determined not to have contributed appreciably to measurement uncertainties, the result was attributed to an interaction between the surface-pressure-fluctuation field and the transducers. Corcos' correction for size effects improved the comparison between transducers at the high frequencies, but did not eliminate an apparent size effect at the lower frequencies.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TN-D-7087 , H-700
    Format: application/pdf
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  • 6
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    Shadowgraphs of air flow over prospective space shuttle configurations at Mach numbers from 0.8 to 1.4 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Shadowgraphs of five space shuttle launch configurations are presented. The model was a 4 percent-scale space shuttle vehicle, tested in the 11- by 11-foot Transonic Wind Tunnel at Ames Research Center. The Mach number was varied from 0.8 to 1.4 with three angles of sideslip (0 deg, 5 deg and -5 deg) that were used in conjunction with three angles of attack (4 deg, -4 deg, and 0 deg). The model configurations included both series-burn and parallel-burn configurations, two canopy configurations, two positions of the orbiter nose relative to the HO tank nose, and two HO tank nose-cones angles (15 deg and 20 deg). The data consist entirely of shadowgraph photographs.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-TM-X-62444 , A-6099
    Format: application/pdf
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  • 7
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    Evaluation of transonic and supersonic wind-tunnel background noise and effects of surface pressure fluctuation measurements. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA PAPER 72-1004 , American Institute of Aeronautics and Astronautics, Aerodynamic Testing Conference; Sept. 13-15, 1972; Palo Alto, CA
    Format: text
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  • 8
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    Effect of gaseous and solid simulated jet plumes on an 040A space shuttle launch configuration at m=1.6 to 2.2 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of plume-induced flow separation and aspiration effects due to operation of both orbiter and the solid rocket motors on a 0.019-scale model of the launch configuration of the Space Shuttle Vehicle is determined. Longitudinal and lateral-directional stability data were obtained at Mach numbers of 1.6, 2.0, and 2.2 with and without the engines operating. The plumes exiting from the engines were simulated by a cold-gas jet supplied by an auxiliary 200-atm air supply system and solid-body plume simulators. The aerodynamic effects produced by these two simulation procedures are compared. The parameters most significantly affected by the jet plumes are pitching moment, elevon control effectiveness, axial force, and orbiter wing loads. The solid rocket motor (SRM) plumes have the largest effect on the aerodynamic characteristics. The effect of the orbiter plumes in combination with the SRM plumes is also significant. Variations in the nozzle design parameters and configuration changes can reduce the jet plume-induced aerodynamic effects.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-3032 , A-5212
    Format: application/pdf
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  • 9
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    Pressure fluctuations underlying attached and separated supersonic turbulent boundary layers and shock waves. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 73-996 , Aero-Acoustics Conference; Oct 15, 1973 - Oct 17, 1973; Seattle, WA
    Format: text
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  • 10
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    Crossflow effects on steady and fluctuating pressures on an ogive-cylinder cone-frustum model in supersonic separated flow (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind-tunnel tests were conducted on an ogive-cylinder model with two axisymmetric protuberances having cone frustum angles of cone = 23 deg and 45 deg that were used to generate detached shock waves and the resulting separated flow areas downstream of the shock. The tests were conducted in a 9 by 7 foot supersonic wind tunnel at a free-stream Mach number of 2.0 and at Reynolds numbers of 1.5 x 1 million and 3.9 x 1 million, based on body diameter. The model had an afterbody fineness ratio of 8.3, and the ogive nose had a fineness ratio of 3.0. Two characteristics of the fluctuating pressures in surface vortex flows that result from the crossflow component, (velocity along the tunnel longitudinal axis free stream angle of attack), in combination with changes in the longitudinal pressure gradient were measured: (1) the broadband, rms-pressure coefficients and (2) the power spectral densities. Measurements are presented for various flow regions on the model such as the attached turbulent boundary layer, the detached frustum shock wave, and separated flow areas. The results indicate that the pressure fluctuations around or in the neighborhood of the foci of the vortex flows had broadband intensities and power spectral densities nearly identical to the levels previously measured in separated-flow regions at angles of attack of 0 deg.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1951 , A-8563
    Format: application/pdf
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