An experimental and theoretical study has shown that the applicability of far-field sonic-boom theory previously demonstrated for more slender shapes may now be extended to bodies with ratios of diameter to length as great as 2 and to Mach numbers at least as high as 4.14. This finding is of special significance in view of the limitations to the use of existing methods for the extrapolation of close-in experimental data
The results of sonic boom research studies are presented. The purpose of the studies was as follows:...
The sonic boom flight test program conducted at Jackass Flats, Nevada, during the summer and fall of...
A second-order theory for supersonic flow past slender bodies is presented. Through the introduction...
Mach number and geometry effects on level of sonic boom overpressure and applicability of Whitham th...
Wind tunnel measurements on effect of slender body shape on sonic boom pressure distribution
Wind tunnel tests were conducted to determine the characteristics of sonic booms. A theoretical exam...
Wind tunnel investigation of lift-induced sonic boom characteristics of two simple wing models at Ma...
Aircraft sonic boom characteristics predicted from near field data obtained in wind tunne
Sonic booms generated by the X-15 airplane flying at Mach numbers of 3.5 and 4.8 were measured. The ...
The Langley unitary plan unitary plan wind tunnel was used to determine the validity of a sonic-boom...
Wind tunnel investigation of delta-wing-body combination sonic boom at Mach 1.41 and 2.0
Pressure distributions, aerodynamic coefficients, and shock shapes were measured on blunt bodies of ...
AbstractBased on bodies of revolution, several flight and shape parameters are considered for invest...
Recent studies of a proposed low cross-range straight-wing space shuttle orbiter have shown that the...
This paper describes the NASA ARC program in sonic boom prediction methodologies. This activity supp...
The results of sonic boom research studies are presented. The purpose of the studies was as follows:...
The sonic boom flight test program conducted at Jackass Flats, Nevada, during the summer and fall of...
A second-order theory for supersonic flow past slender bodies is presented. Through the introduction...
Mach number and geometry effects on level of sonic boom overpressure and applicability of Whitham th...
Wind tunnel measurements on effect of slender body shape on sonic boom pressure distribution
Wind tunnel tests were conducted to determine the characteristics of sonic booms. A theoretical exam...
Wind tunnel investigation of lift-induced sonic boom characteristics of two simple wing models at Ma...
Aircraft sonic boom characteristics predicted from near field data obtained in wind tunne
Sonic booms generated by the X-15 airplane flying at Mach numbers of 3.5 and 4.8 were measured. The ...
The Langley unitary plan unitary plan wind tunnel was used to determine the validity of a sonic-boom...
Wind tunnel investigation of delta-wing-body combination sonic boom at Mach 1.41 and 2.0
Pressure distributions, aerodynamic coefficients, and shock shapes were measured on blunt bodies of ...
AbstractBased on bodies of revolution, several flight and shape parameters are considered for invest...
Recent studies of a proposed low cross-range straight-wing space shuttle orbiter have shown that the...
This paper describes the NASA ARC program in sonic boom prediction methodologies. This activity supp...
The results of sonic boom research studies are presented. The purpose of the studies was as follows:...
The sonic boom flight test program conducted at Jackass Flats, Nevada, during the summer and fall of...
A second-order theory for supersonic flow past slender bodies is presented. Through the introduction...