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  • Aircraft Design, Testing and Performance  (8)
  • Instrumentation and Photography; Aerodynamics  (4)
  • Geosciences (General)  (2)
  • 1
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    Measurements of the Basic SR-71 Airplane Near-Field Signature (1999)
    In:  CASI
    Details
    Publication Date: 2009-11-17
    Description: Airplane design studies have developed configuration concepts that may produce lower sonic boom annoyance levels. Since lower noise designs differ significantly from other HSCT designs, it is necessary to accurately assess their potential before HSCT final configuration decisions are made. Flight tests to demonstrate lower noise design capability by modifying an existing airframe have been proposed for the Mach 3 SR-71 reconnaissance airplane. To support the modified SR-71 proposal, baseline in-flight measurements were made of the unmodified aircraft. These measurements of SR-71 near-field sonic boom signatures were obtained by an F-16XL probe airplane at flightpath separation distances ranging from approximately 740 to 40 ft. This paper discusses the methods used to gather and analyze the flight data, and makes comparisons of these flight data with CFD results from Douglas Aircraft Corporation and NASA Langley Research Center. The CFD solutions were obtained for the near-field flow about the SR-71, and then propagated to the flight test measurement location using the program MDBOOM.
    Keywords: Aircraft Design, Testing and Performance
    Type: High-Speed Research: 1994 Sonic Boom Workshop. Configuration, Design, Analysis and Testing; 171-197; NASA/CP-1999-209699
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  • 2
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    Low-Boom SR-71 Modified Signature Demonstration Program (1999)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: A flight program using the SR-71 airplane to validate sonic boom technologies for High-Speed Commercial Transport (HSCT) operation and potentially for low- or softened-boom design configurations is described. This program employs a shaped signature modification to the SR-71 airplane which is designed to demonstrate computational fluid dynamics (CFD) design technology at a full-scale HSCT operating condition of Mach 1.8 at 48,000 feet altitude. Test plans call for measurements in the near-field, at intermediate propagation altitudes, and through the more turbulent boundary layer near the Earth surface. The shaped signature modification to the airplane is comprised of added cross-section areas on the underside of the airplane forward of the wing and engine nacelles. Because the flight demonstration does not approach maximum SR-71 altitude or Mach number, the airplane provides more than adequate performance and maneuver margins for safe operation of the modified airplane. Probe airplane measurements in the near-field will use fast response pressure sensors. Far-field and ground-based boom measurements will use high response microphones or conventional sonic boom field recorders. Scope of the planned demonstration flights also includes ground level measurements during conditions which cause minimal signature distortion and conditions which cause high distortion of the signature.
    Keywords: Aircraft Design, Testing and Performance
    Type: High-Speed Research: 1994 Sonic Boom Workshop. Configuration, Design, Analysis and Testing; 237-248; NASA/CP-1999-209699
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  • 3
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    Shaped Sonic Boom Demonstration/Experiment Airborne Data (2004)
    In:  CASI
    Details
    Publication Date: 2019-04-04
    Description: This viewgraph presentation reviews NASA's project to demonstrate that careful design of aircraft contour the resultant sonic boom can maintain a tailored shape, propagating through a real atmosphere down to ground level. The areas in covered in this presentation are: (1) Past airborne shock measurement efforts, (2) SR-71 Sonic Boom Propagation Experiment (3) F-5E Inlet Spillage Shock Measurement (4) Flight test approach (5) GPS data (6) Shaped Sonic Boom Demonstration (SSBD) Mach calibration (7) Super Blanik L-23 sailplane (8) Near-field probing (8a)Maneuvers (8b) Control Room Displays (8c) Pressure Instrumentation (8d) Signatures.
    Keywords: Aircraft Design, Testing and Performance
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  • 4
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    The Effect of Sonic Booms on Earthquake Warning Systems (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Several aerospace companies are designing quiet supersonic business jets for service over the United States. These aircraft have the potential to increase the occurrence of mild sonic booms across the country. This leads to interest among earthquake warning (EQW) developers and the general seismological community in characterizing the effect of sonic booms on seismic sensors in the field, their potential impact on EQW systems, and means of discriminating their signatures from those of earthquakes. The SonicBREWS project (Sonic Boom Resistant Earthquake Warning Systems) is a collaborative effort between Seismic Warning Systems, Inc. (SWS) and NASA Dryden Flight Research Center. This project aims to evaluate the effects of sonic booms on EQW sensors. The study consists of exposing high-sample-rate (1000 sps) triaxial accelerometers to sonic booms with overpressures ranging from 10 to 600 Pa in the free field and the built environment. The accelerometers record the coupling of the sonic boom to the ground and surrounding structures, while microphones record the acoustic wave above ground near the sensor. Sonic booms are broadband signals with more high-frequency content than earthquakes. Even a 1000 sps accelerometer will produce a significantly aliased record. Thus the observed peak ground velocity is strongly dependent on the sampling rate, and increases as the sampling rate is reduced. At 1000 sps we observe ground velocities that exceed those of P-waves from M〈sub〉L 〈/sub〉 3 earthquakes at local distances, suggesting that sonic booms are not negligible for EQW applications. We present the results of several experiments conducted under SonicBREWS showing the effects of typical-case low amplitude sonic booms and worst-case high amplitude booms. We show the effects of various sensor placements and sensor array geometries. Finally, we suggest possible avenues for discriminating sonic booms from earthquakes for the purposes of EQW.
    Keywords: Geosciences (General)
    Type: DFRC-E-DAA-TN3366 , Seismological Society of America''s Annual Meeting; Apr 13, 2011; Memphis, TX; United States
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  • 5
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    High-Quality Seismic Observations of Sonic Booms (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The SonicBREWS project (Sonic Boom Resistant Earthquake Warning Systems) is a collaborative effort between Seismic Warning Systems, Inc. and NASA Dryden Flight Research Center. This project aims to evaluate the effects of sonic booms on Earthquake Warning Systems in order to prevent such systems from experiencing false alarms due to sonic booms. The airspace above the Antelope Valley, California includes the High Altitude Supersonic Corridor and the Black Mountain Supersonic Corridor. These corridors are among the few places in the US where supersonic flight is permitted, and sonic booms are commonplace in the Antelope Valley. One result of this project is a rich dataset of high-quality accelerometer records of sonic booms which can shed light on the interaction between these atmospheric phenomena and the solid earth. Nearly 100 sonic booms were recorded with low-noise triaxial MEMS accelerometers recording 1000 samples per second. The sonic booms had peak overpressures ranging up to approximately 10 psf and were recorded in three flight series in 2010 and 2011. Each boom was recorded with up to four accelerometers in various array configurations up to 100 meter baseline lengths, both in the built environment and the free field. All sonic booms were also recorded by nearby microphones. We present the results of the project in terms of the potential for sonic-boom-induced false alarms in Earthquake Warning Systems, and highlight some of the interesting features of the dataset.
    Keywords: Geosciences (General)
    Type: DFRC-372 , S31D-2272 , DFRC-E-DAA-TN4480 , AGU Fall Meeting 2011; Dec 05, 2011 - Dec 09, 2011; San Francisco, CA; United States
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  • 6
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    Airborne Shaped Sonic Boom Demonstration Pressure Measurements with Computational Fluid Dynamics Comparisons (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Shaped Sonic Boom Demonstration project showed for the first time that by careful design of aircraft contour the resultant sonic boom can maintain a tailored shape, propagating through a real atmosphere down to ground level. In order to assess the propagation characteristics of the shaped sonic boom and to validate computational fluid dynamics codes, airborne measurements were taken of the pressure signatures in the near field by probing with an instrumented F-15B aircraft, and in the far field by overflying an instrumented L-23 sailplane. This paper describes each aircraft and their instrumentation systems, the airdata calibration, analysis of the near- and far-field airborne data, and shows the good to excellent agreement between computational fluid dynamics solutions and flight data. The flights of the Shaped Sonic Boom Demonstration aircraft occurred in two phases. Instrumentation problems were encountered during the first phase, and corrections and improvements were made to the instrumentation system for the second phase, which are documented in the paper. Piloting technique and observations are also given. These airborne measurements of the Shaped Sonic Boom Demonstration aircraft are a unique and important database that will be used to validate design tools for a new generation of quiet supersonic aircraft.
    Keywords: Aircraft Design, Testing and Performance
    Type: 43rd AIAA Aerospace Sciences Meeting and Exhibit; Jan 10, 2005 - Jan 13, 2005; Reno, NV; United States
    Format: application/pdf
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  • 7
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    Airdata Measurement and Calibration (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This memorandum provides a brief introduction to airdata measurement and calibration. Readers will learn about typical test objectives, quantities to measure, and flight maneuvers and operations for calibration. The memorandum informs readers about tower-flyby, trailing cone, pacer, radar-tracking, and dynamic airdata calibration maneuvers. Readers will also begin to understand how some data analysis considerations and special airdata cases, including high-angle-of-attack flight, high-speed flight, and nonobtrusive sensors are handled. This memorandum is not intended to be all inclusive; this paper contains extensive reference and bibliography sections.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-104316 , H-2044 , NAS 1.15:104316 , Introduction to Flight Test Engineering; 1; Secti 11; AGARDograph-300
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  • 8
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    Preliminary Results from the QuietSpike Flight Test (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This viewgraph presentation reviews the QuietSpike flight test results. It shows the previous tests from Nearfield probes. The presentation then reviews the approach to test the QuietSpike, and shows graphics of the positions of the test vehicles. It also shows the components of the Sonic Boom Probing Noseboom. A graph of the Pressure Over- Under-shoot (Shaped Sonic Boom Demonstration (SSBD)Data) is presented. It reviews the Shock Probing Orientations, explaining that the probing plane is always behind the tail of the QuietSpike jet. Graphs of the Shock Position Geometry (SSBD Data) and the QuietSpike signature as of the test on 12/13/06, Near-Field Probing Directly Under the QuietSpike jet, and Near-Field Probing to Side, Near-Field Probing Above and to Side. Several slides review the Computational Fluid Dynamic models, and results compared to the probe tests.
    Keywords: Aircraft Design, Testing and Performance
    Type: Industry Panel Presentation at the University of Southern California; Nov 03, 2017; Los Angeles, CA; United States|Fundamental Aeronautics Program 1st Annual Meeting; Oct 30, 2007 - Nov 01, 2007; New Orleans, LA; United States
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  • 9
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    An Optimal Deconvolution Method for Reconstructing Pneumatically Distorted Near-Field Sonic Boom Pressure Measurements (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: In-flight measurements of the SR-71 near-field sonic boom were obtained by an F-16XL airplane at flightpath separation distances from 40 to 740 ft. Twenty-two signatures were obtained from Mach 1.60 to Mach 1.84 and altitudes from 47,600 to 49,150 ft. The shock wave signatures were measured by the total and static sensors on the F-16XL noseboo. These near-field signature measurements were distorted by pneumatic attenuation in the pitot-static sensors and accounting for their effects using optimal deconvolution. Measurement system magnitude and phase characteristics were determined from ground-based step-response tests and extrapolated to flight conditions using analytical models. Deconvolution was implemented using Fourier transform methods. Comparisons of the shock wave signatures reconstructed from the total and static pressure data are presented. The good agreement achieved gives confidence of the quality of the reconstruction analysis. although originally developed to reconstruct the sonic boom signatures from SR-71 sonic boom flight tests, the methods presented here generally apply to other types of highly attenuated or distorted pneumatic measurements.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA TP-4000 , H-2054 , H-2943 , DFRC-968
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  • 10
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    Sonic Booms in Atmospheric Turbulence (SonicBAT) Ground Measurements in a Hot Desert Climate (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Sonic Booms in Atmospheric Turbulence (SonicBAT) Project flew a series of 20 F-18 flights with 69 supersonic passes at Edwards Air Force Base in July 2016 to quantify the effect of atmospheric turbulence on sonic booms. Most of the passes were at a pressure altitude of 32,000 feet and a Mach number of 1.4, yielding a nominal sonic boom overpressure of 1.6 pounds per square foot. Atmospheric sensors such as GPS sondeballoons, Sonic Detection and Ranging (SODAR) acoustic sounders, and ultrasonic anemometers were used to characterize the turbulence state of the atmosphere for each flight. Spiked signatures in excess of 7 pounds per square foot were measured at some locations, as well as rounded sonic-boom signatures with levels much lower than the nominal. This presentation will quantify the range of overpressure and Perceived Level of the sonic boom as a function of turbulence parameters, and also present the spatial variation of these quantities over the array. Comparison with historical data will also be shown.
    Keywords: Aircraft Design, Testing and Performance
    Type: AFRC-E-DAA-TN43652 , Industry Panel Presentation at the University of Southern California; Nov 03, 2017; Los Angeles, CA; United States|Acoustics 2017; Jun 25, 2017 - Jun 29, 2017; Boston, MA; United States
    Format: application/pdf
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