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  • 1
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    In-flight aeroacoustic environments on prospective space shuttle vehicles (1972)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: 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.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA Space Shuttle Technol. Conf.; p 71-96
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 2
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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
    Publikationsdatum: 2019-06-27
    Beschreibung: 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.
    Schlagwort(e): SPACE VEHICLES
    Materialart: NASA-TM-X-62280
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 3
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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
    Publikationsdatum: 2019-06-27
    Beschreibung: 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.
    Schlagwort(e): LAUNCH VEHICLES AND SPACE VEHICLES
    Materialart: NASA-TM-X-62444 , A-6099
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 4
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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
    Publikationsdatum: 2019-07-27
    Schlagwort(e): FACILITIES, RESEARCH, AND SUPPORT
    Materialart: AIAA PAPER 72-1004 , American Institute of Aeronautics and Astronautics, Aerodynamic Testing Conference; Sept. 13-15, 1972; Palo Alto, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 5
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    The effect of ejector augmentation on test-section flow quality in the Calspan 8-ft transonic wind tunnel (1982)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Tests to determine the flow disturbances effects of four ejectors located in the corners just downstream of the diffuser in the Calspan wind tunnel are described. The flow quality in the nonejector mode is employed as the base-line configuration, and operating parameters are compared with data from other wind tunnels. During tests with the ejectors working, fluctuation levels increased between Mach 0.4-0.6, while temperature and vorticity levels remained constant. The ejector exhibited broad spectrum noise typical of free jet noise, yet static pressure measurements revealed only a slight increase in the broadband rms levels with the ejectors on, indicating negligible disturbances upstream caused by the ejectors. Choking the diffuser eliminated the jet noise, and the use of ejectors in the Mach range considered is concluded to cause no significant degradation in the Calspan tunnel flow quality.
    Schlagwort(e): RESEARCH AND SUPPORT FACILITIES (AIR)
    Materialart: AIAA PAPER 82-0571 , In: Aerodynamic Testing Conference; Mar 22, 1982 - Mar 24, 1982; Williamsburg, VA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 6
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    Power- and cross-spectra and space-time correlations of surface fluctuating pressures at Mach numbers between 1.6 and 2.5 (1969)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Statistical analysis of pressure fluctuations in separated turbulent boundary layer
    Schlagwort(e): FLUID MECHANICS
    Materialart: NASA-TN-D-5440
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 7
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    Measurements of surface-pressure fluctuations on the XB-70 airplane at local Mach numbers up to 2.45 (1973)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Measurements of surface-pressure fluctuations were made at two locations on the XB-70 airplane for nine flight-test conditions encompassing a local Mach number range from 0.35 to 2.45. These measurements are presented in the form of estimated power spectral densities, coherence functions, and narrow-band-convection velocities. The estimated power spectral densities compared favorably with wind-tunnel data obtained by other experimenters. The coherence function and convection velocity data supported conclusions by other experimenters that low-frequency surface-pressure fluctuations consist of small-scale turbulence components with low convection velocity.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TN-D-7226 , H-714
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 8
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    Power- and cross-spectra and space-time correlations of surface fluctuating pressures at Mach numbers between 1.6 and 2.5. (1968)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: Statistics of pressure fluctuations on surfaces adjacent to attached and separated turbulent boundary layers, giving power and cross spectra and space-time correlations
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA PAPER 68-77 , AEROSPACE SCIENCES MEETING; Jan 22, 1968 - Jan 24, 1968; NEW YORK, NY
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 9
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    A fluctuating surface pressure test technique utilizing Mach number sweeps at transonic speeds (1974)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A multichannel on-line RMS data acquisition and reduction system has been developed using commercial RMS computing modules and a programmable calculator. Details of this system, which has the capability of acquiring 96 channels of RMS data and computing and printing desired parameters in near real-time, are presented. In addition, raw data can be recorded at a much higher rate for computation and printing later. Results are presented showing the benefits of this system in 'sweep' tests where one parameter such as Mach number or angle of attack is slowly varied with time.
    Schlagwort(e): INSTRUMENTATION AND PHOTOGRAPHY
    Materialart: AIAA PAPER 74-634 , Aerodynamic Testing Conference; Jul 08, 1974 - Jul 10, 1974; Bethesda, MD
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 10
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    Surface-pressure fluctuations associated with aerodynamic noise on the space shuttle launch configuration at transonic and supersonic speeds (1976)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-13
    Beschreibung: A 0.035-scale space shuttle model was recently tested at Ames Research Center to define the fluctuating surface pressures during the launch phase of the full-scale vehicle. A 120-channel data acquisition and reduction system was employed to obtain fluctuating pressure measurements from 240 pressure transducers in two separate data passes. Time histories from all transducers were recorded on four 32-track FM tape recorders. A minicomputer was used to compute and record on-line rms values, the fluctuating pressure coefficient, and full-scale dB levels. The minicomputer also partially controlled the test conditions and fully controlled all data acquisition sequences, thus greatly improving the efficiency of test operations. This paper presents details of the tests and illustrates the fluctuating pressures that will occur on the space shuttle and launch vehicle.
    Schlagwort(e): AERODYNAMICS
    Materialart: Structures, Structural Dynamics, and Materials Conference; May 05, 1976 - May 07, 1976; King of Prussia, PA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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