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  • 1
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    Measured and calculated sonic boom signatures from six nonaxisymmetric wind tunnel models (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Correlation of measured and calculated sonic boom signatures for wind tunnel planform models
    Keywords: AIRCRAFT
    Type: 3D CONF. ON SONIC BOOM RES. 1971; P 341-350
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Measurements of sonic boom signatures from flights at cutoff Mach number (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Low Mach number supersonic flight data on sonic boom signatures at cutoff Mach number
    Keywords: AIRCRAFT
    Type: 3D CONF. ON SONIC BOOM RES. 1971; P 243-254
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Evaluation of certain minimum boom concepts (1968)
    In:  CASI
    Details
    Publication Date: 2006-03-29
    Description: Sonic boom efficiency factor analyses for rectangular configuration, high aspect ratio arrow wing, and delta wing models
    Keywords: AIRCRAFT
    Type: 2ND CONF. ON SONIC BOOM RES. 1968; P 47-55
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Measurements of sonic-boom overpressures from Apollo space vehicles (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: This paper presents representative results of sonic-boom overpressure data recorded during the launch and reentry of the Apollo 15 and 16 space vehicle systems. Comparisons are made between measured overpressures and those predicted using available theory. The measurements were obtained along the vehicle ground track at 68, 87, 92, 129, and 970 km downrange from the launch site during ascent, and at 9, 13, 55, 185, and 500 km from the splash-down point during reentry. Also included are tracings of the sonic-boom signatures along with a brief description of the launch and recovery test areas in which the measurements were obtained, the sonic-boom instrumentation deployment, flight profiles and operating conditions, and high-altitude weather information for the general measurement areas.
    Keywords: SPACE VEHICLES
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Variability in airplane noise measurements (1968)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Aircraft position and meteorological effects on accuracy of acoustic measurements for turbojet engines
    Keywords: AIRCRAFT
    Type: PROGR. OF NASA RES. RELATING TO NOISE ALLEVIATION OF LARGE SUBSONIC JET AIRCRAFT 1968; P 359-367
    Format: application/pdf
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  • 6
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    Noise from aerial bursts of fireworks (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A study was made recording the pressure time histories of the aerial bursts of mortars of various sizes launched during an actual fireworks display. The peak overpressure and duration of blast noise as well as the energy spectral density are compared with the characteristics of a blasting cap and of an F-104 aircraft at a Mach number of 1.4 and an altitude of 42,000 ft. Noise levels of the fireworks aerial bursts peaked 15 decibels below levels deemed damaging to hearing.
    Keywords: PHYSICS, GENERAL
    Type: Acoustical Society of America; vol. 54
    Format: text
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  • 7
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    An acoustic range for the measurement of the noise signature of aircraft during flyby operations (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The remotely operated multiple array acoustic range (ROMAAR), which has been developed to give direct measurement and display of aircraft noise in several measurement units during takeoff, landing, and flyby operations, is described. The ROMAAR, which provides information on the ground noise signature of aircraft, represents a unique combination of state-of-the-art digital and analog noise-recording methods, computer-controlled digital communication methods, radar tracking facilities, quick-look weather (profile) capabilities, and sophisticated data handling routines and facilities. The ROMAAR, which is operated by NASA, allows direct data feedback to the NASA Aircraft Noise Prediction Office. As many as 38 simultaneous noise measurements can be made for each aircraft overflight.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: Noise Control Engineering; 10; May-June
    Format: text
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  • 8
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    The effect of operations on the ground noise footprints associated with a large multibladed, nonbanging helicopter (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: In order to expand the data base of helicopter external noise characteristics, a flyover noise measurement program was conducted utilizing the NASA Civil Helicopter Research Aircraft. The remotely operated multiple array acoustics range (ROMAAR) and a 2560-m linear microphone array were utilized for the purpose of documenting the noise characteristics of the test helicopter during flyby and landing operations. By utilizing both ROMAAR concept and the linear array, the data necessary to plot the ground noise footprints and noise radiation patterns were obtained. Examples of the measured noise signature of the test helicopter, the ground noise footprint or contours, and the directivity patterns measured during level flyby and landing operations of a large, multibladed, nonbanging helicopter, the CH-53, are presented.
    Keywords: ACOUSTICS
    Type: Helicopter Acoustics, Pt. 2; p 519-533
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    A comparison of measured and theoretical predictions for STS ascent and entry sonic booms (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Sonic boom measurements have been obtained during the flights of STS-1 through 5. During STS-1, 2, and 4, entry sonic boom measurements were obtained and ascent measurements were made on STS-5. The objectives of this measurement program were (1) to define the sonic boom characteristics of the Space Transportation System (STS), (2) provide a realistic assessment of the validity of xisting theoretical prediction techniques, and (3) establish a level of confidence for predicting future STS configuration sonic boom environments. Detail evaluation and reporting of the results of this program are in progress. This paper will address only the significant results, mainly those data obtained during the entry of STS-1 at Edwards Air Force Base (EAFB), and the ascent of STS-5 from Kennedy Space Center (KSC). The theoretical prediction technique employed in this analysis is the so called Thomas Program. This prediction technique is a semi-empirical method that required definition of the near field signatures, detailed trajectory characteristics, and the prevailing meteorological characteristics as an input. This analytical procedure then extrapolates the near field signatures from the flight altitude to an altitude consistent with each measurement location.
    Keywords: SPACE TRANSPORTATION
    Type: Shuttle Performance: Lessons Learned, Pt. 2; p 1277-1301
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Correlation of predicted and measured sonic boom characteristics from the reentry of STS-1 orbiter (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Characteristics from sonic boom pressure signatures recorded at 11 locations during reentry of the Space Shuttle Orbiter Columbia are correlated with characteristics of wind tunnel signatures extrapolated from flight altitudes for Mach numbers ranging from 1.23 to 5.87. The flight pressure signature were recorded by microphones positioned at two levels near the descent groundtrack along the California corridor. The wind tunnel signatures used in theoretical predictions were measured using a 0.0041-scale model Orbiter. The mean difference between all measured and predicted overpressures is 12 percent from measured levels. With one exception, the flight signatures are very similar to theoretical n-waves.
    Keywords: ACOUSTICS
    Type: NASA-TP-2475 , S-544 , NAS 1.60:2475
    Format: application/pdf
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