Accession Number N20120013698
Title Experimental Sonic Boom Measurements on a Mach 1.6 Cruise Low-Boom Configuration.
Publication Date Aug 2012
Media Count 135p
Personal Author A. A. Elmiligui D. C. Howe F. J. Wilcox K. A. Waithe L. S. Bangert T. R. Wayman
Abstract A wind tunnel test has been conducted by Gulfstream Aerospace Corporation (GAC) to measure the sonic boom pressure signature of a low boom Mach 1.6 cruise business jet in the Langley Unitary Plan Wind Tunnel at Mach numbers 1.60 and 1.80. Through a cooperative agreement between GAC and the National Aeronautics and Space Administration (NASA), GAC provided NASA access to some of the experimental data and NASA is publishing these data for the sonic boom research community. On-track and off-track near field sonic boom pressure signatures were acquired at three separation distances (0.5, 1.2, and 1.7 reference body lengths) and three angles of attack (-0.26deg, 0.26deg, and 0.68deg). The model was blade mounted to minimize the sting effects on the sonic boom signatures. Although no extensive data analysis is provided, selected data are plotted to illustrate salient features of the data. All of the experimental sonic boom pressure data are tabulated. Schlieren images of the configuration are also included.
Keywords Angle of attack
Mach number
Near fields
Sonic booms
Supersonic speed
Wind tunnel tests
Wind tunnels


 
Source Agency National Aeronautics and Space Administration
NTIS Subject Category 51A - Aerodynamics
Corporate Author National Aeronautics and Space Administration, Hampton, VA. Langley Research Center.
Document Type Technical report
Title Note N/A
NTIS Issue Number 1306
Contract Number N/A

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